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Apollo CSM

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Apollo CSM Credit: � Mark Wade

AKA: Command Service Module. Status: Operational 1967. First Launch: 1967-11-09. Last Launch: 1975-07-15. Number: 17 . Thrust: 97.86 kN (22,000 lbf). Gross mass: 30,329 kg (66,863 lb). Unfuelled mass: 11,841 kg (26,104 lb). Specific impulse: 314 s. Height: 11.03 m (36.18 ft).

Block II CSM's were the only version to fly manned, and they successfully ferried crews to the moon, to the Skylab space station, and to a joint docking with the Russian Soyuz. No production was undertaken after the initial run of 13 Block II capsules - Apollo was abandoned in favor of the Shuttle as the ferry for American manned spaceflight. Forty years later, the Shuttle was to be retired, and a design similar to the Apollo, the CEV, was conceived as the Shuttle's 'replacement'.

Unit Cost $: 77.000 million. Crew Size: 3. Habitable Volume: 6.17 m3. RCS total impulse: 3,774 kgf-sec. Spacecraft delta v: 2,804 m/s (9,199 ft/sec). Electric System: 690.00 kWh. Electric System: 6.30 average kW.

Apollo A American manned space station. Study 1961. Apollo A was a lighter-weight July 1961 version of the Apollo spacecraft.

Apollo X American manned space station. Study 1963.

Apollo Martin 410 American manned lunar lander. Study 1961. The Model 410 was Martin's preferred design for the Apollo spacecraft.

Apollo Direct 2-Man American manned lunar lander. Study 1961. A direct lunar lander design of 1961, capable of being launched to the moon in a single Saturn V launch through use of a 75% scale 2-man Apollo command module.

Apollo W-1 American manned spacecraft. Study 1962. Martin's W-1 design for the Apollo spacecraft was an alternative to the preferred L-2C configuration. The 2652 kg command module was a blunt cone lifting body re-entry vehicle, 3.45 m in diameter, 3.61 m long.

Apollo M-1 American manned spacecraft. Study 1962. Convair/Astronautics preferred M-1 Apollo design was a three-module lunar-orbiting spacecraft.

Apollo D-2 American manned lunar orbiter. Study 1962. The General Electric design for Apollo put all systems and space not necessary for re-entry and recovery into a separate jettisonable 'mission module', joined to the re-entry vehicle by a hatch.

Apollo R-3 American manned spacecraft. Study 1962. General Electric's Apollo horizontal-landing alternative to the ballistic D-2 capsule was the R-3 lifting body. This modified lenticular shape provided a lift-to-drag ratio of just 0.

Apollo L-2C American manned spacecraft. Study 1962. Martin's L-2C design was the basis for the Apollo spacecraft that ultimately emerged. The 2590 kg command module was a flat-bottomed cone, 3. 91 m in diameter, 2.67 m high, with a rounded apex.

Apollo Lenticular American manned spacecraft. Study 1962. The Convair/Astronautics alternate Lenticular Apollo was a flying saucer configuration with the highest hypersonic lift to drag ratio (4.4) of any proposed design.

Apollo LES American test vehicle. Flight tests from a surface pad of the Apollo Launch Escape System using a boilerplate capsule.

Apollo CSM Boilerplate American manned spacecraft. Boilerplate structural Apollo CSM's were used for various systems and booster tests, especially proving of the LES (launch escape system).

Apollo CSM Block I American manned spacecraft. The Apollo Command Service Module was the spacecraft developed by NASA in the 1960's as a standard spacecraft for earth and lunar orbit missions.

FIRE American re-entry vehicle technology satellite. 2 launches, 1964.04.14 (FIRE 1) and 1965.05.22 (FIRE 2). Suborbital re-entry test program that used a subscale model of the Apollo Command Module to verify the configuration at high reentry speed.

Apollo Experiments Pallet American manned lunar orbiter. Study 1965. The Apollo Experiments Pallet was a sophisticated instrument payload that would have been installed in the Apollo CSM for dedicated lunar or earth orbital resource assessment missions.

Apollo SMLL American lunar logistics spacecraft. Study 1966. North American Aviation (NAA) proposed use of the SM as a lunar logistics vehicle (LLV) in 1966. The configuration, simply stated, put a landing gear on the SM.

Apollo CMLS American manned lunar habitat. Study 1966.

Apollo RM American logistics spacecraft. Study 1967. In 1967 it was planned that Saturn IB-launched Orbital Workshops would be supplied by Apollo CSM spacecraft and Resupply Modules (RM) with up to three metric tons of supplies and instruments.

Apollo 120 in Telescope American manned space station. Study 1968. Concept for use of a Saturn V-launched Apollo CSM with an enormous 10 m diameter space laboratory equipped with a 3 m diameter astronomical telescope.

Apollo LMAL American manned space station. Study 1968.

Apollo Rescue CSM American manned rescue spacecraft. Study 1970. Influenced by the stranded Skylab crew portrayed in the book and movie 'Marooned', NASA provided a crew rescue capability for the first time in its history.

Apollo ASTP Docking Module American manned space station module. Docking Module 2. The ASTP docking module was basically an airlock with docking facilities on each end to allow crew transfer between the Apollo and Soyuz spacecraft.

Apollo CM Escape Concept American manned rescue spacecraft. Study 1976. Escape capsule using Apollo command module studied by Rockwell for NASA for use with the shuttle in the 1970's-80's. Mass per crew: 750 kg.

Photo Gallery

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Apollo 15 CSM Apollo 15 CSM over Lunar Surface Credit: NASA

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Apollo CSM / LM Apollo Command Service Module and Lunar Module Credit: � Mark Wade

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Apollo CSM Credit: � Mark Wade

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Apollo CSM

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Apollo vs N1-L3 Apollo CSM / LM vs L3 Lunar Complex Credit: � Mark Wade

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Apollo CSM Apollo CSM with Launch Escape Tower Credit: � Mark Wade

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Apollo CSM Interior Interior of the Apollo Command Service Module on display at Kennedy Space Centre, Florida. Credit: � Mark Wade

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Apollo 10 Credit: Manufacturer Image

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Saturn 6 Credit: Manufacturer Image

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Convair Apollo Credit: NASA

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Apollo Competitors Credit: NASA

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Apollo with Vanes Credit: NASA

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• National space flight program proposed - . Nation: USA. Spacecraft: Apollo CSM, CSM Source Selection.

  The Rocket and Satellite Research Panel, established in 1946 as the V-2 Upper Atmosphere Research Panel and renamed the Upper Atmosphere Rocket Research Panel in 1948, together with the American Rocket Society proposed a national space flight program and a unified National Space Establishment. The mission of such an Establishment would be nonmilitary in nature, specifically excluding space weapons development and military operations in space. By 1959, this Establishment should have achieved an unmanned instrumented hard lunar landing and, by 1960, an unmanned instrumented lunar satellite and soft lunar landing. Manned circumnavigation of the moon with return to earth should have been accomplished by 1965 with a manned lunar landing mission taking place by 1968. Beginning in 1970, a permanent lunar base should be possible.

• Special Committee on Space Technology established - . Nation: USA. Spacecraft: Apollo CSM, CSM Source Selection. NACA established a Special Committee on Space Technology to study the problems of space flight. H. Guyford Stever of the Massachusetts Institute of Technology (MIT) was named Chairman. On November 21, 1957, NACA had authorized formation of the Committee..

• Stever Committee report on the civilian space program - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS, CSM Source Selection.

  The Stever Committee, which had been set up on January 12, submitted its report on the civilian space program to NASA. Among the recommendations:

  • A vigorous, coordinated attack should be made upon the problems of maintaining the performance capabilities of man in the space environment as a prerequisite to sophisticated space exploration.
  • Sustained support should be given to a comprehensive instrumentation development program, establishment of versatile dynamic flight simulators, and provision of a coordinated series of vehicles for testing components and subsystems.
  • Serious study should be made of an equatorial launch capability.
  • Lifting reentry vehicles should be developed.
  • Both the clustered- and single-engine boosters of million-pound thrust should be developed.
  • Research on high-energy propellant systems for launch vehicle upper stages should receive full support.
  • The performance capabilities of various combinations of existing boosters and upper stages should be evaluated, and intensive development concentrated on those promising greatest usefulness in different categories of payload.

• Working Group on Lunar Exploration established by NASA - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  A Working Group on Lunar Exploration was established by NASA at a meeting at Jet Propulsion Laboratory (JPL). Members of NASA, JPL, Army Ballistic Missile Agency, California Institute of Technology, and the University of California participated in the meeting. The Working Group was assigned the responsibility of preparing a lunar exploration program, which was outlined: circumlunar vehicles, unmanned and manned; hard lunar impact; close lunar satellites; soft lunar landings (instrumented). Preliminary studies showed that the Saturn booster with an intercontinental ballistic missile as a second stage and a Centaur as a third stage, would be capable of launching manned lunar circumnavigation spacecraft and instrumented packages of about one ton to a soft landing on the moon.

• Exploration of the moon a NASA responsibility - . Nation: USA. Related Persons: Johnson, Roy. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  Roy W. Johnson, Director of the Advanced Research Projects Agency (ARPA), testified before the House Committee on Science and Astronautics that DOD and ARPA had no lunar landing program. Herbert F. York, DOD Director of Defense Research and Engineering, testified that exploration of the moon was a NASA responsibility.

• Steps toward a manned lunar landing - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  At the second meeting of the Research Steering Committee on Manned Space Flight, held at the Ames Research Center, members presented reports on intermediate steps toward a manned lunar landing and return.

  Bruce T. Lundin of the Lewis Research Center reported to members on propulsion requirements for various modes of manned lunar landing missions, assuming a 10,000-pound spacecraft to be returned to earth. Lewis mission studies had shown that a launch into lunar orbit would require less energy than a direct approach and would be more desirable for guidance, landing reliability, etc. From a 500,000 foot orbit around the moon, the spacecraft would descend in free fall, applying a constant-thrust decelerating impulse at the last moment before landing. Research would be needed to develop the variable-thrust rocket engine to be used in the descent. With the use of liquid hydrogen, the launch weight of the lunar rocket and spacecraft would be 10 to 11 million pounds. Additional Details: here....

• Meetings of the STG New Projects Panel to discuss an advanced manned space flight program - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection. Meetings of the STG New Projects Panel to discuss an advanced manned space flight program. .

• The New Projects Panel of Space Task Group (STG) met for the first time. - . Nation: USA. Spacecraft: Apollo CSM, Gemini Parachute.

  The New Projects Panel of Space Task Group (STG) met for the first time, with H. Kurt Strass in the chair. The panel was to consider problems related to atmospheric reentry at speeds approaching escape velocity, maneuvers in the atmosphere and space, and parachute recovery for earth landing. Alan B. Kehlet of STG's Flight Systems Division was assigned to initiate a program leading to a second-generation capsule incorporating several advances over the Mercury spacecraft: It would carry three men; it would be able to maneuver in space and in the atmosphere; the primary reentry system would be designed for water landing, but land landing would be a secondary goal. At the next meeting, on August 18, Kehlet offered some suggestions for the new spacecraft. The ensuing discussion led panel members to agree that a specifications list should be prepared as the first step in developing an engineering design requirement.

• NASA's future manned space program - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute, CSM Source Selection.

  The STG New Projects Panel (proposed by H. Kurt Strass in June) held its first meeting to discuss NASA's future manned space program. Present were Strass, Chairman, Alan B. Kehlet, William S. Augerson, Jack Funk, and other STG members. Strass summarized the philosophy behind NASA's proposed objective of a manned lunar landing : maximum utilization of existing technology in a series of carefully chosen projects, each of which would provide a firm basis for the next step and be a significant advance in its own right. Additional Details: here....

• First major new NASA project to be a second-generation reentry capsule - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  At its second meeting, STG's New Projects Panel decided that the first major project to be investigated would be the second-generation reentry capsule. The Panel was presented a chart outlining the proposed sequence of events for manned lunar mission system analysis. The target date for a manned lunar landing was 1970.

• Lunar flights to originate from space platforms in earth orbit - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection, LM Mode Debate, LM Source Selection.

  A House Committee Staff Report stated that lunar flights would originate from space platforms in earth orbit according to current planning. The final decision on the method to be used, "which must be made soon," would take into consideration the difficulty of space rendezvous between a space platform and space vehicles as compared with the difficulty of developing single vehicles large enough to proceed directly from the earth to the moon.

• MIT study of the guidance and control design for a variety of space missions - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance, CSM Source Selection. A study of the guidance and control design for a variety of space missions began at the MIT Instrumentation Laboratory under a NASA contract..

• Lenticular-shaped vehicle proposed for the lunar mission - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield, CSM Source Selection.

  At the third meeting of STG's New Projects Panel, Alan B. Kehlet presented suggestions for the multimanned reentry capsule. A lenticular-shaped vehicle was proposed, to ferry three occupants safely to earth from a lunar mission at a velocity of about 36,000 feet per second.

• Importance of weight of end vehicle in the lunar landing mission - . Nation: USA. Related Persons: Goett. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection, LM Mode Debate, LM Source Selection.

  In a memorandum to the members of the Research Steering Committee on Manned Space Flight, Chairman Harry J. Goett discussed the increased importance of the weight of the "end vehicle" in the lunar landing mission. This was to be an item on the agenda of the third meeting of the Committee, to be held in early December. Abe Silverstein, Director of the NASA Office of Space Flight Development, had recently mentioned to Goett that a decision would be made within the next few weeks on the configuration of successive generations of Saturn, primarily the upper stages, Silverstein and Goett had discussed the Committee's views on a lunar spacecraft. Goett expressed the hope in the memorandum that members of the Committee would have some specific ideas at their forthcoming meeting about the probable weight of the spacecraft.

  In addition, Goett informed the Committee that the Vega had been eliminated as a possible booster for use in one of the intermediate steps leading to the lunar mission. The primary possibility for the earth satellite mission was now the first-generation Saturn and for the lunar flight the second-generation Saturn.

• NASA's Ten-Year Plan presented to Congress - . Nation: USA. Related Persons: Glennan. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  In testimony before the House Committee on Science and Astronautics, Richard E. Horner, Associate Administrator of NASA, presented NASA's ten-year plan for 1960-1970. The essential elements had been recommended by the Research Steering Committee on Manned Space Flight. NASA's Office of Program Planning and Evaluation, headed by Homer J. Stewart, formalized the ten-year plan.

  On February 19, NASA officials again presented the ten-year timetable to the House Committee. A lunar soft landing with a mobile vehicle had been added for 1965. On March 28, NASA Administrator T. Keith Glennan described the plan to the Senate Committee on Aeronautical and Space Sciences. He estimated the cost of the program to be more than $1 billion in Fiscal Year 1962 and at least $1.5 billion annually over the next five years, for a total cost of $12 to $15 billion. Additional Details: here....

• Name Apollo suggested - . Nation: USA. Related Persons: Faget, Gilruth, Silverstein. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  At a luncheon in Washington, Abe Silverstein, Director of the Office of Space Flight Programs, suggested the name "Apollo" for the manned space flight program that was to follow Mercury. Others at the luncheon were Don R. Ostrander from NASA Headquarters and Robert R. Gilruth, Maxime A. Faget, and Charles J. Donlan from STG.

• Advanced manned space flight program - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield, CSM Source Selection.

  At a NASA staff conference at Monterey, Calif., officials discussed the advanced manned space flight program, the elements of which had been presented to Congress in January. The Goddard Space Flight Center was asked to define the basic assumptions to be used by all groups in the continuing study of the lunar mission. Some problems already raised were: the type of heatshield needed for reentry and tests required to qualify it, the kind of research and development firings, and conditions that would be encountered in cislunar flight. Additional Details: here....

• Preliminary guidelines for the advanced manned spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection. STG formulated preliminary guidelines by which an "advanced manned spacecraft and system" would be developed. These guidelines were further refined and elaborated; they were formally presented to NASA Centers during April and May..

• Guidelines for an advanced manned spacecraft program - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection. Presentation by STG members of the guidelines for an advanced manned spacecraft program to NASA Centers..

• Command and communications guidelines for the advanced manned spacecraft program listed - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  Command and communications guidelines for the advanced manned spacecraft program were listed by STG's Robert G. Chilton at NASA Centers:

  1. Primary command of the mission should be on board. Since a manned spacecraft would necessarily be much more complex and its cost much greater than an unmanned spacecraft, maximum use should be made of the command decision and operational capabilities of the crew. Studies would be needed to determine the extent of these capabilities under routine, urgent, and extreme emergency conditions. Onboard guidance and navigation hardware would include inertial platforms for monitoring insertion guidance, for abort command, and for abort-reentry navigation; optical devices; computers; and displays. Attitude control would require a multimode system.
  2. Communications and ground tracking should be provided throughout the mission except when the spacecraft was behind the moon. Voice contact once per orbit was considered sufficient for orbital missions. For the lunar mission, telemetry would be required only for backup data since the crew would relay periodic voice reports. Television might be desirable for the lunar mission. For ground tracking, a study of the Mercury system would determine whether the network could be modified and relocated to satisfy the close-in requirements of a lunar mission. The midcourse and circumlunar tracking requirements might be met by the deep-space network facilities at Goldstone, Calif., Australia, and South Africa. Both existing and proposed facilities should be studied to ensure that frequencies for all systems could be made compatible to permit use of a single beacon for midcourse and reentry tracking.

• Guidelines for human factors in the advanced manned spacecraft program - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS, CSM Source Selection.

  Stanley C. White of STG outlined at NASA Centers the guidelines for human factors in the advanced manned spacecraft program:

  1. A "shirtsleeve" spacecraft environment would be necessary because of the long duration of the lunar flight. This would call for a highly reliable pressurized cabin and some means of protection against rapid decompression. Such protection might be provided by a quick-donning pressure suit. Problems of supplying oxygen to the spacecraft; removing carbon dioxide, water vapor, toxic gases, and microorganisms from the capsule atmosphere; basic monitoring instrumentation; and restraint and couch design were all under study. In addition, research would be required on noise and vibration in the spacecraft, nutrition, waste disposal, interior arrangement and displays, and bioinstrumentation.
  2. A minimum crew of three men was specified. Studies had indicated that, for a long-duration mission, multiman crews were necessary and that three was the minimum number required.
  3. The crew should not be subjected to more than a safe radiation dose. Studies had shown that it was not yet possible to shield the crew against a solar flare. Research was indicated on structural materials and equipment for radiation protection, solar-flare prediction, minimum radiation trajectories, and the radiation environment in cislunar space.

• Advanced manned spacecraft program guidelines for aborted missions and landing - . Nation: USA. Related Persons: Faget. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery, CSM Source Selection.

  In discussing the advanced manned spacecraft program at NASA Centers, Maxime A. Faget of STG detailed the guidelines for aborted missions and landing:

  1. The spacecraft must have a capability of safe crew recovery from aborted missions at any speed up to the maximum velocity, this capability to be independent of the launch propulsion system.
  2. A satisfactory landing by the spacecraft on both water and land, avoiding local hazards in the recovery area, was necessary. This requirement was predicated on two considerations: emergency conditions or navigation errors could force a landing on either water or land; and accessibility for recovery and the relative superiority of land versus water landing would depend on local conditions and other factors. The spacecraft should be able to land in a 30-knot wind, be watertight, and be seaworthy under conditions of 10- to 12-foot waves.
  3. Planned landing capability by the spacecraft at one of several previously designated ground surface locations, each approximately 10 square miles in area, would be necessary. Studies were needed to assess the value of impulse maneuvers, guidance quality, and aerodynamic lift over drag during the return from the lunar mission. Faget pointed out that this requirement was far less severe for the earth orbit mission than for the lunar return.
  4. The spacecraft design should provide for crew survival for at least 72 hours after landing. Because of the unpredictability of possible emergency maneuvers, it would be impossible to provide sufficient recovery forces to cover all possible landing locations. The 72-hour requirement would permit mobilization of normally existing facilities and enough time for safe recovery. Locating devices on the spacecraft should perform adequately anywhere in the world.
  5. Auxiliary propulsion should be provided for guidance maneuvers needed to effect a safe return in a launch emergency. Accuracy and capability of the guidance system should be studied to determine auxiliary propulsion requirements. Sufficient reserve propulsion should be included to accommodate corrections for maximum guidance errors. The single system could serve for either guidance maneuvers or escape propulsion requirements.

• Guidelines for an advanced manned spacecraft program presented by STG - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS, CSM Source Selection.

  Members of STG presented guidelines for an advanced manned spacecraft program to NASA Centers to enlist research assistance in formulating spacecraft and mission design.

  To open these discussions, Director Robert R. Gilruth summarized the guidelines: manned lunar reconnaissance with a lunar mission module, corollary earth orbital missions with a lunar mission module and with a space laboratory, compatibility with the Saturn C-1 or C-2 boosters (weight not to exceed 15,000 pounds for a complete lunar spacecraft and 25,000 pounds for an earth orbiting spacecraft), 14-day flight time, safe recovery from aborts, ground and water landing and avoidance of local hazards, point (ten square-mile) landing, 72-hour postlanding survival period, auxiliary propulsion for maneuvering in space, a "shirtsleeve" environment, a three-man crew, radiation protection, primary command of mission on board, and expanded communications and tracking facilities. In addition, a tentative time schedule was included, projecting multiman earth orbit qualification flights beginning near the end of the first quarter of calendar year 1966.

• STG brief advanced manned spacecraft program - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  STG members, visiting Moffett Field, Calif., briefed representatives of the Jet Propulsion Laboratory, Flight Research Center, and Ames Research Center on the advanced manned spacecraft program. Ames representatives then described work at their Center which would be applicable to the program: preliminary design studies of several aerodynamic configurations for reentry from a lunar trajectory, guidance and control requirements studies, potential reentry heating experiments at near-escape velocity, flight simulation, and pilot display and navigation studies. STG asked Ames to investigate heating and aerodynamics on possible lifting capsule configurations. In addition, Ames offered to tailor a payload applicable to the advanced program for a forthcoming Wallops Station launch.

• Guidelines for the advanced manned spacecraft program presented by STG - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection. Briefings on the guidelines for the advanced manned spacecraft program were presented by STG representatives at NASA Headquarters..

• Space Exploration Program Council - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  In a memorandum to NASA Administrator T. Keith Glennan, Robert L. King, Executive Secretary of the Space Exploration Program Council (SEPC), reported on the status of certain actions taken up at the first meeting of the Council:

  • Rather than appoint a separate Senior Steering Group to resolve policy problems connected with the reliability program, SEPC itself tentatively would be used. A working committee would be appointed for each major system and would and rely on the SEPC for broad policy guidance,
  • Proposed rescheduling of the first Atlas-Agena 13 lunar mission for an earlier flight date was abandoned as impractical.

• Proposed advanced manned spacecraft program presented to von Braun - . Nation: USA. Related Persons: von Braun. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  Members of STG presented the proposed advanced manned spacecraft program to Wernher von Braun and 25 of his staff at Marshall Space Flight Center. During the ensuing discussion, the merits of a completely automatic circumlunar mission were compared with those of a manually operated mission. Further discussions were scheduled.

• Proposed advanced manned spacecraft program presented to Lewis Research Center - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  STG members presented the proposed advanced manned spacecraft program to the Lewis Research Center staff. Work at the Center applicable to the program included: analysis and preliminary development of the onboard propulsion system, trajectory analysis, and development of small rockets for midcourse and attitude control propulsion.

• Discussion on the advanced manned spacecraft program at Langley - . Nation: USA. Related Persons: Goett, Low, George. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  A discussion on the advanced manned spacecraft program was held at the Langley Research Center with members of STG and Langley Research Center, together with George M. Low and Ernest O. Pearson, Jr., of NASA Headquarters and Harry J. Goett of Goddard Space Flight Center. Floyd L. Thompson, Langley Director, said that Langley would be studying the radiation problem, making configuration tests (including a lifting Mercury) , and studying aerodynamics, heating, materials, and structures.

• Advanced Vehicle Team to make preliminary design for advanced multiman spacecraft - . Nation: USA. Related Persons: Gilruth, Maynard. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. STG formed the Advanced Vehicle Team, reporting directly to Robert R. Gilruth, Director of the Mercury program. The Team would conduct research and make preliminary design studies for an advanced multiman spacecraft.. Additional Details: here....

• Radiation and its effect on manned space flight - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield, CSM Source Selection.

  Robert O. Piland, Head of the STG Advanced Vehicle Team, and Stanley C. White of STG attended a meeting in Washington, D. C., sponsored by the NASA Office of Life Sciences Programs, to discuss radiation and its effect on manned space flight. Their research showed that it would be impracticable to shield against the inner Van Allen belt radiation but possible to shield against the outer belt with a moderate amount of protection. Additional Details: here....

• Name Apollo approved for the advanced manned space flight program - . Nation: USA. Related Persons: Glennan, Goett, Silverstein. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  NASA Director of Space Flight Programs Abe Silverstein notified Harry J. Goett, Director of the Goddard Space Flight Center, that NASA Administrator T. Keith Glennan had approved the name "Apollo" for the advanced manned space flight program. The program would be so designated at the forthcoming NASA-Industry Program Plans Conference.

• Announcement of the Apollo program to American industry - . Nation: USA. Related Persons: Low, George. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  The first NASA-Industry Program Plans Conference was held in Washington, D.C. The purpose was to give industrial management an overall picture of the NASA program and to establish a basis for subsequent conferences to be held at various NASA Centers. The current status of NASA programs was outlined, including long-range planning, launch vehicles, structures and materials research, manned space flight, and life sciences.

  NASA Deputy Administrator Hugh L. Dryden announced that the advanced manned space flight program had been named "Apollo." George M. Low, NASA Chief of Manned Space Flight, stated that circumlunar flight and earth orbit missions would be carried out before 1970. This program would lead eventually to a manned lunar landing and a permanent manned space station. Additional Details: here....

• Apollo Program Announced - . Nation: USA. Related Persons: Silverstein. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, CSM Source Selection. Name 'Apollo' selected by Silverstein. Conference with aerospace industry outlined NASA's plans for circumlunar and lunar flight..

• Tentative program of the Goddard industry conference to be held on August 30 outlined - . Nation: USA. Related Persons: Goett. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  In a memorandum to Abe Silverstein, Director of NASA's Office of Space Flight Programs, Harry J. Goett, Director of Goddard Space Flight Center, outlined the tentative program of the Goddard industry conference to be held on August 30. At this conference, more details of proposed study contracts for an advanced manned spacecraft would be presented. The requirements would follow the guidelines set down by STG and presented to NASA Headquarters during April and May. Three six-month study contracts at $250,000 each would be awarded.

• Industry briefing on feasibility studies for the Apollo spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  The Goddard Space Flight Center GSFC conducted its industry conference in Washington, D.C., presenting details of GSFC projects, current and future. The objectives of the proposed six-month feasibility contracts for an advanced manned spacecraft were announced. Additional Details: here....

• STG briefing for prospective bidders for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection. An STG briefing was held at Langley Field, Va., for prospective bidders on three six-month feasibility studies of an advanced manned spacecraft as part of the Apollo program. A formal Request for Proposal was issued at the conference..

• Apollo Study Bidder's Conference - . Nation: USA. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, Apollo Lunar Landing, CSM ECS, CSM Source Selection. Bidder's conference for circumlunar Apollo. Specification: Saturn C-2 compatability (6,800 kg mass for circumlunar mission); 14 day flight time; three-man crew in shirt-sleeve environment..

• STG Evaluation Board for advanced manned spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  Charles J. Donlan of STG, Chairman of the Evaluation Board which would consider contractors' proposals on feasibility studies for an advanced manned spacecraft, invited the Directors of Ames Research Center, Jet Propulsion Laboratory, Flight Research Center, Lewis Research Center, Langley Research Center, and Marshall Space Flight Center to name representatives to the Evaluation Board. The first meeting was to be held on October 10 at Langley Field, Va.

• Evaluation Boards formed to consider industry proposals for Apollo spacecraft - . Nation: USA. Related Persons: Faget, Goett. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  Members were appointed to the Technical Assessment Panels and the Evaluation Board to consider industry proposals for Apollo spacecraft feasibility studies. Members of the Evaluation Board were: Charles J. Donlan (STG), Chairman; Maxime A. Faget (STG) ; Robert O. Piland (STG), Secretary; John H. Disher (NASA Headquarters Office of Space Flight Programs); Alvin Seiff (Ames); John V. Becker (Langley); H. H. Koelle (Marshall); Harry J. Goett (Goddard), ex officio; and Robert R. Gilruth (STG), ex officio.

• Contractors' proposals for an advanced manned spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  Contractors' proposals on feasibility studies for an advanced manned spacecraft were received by STG. Sixty-four companies expressed interest in the Apollo program, and of these 14 actually submitted proposals: The Boeing Airplane Company; Chance Vought Corporation; Convair/Astronautics Division of General Dynamics Corporation; Cornell Aeronautical Laboratory, Inc.; Douglas Aircraft Company; General Electric Company; Goodyear Aircraft Corporation; Grumman Aircraft Engineering Corporation; Guardite Division of American Marietta Company; Lockheed Aircraft Corporation; The Martin Company; North American Aviation, Inc.; and Republic Aviation Corporation. These 14 companies, later reduced to 12 when Cornell and Guardite withdrew, were subsequently invited to submit prime contractor proposals for the Apollo spacecraft development in 1961. The Technical Assessment Panels began evaluation of contractors' proposals on October 10.

• Evaluation completed on proposals for an advanced manned spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  The Technical Assessment Panels presented to the Evaluation Board their findings on the contractors' proposals for feasibility studies of an advanced manned spacecraft. On October 24, the Evaluation Board findings and recommendations were presented to the STG Director.

• Design constraints for in-house study of the Apollo spacecraft - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. A staff meeting of STG's Flight Systems Division was held to fix additional design constraints for the in- house design study of the Apollo spacecraft.

  Fundamental decisions were made as a result of this and a previous meeting on September 20.. Additional Details: here....

• Apollo Initial Study Contracts - . Nation: USA. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, CSM Source Selection. From 16 bids, Convair, General Electric, and Martin selected to conduct $250,000 study contracts. Meanwhile Space Task Group Langley undertakes its own studies, settling on Apollo CM configuration as actually built by October 1960..

• Convair, General Electric, and Martin selected to prepare Apollo spacecraft feasibility studies - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  NASA selected three contractors to prepare individual feasibility studies of an advanced manned spacecraft as part of Project Apollo. The contractors were Convair/Astronautics Division of General Dynamics Corporation, General Electric Company, and The Martin Company.

• General Electric, Martin, and General Dynamics negotiate Apollo systems study contracts - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  Representatives of the General Electric Company, The Martin Company, and Convair/Astronautics Division of General Dynamics Corporation visited STG to conduct negotiations on the Apollo systems study contracts announced on October 25. The discussions clarified or identified areas not completely covered in company proposals. Contracts were awarded on November 15.

• MIT navigation and guidance support for Project Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance, CSM Source Selection.

  STG held a meeting at Goddard Space Flight Center to discuss a proposed contract with MIT Instrumentation Laboratory for navigation and guidance support for Project Apollo. The proposed six-month contract for $100,000 might fund studies through the preliminary design stage but not actual hardware. Milton B. Trageser of the Instrumentation Laboratory presented a draft work statement which divided the effort into three parts: midcourse guidance, reentry guidance, and a satellite experiment feasibility study using the Orbiting Geophysical Observatory. STG decided that the Instrumentation Laboratory should submit a more detailed draft of a work statement to form the basis of a contract. In a discussion the next day, Robert G. Chilton of STG and Trageser clarified three points:

  1. The current philosophy was that an onboard computer program for a normal mission sequence would be provided and would be periodically updated by the crew. If the crew were disabled, the spacecraft would continue on the programmed flight for a normal return. No capability would exist for emergency procedures.
  2. Chilton emphasized that consideration of the reentry systems design should include all the guideline requirements for insertion monitoring by the crew, navigation for aborted missions, and, in brief, the whole design philosophy for manned flight.
  3. The long-term objective of a lunar landing mission should be kept in mind although design simplicity was of great importance.
  Chilton and Trageser agreed that the purpose of the Apollo program was the development of manned space flight system capability, not simply circumnavigation of the moon with an encapsulated man.

• Briefing on the Apollo and Saturn programs - . Nation: USA. Related Persons: Faget, von Braun. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection, LM Mode Debate, LM Source Selection.

  A joint briefing on the Apollo and Saturn programs was held at Marshall Space Flight Center MSFC, attended by representatives of STG and MSFC. Maxime A. Faget of STG and MSFC Director Wernher von Braun agreed that a joint STG-MSFC program would be developed to accomplish a manned lunar landing. Areas of responsibility were: MSFC launch vehicle and landing on the moon; STG - lunar orbit, landing, and return to earth.

• Study program on the guidance aspects of Project Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance, CSM Source Selection.

  Milton B. Trageser of MIT Instrumentation Laboratory transmitted to Charles J. Donlan of STG the outline of a study program on the guidance aspects of Project Apollo. He outlined what might be covered by a formal proposal on the Apollo spacecraft guidance and navigation contract discussed by STG and Instrumentation Laboratory representatives on November 22.

• First technical review of the General Electric Apollo feasibility study - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  The first technical review of the General Electric Company Apollo feasibility study was held at the contractor's Missile and Space Vehicle Department. Company representatives presented reports on the study so that STG representatives might review progress, provide General Electric with pertinent information from NASA or other sources, and discuss and advise as to the course of the study.

• Martin presented the first technical review of its Apollo feasibility study - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery, CSM Source Selection.

  The Martin Company presented the first technical review of its Apollo feasibility study to STG officials in Baltimore, Md. At the suggestion of STG, Martin agreed to reorient the study in several areas: putting more emphasis on lunar orbits, putting man in the system, and considering landing and recovery in the initial design of the spacecraft.

• Frst technical review of the Convair Apollo feasibility study - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  Convair/Astronautics Division of the General Dynamics Corporation held its first technical review of the Apollo feasibility study in San Diego, Calif. Brief presentations were made by contractor and subcontractor technical specialists to STG representatives. Convair/Astronautics' first approach was oriented toward the modular concept, but STG suggested that the integral spacecraft concept should be investigated.

• MIT proposal for a study of a navigation and guidance system for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance, CSM Source Selection. The MIT Instrumentation Laboratory submitted a formal proposal to NASA for a study of a navigation and guidance system for the Apollo spacecraft..

• Low Committee established - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, Apollo Lunar Landing, CSM Source Selection, LM Mode Debate, LM Source Selection.

  The Manned Lunar Landing Task Group (Low Committee) set up by the Space Exploration Program Council was instructed to prepare a position paper for the NASA Fiscal Year 1962 budget presentation to Congress. The paper was to be a concise statement of NASA's lunar program for Fiscal Year 1962 and was to present the lunar mission in term of both direct ascent and rendezvous. The rendezvous program would be designed to develop a manned spacecraft capability in near space, regardless of whether such a technique would be needed for manned lunar landing. In addition to answering such questions as the reason for not eliminating one of the two mission approaches, the Group was to estimate the cost of the lunar mission and the date of its accomplishment, though not in specific terms. Although the decision to land a man on the moon had not been approved, it was to be stressed that the development of the scientific and technical capability for a manned lunar landing was a prime NASA goal, though not the only one. The first meeting of the Group was to be held on January 9.

• First meeting of the Manned Lunar Landing Task Group - . Nation: USA. Related Persons: Silverstein. Program: Apollo. Spacecraft: Apollo CSM, Apollo Lunar Landing, CSM Source Selection, LM Mode Debate, LM Source Selection.

  At the first meeting of the Manned Lunar Landing Task Group, Associate Administrator Robert C. Seamans, Jr., Director of the Office of Space Flight Programs Abe Silverstein, and Director of the Office of Advanced Research Programs Ira H. Abbott outlined the purpose of the Group to the members. After a discussion of the instructions, the Group considered first the objectives of the total NASA program:

  1. the exploration of the solar system for knowledge to benefit mankind; and
  2. the development of technology to permit exploitation of space flight for scientific, military, and commercial uses.
  NASA's lunar program was a logical step toward these objectives. In current lunar program planning, three steps were projected:
  1. a manned landing on the moon with return to earth,
  2. limited manned lunar exploration, and
  3. a scientific lunar base.
  To accomplish the first step, a great increase in launch vehicle capability would be needed beyond that provided by current funding. A comparison of a three-million-pound-thrust and a six-million-pound-thrust Nova launch vehicle was made. It was estimated that a 60,000- to 80,000-pound payload to escape velocity would be needed for a manned lunar landing mission.

• STG briefed on Convair Apollo feasibility study - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  Representatives of STG visited Convair Astronautics Division of the General Dynamics Corporation to monitor the Apollo feasibility study contract. The meeting consisted of several individual informal discussions between the STG and Convair specialists on configurations and aerodynamics, heating, structures and materials, human factors, trajectory analysis, guidance and control, and operation implementation.

• Three of the Apollo Technical Liaison Groups held their first meetings - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield, CSM Source Selection.

  Three of the Apollo Technical Liaison Groups (Trajectory Analysis, Heating, and Human Factors) held their first meetings at the Ames Research Center.

  After reviewing the status of the contractors' Apollo feasibility studies, the Group on Trajectory Analysis discussed studies being made at NASA Centers. An urgent requirement was identified for a standard model of the Van Allen radiation belt which could be used in all trajectory analysis related to the Apollo program,

  The Group on Heating, after consideration of NASA and contractor studies currently in progress, recommended experimental investigation of control surface heating and determination of the relative importance of the unknowns in the heating area by relating estimated "ignorance" factors to resulting weight penalties in the spacecraft. The next day, three members of this Group met for further discussions and two areas were identified for more study: radiant heat inputs and their effect on the ablation heatshield, and methods of predicting heating on control surfaces, possibly by wind tunnel tests at high Mach numbers.

  The Group on Human Factors considered contractors' studies and investigations being done at NASA Centers. In particular, the Group discussed the STG document, "Project Apollo Life Support Programs," which proposed 41 research projects. These projects were to be carried out by various organizations, including NASA, DOD, industry, and universities. Medical support experience which might be applicable to Apollo was also reviewed.

• Briefing given to the Saturn Guidance Committee on the Apollo program - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection, LM Mode Debate, LM Source Selection.

  J. Thomas Markley of the Apollo Spacecraft Project Office reported to Associate Director of STG Charles J. Donlan that an informal briefing had been given to the Saturn Guidance Committee on the Apollo program. The Committee had been formed by Don R. Ostrander, NASA Director of the Office of Launch Vehicle Programs, to survey the broad guidance and control requirements for Saturn. The Committee was to review Marshall Space Flight Center guidance plans, review plans of mission groups who intended to use Saturn, recommend an adequate guidance system for Saturn, and prepare a report of the evaluation and results during January. Members of STG, including Robert O. Piland, Markley, and Robert G. Chilton, presented summaries of the overall Apollo program and guidance requirements for Apollo.

• First meetings of three of the Apollo Technical Liaison Groups - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  Three of the Apollo Technical Liaison Groups Structures and Materials, Configurations and Aerodynamics, and Guidance and Control held their first meetings at the Ames Research Center.

  The Group on Structures and Materials, after reviewing contractors' progress on the Apollo feasibility studies, considered reports on Apollo-related activities at NASA Centers. Among these activities were work on the radiative properties of material suitable for temperature control of spacecraft (Ames), investigation of low-level cooling systems in the reentry module (Langley), experiments on the landing impact of proposed reentry module shapes (Langley), meteoroid damage studies (Lewis), and the definition of suitable design criteria and safety factors to ensure the structural integrity of the spacecraft STG.

  The Group on Configurations and Aerodynamics recommended :

  • Investigations to determine the effects of aerodynamic heating on control surfaces.
  • Studies of the roll control maneuvers with center of gravity offset for range control.
  • Tests of packaging and deployment of paraglider and multiple parachute landing systems.
  • Studies to determine the effects of jet impingement upon the static and dynamic stability of the spacecraft.
  The various spacecraft configurations under consideration by the Apollo feasibility study contractors were reviewed:
  1. The General Electric Company effort was being concentrated on the Mark-ll, NERV, RVX (9 degree blunted cone), elliptical cone, half-cone, and Bell Aerospace Corporation Dyna-Soar types.
  2. The Martin Company was studying the M-1 and M-2 lifting bodies, the Mercury with control flap, the Hydrag (Avco Corporation), and a winged vehicle similar to Dyna-Soar. In addition, Martin was proposing to investigate the M-1-1, a lifting body halfway between the M-1 and the M- 2; a flat-bottomed lifting vehicle similar to the M-1-1 ; a lenticular shape; and modified flapped Mercury (the Langley L-2C).
  3. Convair/Astronautics Division of the General Dynamics Corporation had subcontracted the major effort on reentry to Avco, which was looking into five configurations: a Mercury-type capsule, the lenticular shape, the M-1, the flat-face cone, and half-cone.
  The Group for Guidance and Control drew up a list of suggestions for research and development programs:
  • An "absolute emergency" navigation system in which the crew would use only a Land camera and a slide rule.
  • The possible applications of the equipment and test programs to be used on Surveyor.
  • The question whether Apollo lunar landing trajectories should be based on minimum fuel expenditure - if so, doubts were raised that the current STG concept would accomplish this goal.
  • The question whether radio ranging could be used to reduce the accuracy requirements for celestial observations and whether such a composite system would fall within the limits set by the Apollo guidelines.
  • The effects of lunar impact on the return spacecraft navigation equipment.
  • Studies of hardware drift-error in the guidance and navigation systems and components.
  • A study of the effect of rotating machinery aboard the spacecraft on attitude alignment and control requirements.
  • Problems of planet tracking when the planetary disk was only partially illuminated.
  • A study of the transient effects of guidance updating by external information.
  • One adequate guidance and control concept to be mechanized and errors analyzed and evaluated.
  • The effects of artificial g configurations on observation and guidance.
  • The development of a ground display mission progress evaluation for an entire mission
  • An abort guidance sequence including an abort decision computer and pilot display
  • An earth orbit evaluation of the position computer input in a highly eccentric orbit (500- to 1000-mile perigee, 60,000-mile apogee).

• Martin progress on the Apollo feasibility study contract - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery, CSM Source Selection.

  Representatives of STG visited The Martin Company in Baltimore, Md., to review the progress of the Apollo feasibility study contract. Discussions on preliminary design of the spacecraft, human factors, propulsion, power supplies, guidance and control, structures, and landing and recovery were held with members of the Martin staff.

• Studies of manned lunar and interplanetary expeditions - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection. The Marshall Space Flight Center awarded contracts to the Douglas Aircraft Company and Chance Vought Corporation to study the launching of manned exploratory expeditions into lunar and interplanetary space from earth orbits..

• Study on the feasibility of refueling a spacecraft in orbit - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection, LM Mode Debate, LM Source Selection. NASA announced that the Lockheed Aircraft Corporation had been awarded a contract by the Marshall Space Flight Center to study the feasibility of refueling a spacecraft in orbit..

• Apollo feasibility study progress - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  Members of STG met with representatives of the Convair Astronautics Division of the General Dynamics Corporation and Avco Corporation to monitor the progress of the Apollo feasibility study. Configurations and aerodynamics and Apollo heating studies were discussed. Current plans indicated that final selection of their proposed spacecraft configuration would be made by Convair Astronautics within a week. The status of the spacecraft reentry studies was described by Avco specialists.

• MIT selected for a study of a navigation and guidance system for the Apollo spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance, CSM Source Selection. NASA selected the Instrumentation Laboratory of MIT for a six-month study of a navigation and guidance system for the Apollo spacecraft..

• STG met to plan general requirements for a proposal for advanced manned spacecraft development - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection. Management personnel from NASA Headquarters and STG met to plan general requirements for a proposal for advanced manned spacecraft development..

• Convair selects M-1 design for Apollo in preference to lenticular configuration - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield, CSM Source Selection.

  William W. Petynia of STG visited the Convair Astronautics Division of General Dynamics Corporation to monitor the Apollo feasibility study contract. A selection of the M-1 in preference to the lenticular configuration had been made by Convair. May 17 was set as the date for the final Convair presentation to NASA.

• Preparation of material for the Apollo spacecraft specification discussed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection, CSM Structural.

  The Apollo Technical Liaison Group for Structures and Materials discussed at STG the preparation of material for the Apollo spacecraft specification. It decided that most of the items proposed for its study could not be specified at that time and also that many of the items did not fall within the structures and materials area. A number of general areas of concern were added to the work plan: heat protection, meteoroid protection, radiation effects, and vibration and acoustics.

• Second meeting of the Apollo Technical Liaison Group for Configurations and Aerodynamics at STG - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute, CSM Source Selection.

  At the second meeting of the Apollo Technical Liaison Group for Configurations and Aerodynamics at STG, presentations were made on Apollo-related activities at the NASA Centers: heatshield tests (Ames Research Center); reentry configurations (Marshall Space Flight Center); reentry configurations, especially lenticular (modified) and spherically blunted, paraglider soft-landing system, dynamic stability tests, and heat transfer tests (Langley Research Center); tumbling entries in planetary atmospheres (Mars and Venus) (Jet Propulsion Laboratory); air launch technique for Dyna-Soar (Flight Research Center); and steerable parachute system and reentry spacecraft configuration (STG). Work began on the background material for the Apollo spacecraft specification.

• STG / Apollo Technical Liaison Group for Human Factors discussed Apollo spacecraft specification - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit, CSM Source Selection.

  At STG the Apollo Technical Liaison Group for Human Factors discussed the proposed outline for the spacecraft specification. Its recommendations included:

  • NASA Headquarters Offices should contact appropriate committees and other representatives of the scientific community to elicit recommendations for scientific experiments aboard the orbiting laboratory to be designed as a mission module for use with the Apollo spacecraft.
  • NASA should sponsor a conference of recognized scientists to suggest a realistic radiation dosage design limit for Apollo crews.

• Apollo Technical Liaison Group for Instrumentation and Communications drafted guidelines - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS, CSM Source Selection.

  The Apollo Technical Liaison Group for Instrumentation and Communications met at STG and drafted an informal set of guidelines and sent them to the other Technical Liaison Groups:

  • Instrumentation requirements: all Groups should submit their requests for measurements to be made on the Apollo missions, including orbital, circumlunar, and lunar landing operations.
  • Television: since full-rate, high-quality television for the missions would add a communications load that could swamp all others and add power and bandwidth requirements not otherwise needed, other Groups should restate their justification for television requirements.
  • Temperature environment; heat normally pumped overboard might be made available for temperature control systems without excessive cost and complexity.
  • Reentry communications; continuous reentry communications were not yet feasible and could not be guaranteed. It was suggested that all Groups plan their systems as though no communications would exist at altitudes between about 250,000 feet and 90,000 feet.
  • Vehicle reentry and recovery: if tracking during reentry were desired, it would be far more economical to use a water landing site along the Atlantic Missile Range or another East Coast site.
  • Digital computer : the onboard digital computer, if it were flexible enough, would permit the examination of telemetry data for bandwidth reduction before transmission.
  • Antenna-pointing information: the spacecraft should have information relative to its orientation so that any high-gain directive antenna could be positioned toward the desired location on earth.
  The Group then discussed the preparation of material for the Apollo spacecraft specification.

• Apollo spacecraft specification work - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS, CSM Source Selection.

  In preparing background material for the Apollo spacecraft specification at STG, the Apollo Technical Liaison Group for Mechanical Systems worked on environmental control systems, reaction control systems, auxiliary power supplies, landing and recovery systems, and space cabin sealing.

• Apollo Technical Liaison Group for Trajectory Analysis commented on Apollo specification - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance, CSM Source Selection.

  The Apollo Technical Liaison Group for Trajectory Analysis met at STG and began preparing material for the Apollo spacecraft specification. It recommended:

  • STG should take the initiative with NASA Headquarters in delegating responsibility for setting up and updating a uniform model of astronomical constants.
  • The name of the Group should be changed to Mission Analysis to help clarify its purpose.
  • A panel should be set up to determine the scientific experiments which could be done on board, or in conjunction with the orbiting laboratory, so that equipment, weight, volumes, laboratory characteristics, etc., might be specified

• Contract for the liquid-hydrogen liquid-oxygen fuel cell - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS, CSM Source Selection.

  A conference was held at Lewis Research Center between STG and Lewis representatives to discuss the research and development contract for the liquid-hydrogen liquid-oxygen fuel cell as the primary spacecraft electrical power source. Lewis had been provided funds approximately $300,000 by NASA Headquarters to negotiate a contract with Pratt & Whitney Aircraft Division of United Aircraft Corporation for the development of a fuel cell for the Apollo spacecraft. STG and Lewis representatives agreed that the research and development should be directed toward the liquid-hydrogen - liquid-oxygen fuel cell. Guidelines were provided by STG:

  • Power output requirement for the Apollo spacecraft was estimated at two to three kilowatts.
  • Nominal output voltage should be about 27.5 volts.
  • Regulation should be within +/- 10 percent of nominal output voltage.
  • The fuel cell should be capable of sustained operation at reduced output (10 percent of rated capacity, if possible).
  • The fuel cell and associated system should be capable of operation in a space environment.
  Lewis planned to request a pilot model of the fuel cell of about 250 watts capacity, capable of unattended operation. Contract negotiations were expected to be completed by May 2 and the model delivered within 12 months of the contract award.

• First draft of the Apollo spacecraft specification - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  STG completed the first draft of "Project Apollo, Phase A, General Requirements for a Proposal for a Manned Space Vehicle and System" (Statement of Work), an early step toward the spacecraft specification. A circumlunar mission was the basis for planning.

• Initial Study Contracts - . Nation: USA. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, CSM Source Selection.

  In initial study contracts, Martin proposed vehicle similar to the Apollo configuration that would eventually fly and closest to STG concepts. GE proposed design that would lead directly to Soyuz. Convair proposed a lifting body concept. All bidders were influenced by STG mid-term review that complained that they were not paying enough attention to conical blunt-body CM as envisioned by STG.

• Final study contract reports. - . Nation: USA. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, CSM Source Selection.

  The final reports on the feasibility study contracts for the advanced manned spacecraft were submitted to STG at Langley Field, Va., by the General Electric Company, Convair Astronautics Division of General Dynamics Corporation, and The Martin Company. These studies had begun in November 1960.

• Apollo A - . Nation: USA. Related Persons: Gilruth. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo A.

  Space Task Group Director Robert R. Gilruth informed Ames Research Center that current planning for Apollo 'A' called for an adapter between the Saturn second stage and the Apollo spacecraft to include, as an integral part, a section to be used as an orbiting laboratory. Preliminary in-house configuration designs indicated this laboratory would be a cylindrical section about 3.9 m in diameter and 2.4 m in height. Additional Details: here....

• Second draft of the Apollo spacecraft specification - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection. The second draft of a Statement of Work for the development of an advanced manned spacecraft was completed, incorporating results from NASA in-house and contractor feasibility studies..

• Fleming Committee Report: lunar mission could be accomplished within the decade - . Nation: USA. Related Persons: Seamans. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection, LM Mode Debate, LM Source Selection.

  The Fleming Committee, which had been appointed on May 2, submitted its report to NASA associate Administrator Robert C. Seamans, Jr., on the feasibility of a manned lunar landing program. The Committee concluded that the lunar mission could be accomplished within the decade. Chief pacing items were the first stage of the launch vehicle and the facilities for testing and launching the booster. It also concluded that information on solar flare radiation and lunar surface characteristics should be obtained as soon as possible, since these factors would influence spacecraft design. Special mention was made of the need for a strong management organization.

• Project Apollo feasibility studies assessed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  STG completed a detailed assessment of the results of the Project Apollo feasibility studies submitted by the three study contractors: the General Electric Company, Convair/Astronautics Division of the General Dynamics Corporation, and The Martin Company. (Their findings were reflected in the Statement of Work sent to prospective bidders on the spacecraft contract on July 28.)

• NASA-Industry Apollo Technical Conference - . Nation: USA. Related Persons: Gilruth. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, CSM Source Selection.

  1,000 persons from 300 potential Project Apollo contractors and government agencies attended the conference. STG pushed the conical CM shape, in defiance of Gilruth's preference for the competitive blunt body/lifting body designs. Scientists from NASA, the General Electric Company, The Martin Company, and General Dynamics/Astronautics presented the results of studies on Apollo requirements. Within the next four to six weeks NASA was expected to draw up the final details and specifications for the Apollo spacecraft.

• NASA invitation to bids for Apollo prime contract - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Original Specification, CSM Source Selection.

  NASA invited 12 companies to submit prime contractor proposals for the Apollo spacecraft by October 9: The Boeing Airplane Company, Chance Vought Corporation, Douglas Aircraft Company, General Dynamics/Convair, the General Electric Company, Goodyear Aircraft Corporation, Grumman Aircraft Engineering Corporation, Lockheed Aircraft Corporation, McDonnell Aircraft Corporation, The Martin Company, North American Aviation, Inc., and Republic Aviation Corporation. Additional Details: here....

• Source Evaluation Board to evaluate contractors' proposals for the Apollo spacecraft - . Nation: USA. Related Persons: Chamberlin, Faget. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  NASA Associate Administrator Robert C. Seamans, Jr., appointed members to the Source Evaluation Board to evaluate contractors' proposals for the Apollo spacecraft. Walter C. Williams of STG served as Chairman, and members included Robert O. Piland, Wesley L. Hjornevik, Maxime A. Faget, James A. Chamberlin, Charles W. Mathews, and Dave W. Lang, all of STG; George M. Low, Brooks C. Preacher, and James T. Koppenhaver (nonvoting member) from NASA Headquarters; and Oswald H. Lange from Marshall Space Flight Center. On November 2, Faget became the Chairman, Kenneth S. Kleinknecht was added as a member, and Williams was relieved from his assignment.

• Work statements for the Apollo guidance and navigation system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance, CSM Source Selection. The MIT Instrumentation Laboratory and NASA completed the work statements for the Laboratory's program on the Apollo guidance and navigation system and the request for quotation for industrial support was prepared..

• Polaris program experience studied for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance, CSM Source Selection.

  Ralph Ragan of the MIT Instrumentation Laboratory, former director of the Polaris guidance and navigation program, in cooperation with Milton B. Trageser of the Laboratory and with Robert O. Piland, Robert C. Seamans, Jr., and Robert G. Chilton, all of NASA, had completed a study of what had been done on the Polaris program in concept and design of a guidance and navigation system and the documentation necessary for putting such a system into production on an extremely tight schedule. Using this study, the group worked out a rough schedule for a similar program on Apollo.

• Additional Panels evaluate proposals for the Apollo spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection. STG appointed members to the Technical Subcommittee and to the Technical Assessment Panels for evaluation of industry proposals for the development of the Apollo spacecraft..

• First Apollo development contract - . Nation: USA. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, CSM Guidance, CSM Source Selection.

  NASA selected MIT's Instrumentation Laboratory to develop the guidance-navigation system for Project Apollo spacecraft. This first major Apollo contract was required since guidance-navigation system is basic to overall Apollo mission. The Instrumentation Laboratory of MIT, a nonprofit organization headed by C. Stark Draper, has been involved in a variety of guidance and navigation systems developments for 20 years. This first major Apollo contract had a long lead-time, was basic to the overall Apollo mission, and would be directed by STG.

• Apollo pre-proposal bidders' briefing - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, Apollo Lunar Landing, CSM Source Selection.

  STG held a pre-proposal briefing at Langley Field, Va., to answer bidders' questions pertaining to the Request for Proposal for the development of the Apollo spacecraft. 14 companies (Boeing, Vought, Douglas, GD, Goodyear, Grumman, Lockheed, Martin, McDonnell, Radio Corp, Republic, STL) attended. The winning bidder would receive contract for CSM (but not LM, if any) and integrate spacecraft with launch vehicle.

• Atmospheric requirement for the Apollo spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS, CSM Source Selection.

  STG requested that a program be undertaken by the U.S. Navy Air Crew Equipment Laboratory, Philadelphia, Penna., to validate the atmospheric composition requirement for the Apollo spacecraft. On November 7, the original experimental design was altered by the Manned Spacecraft Center (MSC). The new objectives were:

  • Establish the required preoxygenation time for a rapid decompression (80 seconds) from sea level to 35,000 feet.
  • Discover the time needed for equilibrium (partial denitrogenation) at the proposed cabin atmosphere for protection in case of rapid decompression to 35,000 feet.
  • Investigate the potential hazard associated with an early mission decompression - i.e., before the equilibrium time was reached, preceded by the determined preoxygenation period.
  • Conduct any additional tests suggested by the results of the foregoing experiments.

• STG Panels formed for evaluation of proposals for the development of the Apollo spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection. STG appointed members to the Business Subcommittee and to the Business Assessment Panels for evaluation of industry proposals for the development of the Apollo spacecraft..

• Progress review of the Apollo navigation and guidance system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance, CSM Source Selection.

  Representatives of STG and NASA Headquarters visited the Instrumentation Laboratory of MIT to discuss the contract awarded to the Laboratory on August 9 and progress in the design and development of the Apollo spacecraft navigation and guidance system. They mutually decided that a draft of the final contract should be completed for review at Instrumentation Laboratory by October 2 and the contract resolved by October 9. Revisions were to be made in the Statement of Work to define more clearly details of the contract. Milton B. Trageser of the Laboratory, in the first month's technical progress report, gave a brief description of the first approach to the navigation and guidance equipment and the arrangement of the equipment within the spacecraft. He also presented the phases of the lunar flight and the navigation and guidance functions or tasks to be performed. Other matters discussed were a space sextant and making visual observations of landmarks through cloud cover.

• Concepts of Apollo navigation equipment described - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance, CSM Source Selection.

  Richard H. Battin published MIT Instrumentation Laboratory Report R-341, "A Statistical Optimizing Navigation Procedure for Space Flight," describing the concepts by which Apollo navigation equipment could make accurate computations of position and velocity with an onboard computer of reasonable size.

• Apollo X - . Nation: USA. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo X.

  Emanuel Schnitzer of LaRC suggested a possible adaptation for existing Apollo hardware to create a space laboratory, which he termed an 'Apollo X' vehicle. Schnitzer's concept involved using a standard Apollo command and service module in conjunction with an inflatable spheroid structure and transfer tunnel to create a space laboratory with artificial gravity potential. Additional Details: here....

• Apollo spacecraft guidance and navigation progress - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS, CSM Source Selection.

  Representatives of STG visited the Instrumentation Laboratory of MIT for the second monthly progress report meeting on the Apollo spacecraft guidance and navigation contract. A number of technical topics were presented by Laboratory speakers: space sextant visibility and geometry problems, gear train analysis, vacuum environmental approach, midcourse guidance theory, inertial measurement unit, and gyro. The organization of the Apollo effort at the Laboratory was also discussed. A preliminary estimate of the cost for both Laboratory and industrial support for the Apollo navigation and guidance system was presented: $158.4 million through Fiscal Year 1966.

• Bids received for Apollo prime contractor - . Nation: USA. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, CSM Source Selection. Five Bidding Teams: GD/Avco; GE/Douglas/Grumman/STL; McDonnell/Lockheed/Hughes/Vought; Martin/North American.

• Presentations by industrial teams on the Apollo spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Source Selection.

  Officials of STG heard oral reports from representatives of five industrial teams bidding on the contract for the Apollo spacecraft: General Dynamics/Astronautics in conjunction with the Avco Corporation; General Electric Company, Missile and Space Vehicle Department, in conjunction with Douglas Aircraft Company, Grumman Aircraft Engineering Corporation, and Space Technology Laboratories, Inc.; McDonnell Aircraft Corporation in conjunction with Lockheed Aircraft Corporation, Hughes Aircraft Company, and Chance Vought Corporation of Ling-Temco-Vought, Inc.; The Martin Company; and North American Aviation, Inc. Additional Details: here....

• New information on the Apollo spacecraft roll inertia, pitch and yaw inertia, and attitude jets - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance, CSM Source Selection. Robert G. Chilton of STG gave the MIT Instrumentation Laboratory new information based on NASA in- house studies on the Apollo spacecraft roll inertia, pitch and yaw inertia, and attitude jets.

  David G. Hoag, MIT, personal notes, October 1961..

• An Apollo Egress Working Group was formed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery, CSM Source Selection.

  An Apollo Egress Working Group, consisting of personnel from Marshall Space Flight Center, Launch Operations Directorate, and Atlantic Missile Range, was formed on November 2. Meetings on that date and on November 6 resulted in publication of a seven-page document, "Apollo Egress Criteria." The Group established ground rules, operations and control procedures criteria, and space vehicle design criteria and provided requirements for implementation of emergency egress system.

• MIT contract for the Apollo navigation and guidance system discussed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance, CSM Source Selection.

  Representatives of MSC and NASA Headquarters visited the MIT Instrumentation Laboratory to discuss clauses in the contract for the Apollo navigation and guidance system, technical questions proposed by MSC, and work in progress. Topics discussed included the trajectories for the SA-7 and SA-8 flights and the estimated propellant requirements for guidance attitude maneuvers and velocity changes for the lunar landing mission. Presentations were made on the following subjects by members of the Laboratory staff: the spacecraft gyro, Apollo guidance computer logic design, computer displays and interfaces, guidance computer programming, horizon sensor experiments, and reentry guidance.

• Bid Evaluation for Prime Contractor Completed - . Nation: USA. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, CSM Source Selection. Bid ratings: Martin 6.9; GD 6.6; North American 6.6; GE 6.4; McDonnell 6.4.

• Apollo spacecraft Statement of Work expanded - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Original Specification, CSM Source Selection. The original Apollo spacecraft Statement of Work of July 28 had been substantially expanded, including a single-engine service module propulsion system using Earth-storable, hypergolic propellants.. Additional Details: here....

• North American awarded Apollo prime contract - . Nation: USA. Related Persons: Webb. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft: Apollo CSM, Apollo Lunar Landing, CSM Source Selection.

  Despite an announcement at Martin on 27 November that they had won the Apollo program, the decision was reversed at the highest levels of the US government. NASA announced instead that the Space and Information Systems Division of North American Aviation, Inc., had been selected to design and build the Apollo spacecraft. The official line: 'the decision by NASA Administrator James E. Webb followed a comprehensive evaluation of five industry proposals by nearly 200 scientists and engineers representing both NASA and DOD. Webb had received the Source Evaluation Board findings on November 24. Although technical evaluations were very close, NAA had been selected on the basis of experience, technical competence, and cost'. NAA would be responsible for the design and development of the command module and service module. NASA expected that a separate contract for the lunar landing system would be awarded within the next six months. The MIT Instrumentation Laboratory had previously been assigned the development of the Apollo spacecraft guidance and navigation system. Both the NAA and MIT contracts would be under the direction of MSC.

• Emergency switchover from Saturn to Apollo guidance as backup discussed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance. On a visit to Marshall Space Flight Center by MIT Instrumentation Laboratory representatives, the possibility was discussed of emergency switchover from Saturn to Apollo guidance systems as backup for launch vehicle guidance..

• Project Apollo Statement of Work completed - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  The Project Apollo Statement of Work for development of the Apollo spacecraft was completed. A draft letter based on this Statement of Work was presented to NAA for review. A prenegotiation conference on the development of the Apollo spacecraft was held at Langley Field, Va.

• NASA negotiations with NAA on the Apollo spacecraft contract were held at Williamsburg, Va - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES.

  NASA negotiations with NAA on the Apollo spacecraft contract were held at Williamsburg, Va. Nine Technical Panels met on December 11 and 12 to review Part 3, Technical Approach, of the Statement of Work. These Panels reported their recommended changes and unresolved questions to the Technical Subcommittee for action. Later in the negotiations, NASA and NAA representatives agreed on changes intended to clarify the original Statement of Work. Among these was the addition of the boilerplate program. Two distinct types of boilerplates were to be fabricated: those of a simple cold-rolled steel construction for drop impact tests and the more complex models to be used with the Little Joe II and Saturn launch vehicles. The Little Joe II, originally conceived in June 1961, was a solid-fuel rocket booster which would be used to man-rate the launch escape system for the command module.

  In addition, the Apollo Project Office, which had been part of the MSC Flight Systems Division, would now report directly to the MSC Director and would be responsible for planning and directing all activities associated with the completion of the Apollo spacecraft project. Primary functions to be performed by the Office would include:

  • Monitor the work of the Apollo Principal Contractor NAA and Associate Contractors.
  • Resolve technical problems arising between the Principal Contractor and Associate Contractors which were not directly resolved between the parties involved.
  • Maintain close liaison with all Apollo contractors to keep fully and currently informed on the status of contract work, potential schedule delays, or technical problems which might impede progress.
  (On January 15, 1962, the Apollo Spacecraft Project Office was established at MSC.)

  Letter contract No. NAS 9-150, authorizing work on the Apollo development program to begin on January 1, 1962, was signed by NASA and NAA on December 21. Under this contract, NAA was assigned the design and development of the command and service modules, the spacecraft adapter, associated ground support equipment, and spacecraft integration. Formal signing of the contract followed on December 31.

• First design-study Apollo space sextant produced - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  Fred T. Pearce, Jr., of MSC visited the MIT Instrumentation Laboratory to discuss the first design-study space sextant produced at the Laboratory, The instrument was intended to be used with the guidance computer. The working mockup was demonstrated and the problem of the effect of the vehicle motion on the sextant was discussed.

• Four major subcontractors for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute.

  NAA's Space and Information Systems Division selected four companies as subcontractors to design and build four of the major Apollo spacecraft systems. The Collins Radio Company, Cedar Rapids, Iowa, received the telecommunications systems contract, worth more than $40 million; Minneapolis-Honeywell Regulator Company, Minneapolis, Minn., received the stabilization and control systems contract, $30 million; AiResearch Manufacturing Company, division of The Garrett Corporation, Los Angeles, Calif., was awarded the environmental control system contract, $10 million; and Radioplane Division of Northrop Corporation, Van Nuys, Calif., was selected for the parachute landing system contract, worth more than $1 million. The total cost for the initial phase of the NAA contract was expected to exceed $400 million.

• Requests for Quotation for Apollo guidance and navigation system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  The Requests for Quotation on production contracts for major components of the Apollo spacecraft guidance and navigation system, comprising seven separate items, were released to industry by the MIT Instrumentation Laboratory. (The Source Evaluation Board, appointed on January 31, began its work during the week of March 5 and contractors were selected on May 8.)

• Apollo Spacecraft Project Office established - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  The Apollo Spacecraft Project Office (ASPO) was established at MSC. Charles W. Frick was selected as Manager of the new Office, to assume his duties in February. Frick had been Chief of Technical Staff for General Dynamics Convair. Robert O. Piland was appointed Deputy Manager of ASPO and would serve as Acting Manager until Frick's arrival. ASPO would be responsible for the technical direction of NAA and other industrial contractors assigned to work on the Apollo spacecraft. Additional Details: here....

• First Apollo engineering order issued - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. The first Apollo engineering order was issued to fabricate mockups of the Apollo command and service modules..

• Preliminary layouts of the Apollo command module - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Hatch.

  NAA engineers began preliminary layouts to define the elements of the command module (CM) configuration. Additional requirements and limitations imposed on the CM included reduction in diameter, paraglider compatibility, 250 pounds of radiation protection water, redundant propellant tankage for the attitude control system, and an increase in system weight and volume. Additional Details: here....

• Apollo command module heatshield requirements established for several design trajectories - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  Command module heatshield requirements, including heating versus time curves, were established by NAA for several design trajectories. A computer program method of analyzing the charring ablation process had been developed. By this means, it was possible to calculate the mass loss, surface char layer temperature, amount of heat conducted through the uncharred ablation material and insulation into the cabin, and temperature profile through the ablator and insulation layers. In February, NAA determined that a new and more refined computer program would be needed.

• Storable liquid propellant selected for Apollo service module - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM SPS.

  The solid propellant called for in the original NAA proposal on the service module propulsion system was replaced by a storable, hypergolic propellant. Multitank configurations under study appeared to present offloading capabilities for alternative missions.

• Single-engine design for the Apollo service module - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM SPS.

  On the basis of a study by NAA, a single-engine configuration was chosen as the optimum approach for the service module propulsion subsystem. The results of the study were presented to MSC representatives and NAA was authorized to issue a work statement to begin procurement of an engine for this configuration. Agreement was also reached at this meeting on a vacuum thrust level of 20,000 pounds for the engine. This would maintain a thrust-to-weight ratio of 0.4 and allow a considerable increase in the lunar liftoff weight of the spacecraft.

• General Electric selected for Apollo support - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  NASA announced that the General Electric Company had been selected for a major supporting role in the Apollo project, to provide integration analysis of the total space vehicle (including booster-spacecraft interface), ensure reliability of the entire space vehicle, and develop and operate a checkout system.

• Contract for Apollo launch escape system rocket - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES.

  A contract for the escape rocket of the Apollo spacecraft launch escape system was awarded to the Lockheed Propulsion Company by NAA. The initial requirements were for a 200,000-pound-thrust solid- propellant rocket motor with an active thrust-vector-control subsystem. Additional Details: here....

• NASA announced Project Fire - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: FIRE.

  NASA announced Project Fire, a high-speed reentry heat research program to obtain data on materials, heating rates, and radio signal attenuation on spacecraft reentering the atmosphere at speeds of about 24,500 miles per hour. Information from the program would support technology for manned and unmanned reentry from lunar missions. Under the management of the Langley Research Center, Project Fire would use Atlas D boosters and the reentry package would be powered by an Antares solid-fuel motor (third stage of the Scout).

• Apollo command module couch redesign - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute.

  The command module crew couch was repositioned and redesigned because of numerous problems. In the new design, an adjustable hand controller, similar to that used on the X-15, would be attached to an adjustable arm rest. The head rest could be regulated for an approximate four-inch movement, while the side head support was limited in movement for couch-module clearance. The adjustable leg support included a foot controller which could be folded up.

  The center couch, including the crewman parachute and survival kit, could be folded out to a sleep position and stowed under either remaining couch. Allowance was made for the crewman to turn over.

  Principal problems remaining were the difficulty of removing the center couch and providing the clearances needed for the couch positions specified for various phases of the lunar mission.

• Marquardt to build the reaction control rocket engines for the Apollo spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS. The Marquardt Corporation was selected by NAA's Space and Information Systems Division to design and build the reaction control rocket engines for the Apollo spacecraft. The contract was signed during April..

• Aerojet-General named for the Apollo service module propulsion system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM SPS. The Aerojet-General Corporation was named by NAA as a subcontractor for the Apollo service module propulsion system..

• The staffing for the MSC Apollo Spacecraft Project Office was announced - . Nation: USA. Related Persons: Johnson, Caldwell. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery.

  The organizational elements and staffing for the MSC Apollo Spacecraft Project Office was announced:

  Office of Project Manager

  Charles W. Frick, Project Manager

  Robert O. Piland, Deputy Project Manager

  Command and Service Module

  Caldwell C. Johnson, Chief

  William F. Rector, Special Assistant

  Calvin H. Perrine, Flight Technology

  Lee N. McMillion, Crew Systems

  David L. Winterhalter, Sr., Power Systems

  Wallace D. Graves, Mechanical Systems

  Milton C. Kingsley, Electrical Systems

  (Vacant), Ground Support Equipment

  Lunar Landing Module

  Robert O. Piland, Acting Chief

  Guidance and Control Development

  David W. Gilbert, Chief

  Jack Barnard, Apollo Office at MIT

  Systems Integration

  Paul F. Weyers, Chief

  (Vacant), Reliability and Quality Control

  Emory F. Harris, Operations Requirements

  Robert P. Smith, Launch Vehicle Integration

  Owen G. Morris, Mission Engineering

  Marion R. Franklin, Ground Operational Support Systems

  Apollo Office at NAA

  Herbert R. Ash, Acting Manager

  Alan B. Kehlet, Engineering

  Alan B. Kehlet, Acting Manager, Quality Control and Engineering

  Herbert R. Ash, Acting Manager, Business Administration

  Planning and Resources

  Thomas F. Baker, Chief

• Contract for the Apollo spacecraft fuel cell to Pratt & Whitney - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Fuel Cell. NAA awarded a development contract for the Apollo spacecraft fuel cell to Pratt & Whitney Aircraft Division of United Aircraft Corporation..

• Apollo program to be given DX priority - . Nation: USA. Related Persons: Johnson, Lyndon, Kennedy, Webb. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  James E. Webb, NASA Administrator, recommended to President John F. Kennedy that the Apollo program be given DX priority (highest priority in the procurement of critical materials). He also sent a memorandum to Vice President Lyndon B. Johnson, Chairman of the National Aeronautics and Space Council, requesting that the Council consider advising the President to add the Apollo program to the DX priority list.

• First monthly meeting of the Apollo design and review team to survey NAA's progress - . Nation: USA. Related Persons: Faget, Kraft, Maynard. Program: Apollo. Spacecraft: Apollo CSM, CSM Fuel Cell, CSM Heat Shield.

  Charles W. Frick, Manager of the MSC Apollo Spacecraft Project Office, together with Maxime A. Faget, Charles W. Mathews, Christopher C. Kraft, Jr., John B. Lee, Owen E. Maynard, and Alan B. Kehlet of MSC and George M. Low of the NASA Office of Manned Space Flight, visited NAA at Downey, Calif. This was the first monthly meeting of the Apollo design and review team to survey NAA's progress in various areas, including the Apollo spacecraft heatshield, fuel cells, and service module.

• Avco selected for ablative material for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield. The Avco Corporation was selected by NAA to design and install the ablative material on the Apollo spacecraft outer surface..

• Wind tunnel tests on two configurations of Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield. Wind tunnel tests were completed at the Jet Propulsion Laboratory and at Langley Research Center on two early configurations of Apollo spacecraft models..

• Republic to build two experimental FIRE spacecraft - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: FIRE.

  NASA announced that a $5 million contract would be awarded to Republic Aviation Corporation for the construction of two experimental reentry spacecraft. Republic was selected from eight companies that submitted bids on March 12. The contract was part of Project Fire, to develop a spacecraft capable of withstanding reentry into the earth's atmosphere from a lunar mission. Plans called for the spacecraft to be tested during the second half of 1963.

• Apollo guidance and navigation system defined - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  The Apollo guidance and navigation system was defined in more detail as more information from NASA MIT studies was received on new requirements for the system. As a result, the scope of the component development tasks given to all the guidance and navigation subcontractors was substantially increased.

• Design criteria of the Apollo service module for the lunar landing maneuver - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, Apollo Lunar Landing. NAA was directed by the MSC Apollo Spacecraft Project Office to begin a study to define the configuration and design criteria of the service module which would make the lunar landing maneuver and touchdown..

• Meeting at NASA Headquarters reviews the lunar orbit rendezvous (LOR) technique for Project Apollo - . Nation: USA. Related Persons: Geissler, Horn, Maynard, Shea. Program: Apollo. Spacecraft: Apollo CSM, Apollo Lunar Landing, CSM LES, CSM Recovery, CSM SPS, CSM Television.

  A meeting to review the lunar orbit rendezvous (LOR) technique as a possible mission mode for Project Apollo was held at NASA Headquarters. Representatives from various NASA offices attended: Joseph F. Shea, Eldon W. Hall, William A. Lee, Douglas R. Lord, James E. O'Neill, James Turnock, Richard J. Hayes, Richard C. Henry, and Melvyn Savage of NASA Headquarters; Friedrich O. Vonbun of Goddard Space Flight Center (GSFC); Harris M. Schurmeier of Jet Propulsion Laboratory; Arthur V. Zimmeman of Lewis Research Center; Jack Funk, Charles W. Mathews, Owen E. Maynard, and William F. Rector of MSC; Paul J. DeFries, Ernst D. Geissler, and Helmut J. Horn of Marshall Space Flight Center (MSFC); Clinton E. Brown, John C. Houbolt, and William H. Michael, Jr., of Langley Research Center; and Merrill H. Mead of Ames Research Center. Each phase of the LOR mission was discussed separately.

  The launch vehicle required was a single Saturn C-5, consisting of the S-IC, S-II, and S-IVB stages. To provide a maximum launch window, a low earth parking orbit was recommended. For greater reliability, the two-stage-to-orbit technique was recommended rather than requiring reignition of the S-IVB to escape from parking orbit.

  The current concepts of the Apollo command and service modules would not be altered. The lunar excursion vehicle (LEV), under intensive study in 1961, would be aft of the service module and in front of the S-IVB stage. For crew safety, an escape tower would be used during launch. Access to the LEV would be provided while the entire vehicle was on the launch pad.

  Both Apollo and Saturn guidance and control systems would be operating during the launch phase. The Saturn guidance and control system in the S-IVB would be "primary" for injection into the earth parking orbit and from earth orbit to escape. Provisions for takeover of the Saturn guidance and control system should be provided in the command module. Ground tracking was necessary during launch and establishment of the parking orbit, MSFC and GSFC would study the altitude and type of low earth orbit.

  The LEV would be moved in front of the command module "early" in the translunar trajectory. After the S-IVB was staged off the spacecraft following injection into the translunar trajectory, the service module would be used for midcourse corrections. Current plans were for five such corrections. If possible, a symmetric configuration along the vertical center line of the vehicle would be considered for the LEV. Ingress to the LEV from the command module should be possible during the translunar phase. The LEV would have a pressurized cabin capability during the translunar phase. A "hard dock" mechanism was considered, possibly using the support structure needed for the launch escape tower. The mechanism for relocation of the LEV to the top of the command module required further study. Two possibilities were discussed: mechanical linkage and rotating the command module by use of the attitude control system. The S-IVB could be used to stabilize the LEV during this maneuver.

  The service module propulsion would be used to decelerate the spacecraft into a lunar orbit. Selection of the altitude and type of lunar orbit needed more study, although a 100-nautical-mile orbit seemed desirable for abort considerations.

  The LEV would have a "point" landing (�� mile) capability. The landing site, selected before liftoff, would previously have been examined by unmanned instrumented spacecraft. It was agreed that the LEV would have redundant guidance and control capability for each phase of the lunar maneuvers. Two types of LEV guidance and control systems were recommended for further analysis. These were an automatic system employing an inertial platform plus radio aids and a manually controlled system which could be used if the automatic system failed or as a primary system.

  The service module would provide the prime propulsion for establishing the entire spacecraft in lunar orbit and for escape from the lunar orbit to earth trajectory. The LEV propulsion system was discussed and the general consensus was that this area would require further study. It was agreed that the propulsion system should have a hover capability near the lunar surface but that this requirement also needed more study.

  It was recommended that two men be in the LEV, which would descend to the lunar surface, and that both men should be able to leave the LEV at the same time. It was agreed that the LEV should have a pressurized cabin which would have the capability for one week's operation, even though a normal LOR mission would be 24 hours. The question of lunar stay time was discussed and it was agreed that Langley should continue to analyze the situation. Requirements for sterilization procedures were discussed and referred for further study. The time for lunar landing was not resolved.

  In the discussion of rendezvous requirements, it was agreed that two systems be studied, one automatic and one providing for a degree of manual capability. A line of sight between the LEV and the orbiting spacecraft should exist before lunar takeoff. A question about hard-docking or soft-docking technique brought up the possibility of keeping the LEV attached to the spacecraft during the transearth phase. This procedure would provide some command module subsystem redundancy.

  Direct link communications from earth to the LEV and from earth to the spacecraft, except when it was in the shadow of the moon, was recommended. Voice communications should be provided from the earth to the lunar surface and the possibility of television coverage would be considered.

  A number of problems associated with the proposed mission plan were outlined for NASA Center investigation. Work on most of the problems was already under way and the needed information was expected to be compiled in about one month.

  (This meeting, like the one held February 13-15, was part of a continuing effort to select the lunar mission mode).

• Mockup of the Apollo command module made public - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. A mockup of the Apollo command module, built by the Space and Information Systems Division of NAA, was made public for the first time during a visit to NAA by news media representatives..

• Thiokol selected for Apollo launch escape tower jettison motors - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES. The Thiokol Chemical Corporation was selected by NAA to build the solid-fuel rocket motor to be used to jettison the Apollo launch escape tower following a launch abort or during a normal mission..

• Request for proposal for the Little Joe II launch vehicle - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  The request for a proposal on the Little Joe II test launch vehicle was submitted to bidders by a letter from MSC, together with a Work Statement. Five launches, which were to test boilerplate models of the Apollo spacecraft command module in abort situations, were called for: three in 1963 and two in 1964. Additional Details: here....

• DX (highest) priority for the Apollo program - . Nation: USA. Related Persons: Kennedy. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. President John F, Kennedy designated the Apollo program including essential spacecraft, launch vehicles, and facilities as being in the highest national priority category (DX) for research and development and for achieving operational capability..

• Monthly NAA-NASA Apollo spacecraft design review - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  Discussions at the monthly NAA-NASA Apollo spacecraft design review included:

  • Results of an NAA study on environmental control system (ECS) heating capabilities for lunar night operations were presented. The study showed that the system could not provide enough heating and that the integration of ECS and the fuel cell coolant system was the most promising source for supplemental heating.
  • The launch escape system configuration was approved. It embodied a 120inch tower, symmetrical nose cone, jettison motor located forward of the launch escape motor, and an aerodynamic skirt covering the escape motor nozzles. This configuration change in the escape rocket nozzle cant angle was intended to prevent impingement of hot gases on the command module.
  • MSC senior personnel directed NAA to study the technical penalties and scheduling effects of spacecraft design capabilities with direct lunar landing and lunar rendezvous techniques.

• Three major changes made by NAA in the Apollo space-suit circuit - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Structural.

  Three major changes were made by NAA in the Apollo space-suit circuit:

  1. The demand oxygen regulator was moved downstream of the crew to prevent a sudden drop of pressure when a crewman opened his face plate.
  2. The suit manifold would now have a pressure-controlled bypass to prevent variable flow to other crew members if one crewman increased or decreased oxygen flow. The manifold would also include a venturi in each suit-inlet connection to prevent a loss of oxygen flow to other crew members if the suit of one crewman should rupture. In this situation, the venturi would prevent the damaged suit flow out from exceeding the maximum flow of demand regulators.
  3. The circuit water evaporator and coolant loop heat exchanger of the suit were integrated into one by fluid exchange to make it smaller. A coolant-temperature control was also provided for sunlight operation on the moon.
  In addition, a suit inlet-outlet was added to the command module sleeping quarters, and the cabin fan was shifted so that it would operate as an intake fan during the post-landing phase.

• Shock attenuation in the Apollo command module - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  NAA developed a concept for shock attenuation along the command module Y-Y axis by the use of aluminum honeycomb material. Cylinders mounted on the outboard edge of the left and right couches would extend mechanically to bear against the side compartment walls.

• Apollo inflight nuclear radiation instrumentation - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  NAA determined that preliminary inflight nuclear radiation instrumentation would consist of an onboard system to detect solar x-ray or ultraviolet radiation and a ground visual system for telemetering solar flare warning signals to the command module. The crew would have eight to ten minutes warning to take protective action before the arrival of solar flare proton radiation.

• Configuration of the Apollo command module forward compartment changed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS. The basic design configuration of the command module forward compartment was changed by the relocation of two attitude control engines from the lower to the upper compartment area, where less heat flux would be experienced during reentry..

• Apollo service module propulsion engine contract to Aerojet - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM SPS. The contract for the Apollo service module propulsion engine was awarded by NAA to Aerojet-General Corporation. The estimated cost of the contract was $12 million. NAA had given Aerojet-General authority April 9 to begin work..

• Changes in the Apollo environmental control system (ECS) - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Fuel Cell, CSM Recovery.

  NAA studies resulted in significant changes in the command module environmental control system (ECS).

  1. Among modifications in the ECS schematic were included:
     1. Reduction in the cooling water capacity
     2. Combining into one command module tank the potable water and cooling water needed during boost
     3. Elimination of the water blanket for radiation protection.
  2. More water would be generated by the fuel cells than necessary and could be dumped to decrease lunar landing and lunar takeoff weight.
  3. Airlock valving requirements would permit two or more crewmen to perform extravehicular operation simultaneously. Area control of the space radiator to prevent coolant freezing was specified.
  4. A new concept to integrate heat rejection from the spacecraft power system and the ECS into one space radiator subsystem was developed. This subsystem would provide full versatility for both lunar night and lunar day conditions and would decrease weight and complexity.
  5. Because of the elimination of the lunar supplemental refrigeration system and deployable radiators, the water-glycol coolant system was modified:
     1. Removal from the service module of the coolant loop regenerative heat exchanger
     2. Replacement by a liquid valving arrangement of the gas-leak check provision at the radiator panels
     3. Changeover to a completely cascaded system involving the suit-circuit heat exchanger, cabin heat exchanger, and electronic component coldplate.
  In addition, a small, regenerative heat exchanger was added in the command module to preheat the water-glycol. A separate coolant branch to the inertial measurement unit section of the electronic system provided for the more critical cooling task required in that area.

• Purchase request for Apollo wind tunnel support services from the Air Force - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  A purchase request was being prepared by NASA for wind tunnel support services from the Air Force's Arnold Engineering Development Center in the amount of approximately $222,000. These wind tunnel tests were to provide design parameter data on static stability, dynamic stability, pressure stability, and heat transfer for the Apollo program. The funds were to cover tests during June and July 1962. Approximately $632,000 would be required in Fiscal Year 1963 to fund the tests scheduled to December 1962.

• Source Evaluation Board for selecting Apollo navigation and guidance completed its evaluation - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  The Source Evaluation Board for selecting Apollo navigation and guidance components subcontractors completed its evaluation of bids and technical proposals and submitted its findings to NASA Headquarters. Preliminary presentation of the Board's findings had been made to NASA Administrator James E. Webb on April 5.

• Comprehensive test plan for verifying the overall integrity of the heatshield - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  At the monthly Apollo spacecraft design review meeting at NAA, MSC representatives recommended that NAA and Avco Corporation prepare a comprehensive test plan for verifying the overall integrity of the heatshield including flight tests deemed necessary, without regard for anticipated hunch vehicle availability.

• NAA's Apollo spacecraft letter contract increased - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  MSC processed a purchase request to increase NAA's spacecraft letter contract from $32 million to $55 million to cover NAA's costs to June 30, 1962. (Pending the execution of a definitive contract (signed August 14, 1963), actions of this type were necessary).

• Three contractors for the Apollo guidance and navigation system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  NASA announced the selection of three companies for the negotiation of production contracts for major components of the Apollo spacecraft guidance and navigation system under development by the MIT Instrumentation Laboratory. The largest of the contracts, for $16 million, would be negotiated with AC Spark Plug Division of General Motor Corporation for fabrication of the inertial, gyroscope-stabilized platform of the Apollo spacecraft; for development and construction of ground support and checkout equipment; and for assembling and testing all parts of the system. The second contract, for $2 million, would be negotiated with the Raytheon Company to manufacture the digital computer aboard the spacecraft. Under the third contract, for about $2 million, Kollsman Instrument Corporation would build the optical subsystems, including a space sextant, sunfinders, and navigation display equipment.

• Urine management system recommended - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  Two NAA analyses showed that the urine management system would prevent a rise in the command module humidity load and atmospheric contamination and that freeze-up of the line used for daily evacuation of urine to the vacuum of space could be prevented by proper orificing of the line.

• Apollo command module reaction control system selected - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS.

  The command module reaction control system (RCS) selected by NAA was a dual system without interconnections. Either would be sufficient for the entire mission.

  For the service module RCS, a quadruple arrangement was chosen which was basically similar to the command module RCS except that squib valves and burst discs were eliminated.

• Study of integrating the Apollo fuel cell and environmental control heat rejection systems - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Fuel Cell.

  NAA evaluated the possibility of integrating the fuel cell and environmental control system heat rejection into one system. The integrated system proved to be unsatisfactory, being 300 pounds heavier and considerably more complex than the two separate systems. A preliminary design of separate fuel cell radiators, possibly located on the service module, was started by NAA.

• Apollo command module toxic materials - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  NAA began compiling a list of command module materials to be classified selectively for potentially toxic properties. These materials would be investigated to determine location (related to possible venting of gases), fire resistance, exposure to excessive temperatures, gases resulting from thermal decomposition, and toxicity of gases released under normal and material-failure conditions. Although a complete examination of every material was not feasible, materials could be grouped according to chemical constituency and quantity of gases released.

• Layouts of Apollo command module windows - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery. Layouts of three command module observation window configurations were made by NAA. A study disclosed that sufficient direct vision for lunar landing was not feasible and that windows could not be uncovered during reentry..

• First reliability prediction for Apollo - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  The first reliability prediction study for the Apollo spacecraft was completed by NAA. Assuming all systems as series elements and excluding consideration of alternative modes, redundancies, or inflight maintenance provisions, the study gave a reliability estimate of 0.731. This analysis provided a basis from which means of improving reliability would be evaluated and formulated.

• Preliminary requirement for spacecraft docking - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Docking.

  NAA completed a preliminary requirement outline for spacecraft docking. The outline specified that the two spacecraft be navigated to within a few feet of each other and held to a relative velocity of less than six inches per second and that they be steered to within a few inches of axial alignment and parallelism. The crewman in the airlock was assumed to be adequately protected against radiation and meteoric bombardment and to be able to grasp the docking spacecraft and maneuver it to the sealing faces for final clamp.

• Apollo emergency flight mode for lunar mission reentry - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  A feasibility study was completed by NAA on the ballistic (zero-lift) maneuver as a possible emergency flight mode for lunar mission reentry. Based upon single-pass and 12 g maximum load-factor criteria, the guidance corridor would be nine nautical miles. When atmospheric density deviations were considered (+/- 50 percent from standard), the allowable corridor would be reduced to four nautical miles. Touchdown dispersions within the defined corridor exceeded 2500 nautical miles.

• Apollo spacecraft crew hatch concept - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Hatch.

  NAA decided to retain the inward-opening pull-down concept for the spacecraft crew hatch, which would use plain through bolts for lower sill attachment and a manual jack-screw device to supply the force necessary to seat and unseat the hatch.

  Concurrently, a number of NAA latching concepts were in preparation for presentation to NASA, including that of an outward-opening, quick- opening crew door without an outer emergency panel. This design, however, had weight and complexity disadvantages, as well as requiring explosive charges.

• Telescope requirements for the Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute.

  Telescope requirements for the spacecraft were modified after two study programs had been completed by NAA.

  A study on the direct vision requirement for lunar landing showed that, to have a simultaneous direct view of the lunar landing point and the landing feet without changing the spacecraft configuration, a periscope with a large field of view integrated with a side window would be needed. A similar requirement on the general-purpose telescope could thus be eliminated, reducing the complexity of the telescope design.

  Another study showed that, with an additional weight penalty of from five to ten pounds, an optical drift indicator for use after parachute deployment could easily be incorporated into the general-purpose telescope.

• NAA studies on Apollo prototype crew couch - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit. NAA studies on the prototype crew couch included one on the use of the center couch for supporting a crewman at the astrosextant during lunar approach and another on the displacement of outboard couches for access to equipment areas..

• von Braun recommends lunar orbit rendezvous mode for Apollo - . Nation: USA. Related Persons: von Braun. Program: Apollo. Spacecraft: Apollo CSM, Apollo Lunar Landing, CSM Recovery, CSM SPS.

  Wernher von Braun, Director, Marshall Space Flight Center, recommended to the NASA Office of Manned Space Flight that the lunar orbit rendezvous mode be adopted for the lunar landing mission. He also recommended the development of an unmanned, fully automatic, one-way Saturn C-5 logistics vehicle in support of the lunar expedition; the acceleration of the Saturn C-1B program; the development of high-energy propulsion systems as a backup for the service module and possibly the lunar excursion module; and further development of the F-1 and J-2 engines to increase thrust or specific impulse.

• NAA directed to design an earth landing system for an Apollo CM passive touchdown mode - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield, CSM LES, CSM Recovery.

  NAA was directed by the Apollo Spacecraft Project Office at the monthly design review meeting to design an earth landing system for a passive touchdown mode to include the command module cant angle limited to about five degrees and favoring offset center of gravity, no roll orientation control, no deployable heatshield, and depressurization of the reaction control system propellant prior to impact. At the same meeting, NAA was requested to use a single "kicker" rocket and a passive thrust-vector-control system for the spacecraft launch escape system.

• VVS Conference: Military Use of Space - the Short-Term Perspective - . Nation: Russia. Related Persons: Malinovskiy, Rudenko, Vershinin. Spacecraft: Apollo CSM, Soyuz A, Soyuz B, Soyuz V.

  The projection is made that the US will surpass the USSR in space in 1963-1964. Kennedy's 1961 speech announcing the Apollo project to land on the moon was passed to Vershinin for comment, but no reply was ever received. Rudenko, Vershinin, and especially Malinovskiy see no role for piloted space flight, let alone flights to the moon. America, with its superior electronics capability, is still proceeding with development of manned spacecraft that require the active piloting of the astronaut. Why then, Kamanin fumes, is the USSR trying to develop completely automated manned spacecraft? Military space is being run in the USSR by men who know nothing of it, he notes. Rudenko is ill, and not even at the conference.

• Apollo propulsion to be tested at White Sands - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM SPS. NASA announced that the Apollo service module propulsion system would be tested at a new facility at White Sands Missile Range, N. Mex..

• 100 percent oxygen atmosphere for Apollo would save 30 pounds - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS. Results of a preliminary investigation by NAA showed that a 100 percent oxygen atmosphere for the command module would save about 30 pounds in weight and reduce control complexity..

• Location of the onboard space sextant in the Apollo command module changed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  As the result of considerable joint engineering effort and discussion by NAA and MIT Instrumentation Laboratory, the location of the onboard space sextant in the command module was changed from the main instrument panel to the wall of the lower equipment bay. The instrument would penetrate the hull on the hot side during reentry and the navigator would have to leave his couch to make navigation sightings and to align the inertial measurement unit.

• Microcircuits to be used on the Apollo computer - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance. NASA and MIT agreed that the Instrumentation Laboratory would use the microcircuit for the prototype Apollo onboard computer. The Fairchild Controls Corporation microcircuit was the only one available in the United States..

• Results of the study on lunar mission mode selection - . Nation: USA. Related Persons: Shea. Program: Apollo. Spacecraft: Apollo CSM, LM Mode Debate, LM Source Selection.

  Joseph F. Shea, NASA Deputy Director of Manned Space Flight (Systems), presented to the Manned Space Flight Management Council the results of the study on lunar mission mode selection. The study included work by personnel in Shea's office, MSC, and Marshall Space Flight Center. The criteria used in evaluating the direct ascent technique, earth orbit rendezvous connecting and fueling modes, and lunar orbit rendezvous were: the mission itself, weight margins, guidance accuracy, communications and tracking requirements, reliability (abort problems), development complexity, schedules, costs, flexibility, growth potential, and military implications.

• Study of repair of J-2 engine in space - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  Five NASA scientists, dressed in pressure suits, completed an exploratory study at Rocketdyne Division of the feasibility of repairing, replacing, maintaining, and adjusting components of the J-2 rocket while in space. The scientific team also investigated the design of special maintenance tools and the effectiveness of different pressure suits in performing maintenance work in space.

• Apollo employment at NAA reached 14,119 - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. Employment at NAA's Space and Information Systems Division reached 14,119, an increase of 7,000 in seven months..

• Apollo atmosphere to be pure oxygen - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  At the monthly Apollo spacecraft design review meeting with NAA, MSC officials directed NAA to design the spacecraft atmospheric system for 5 psia pure oxygen. From an engineering standpoint, the single-gas atmosphere offered advantages in minimizing weight and leakage, in system simplicity and reliability, and in the extravehicular suit interface. Additional Details: here....

• Beech selected build the Apollo fuel cell vessels - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Fuel Cell. Beech Aircraft Corporation was selected by NASA to build the spherical pressure vessels that would be used to store in the supercritical state the hydrogen-oxygen reactants for the spacecraft fuel cell power supply..

• Modified method of cooling Apollo selected - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  A modified method of cooling crew and equipment before launch and during boost was tentatively selected by NAA. Chilled, ground-support-equipment-supplied water-glycol would be pumped through the spacecraft coolant system until 30 seconds before launch, when these lines would be disconnected. After umbilical separation the glycol, as it evaporated at the water boiler, would be chilled by Freon stored in the water tanks.

• Apollo spacecraft design criteria - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  The Manned Space Flight Management Council decided that the Apollo spacecraft design criteria should be worked out under the guidance of the Office of Manned Space Flight (OMSF) Office of Systems. These criteria should be included in the systems specifications to be developed. A monthly exchange of information on spacecraft weight status should take place among the Centers and OMSF. Eldon W. Hall of the Office of Space Systems would be responsible for control of the detailed system weights.

• Apollo Command module flotation studies - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  Command module (CM) flotation studies were made by NAA, in which the heatshield was assumed to be upright with no flooding having occurred between the CM inner and outer walls. The spacecraft was found to have two stable attitudes: the desired upright position and an unacceptable on-the-side position 128 degrees from the vertical. Further studies were scheduled to determine how much lower the CM center of gravity would have to be to eliminate the unacceptable stable condition and to measure the overall flotation stability when the CM heatshield was extended.

• Docking methods for Apollo investigated - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Docking.

  NAA investigated several docking methods. These included extendable probes to draw the modules together; shock-strut arms on the lunar excursion module with ball locators to position the modules until the spring latch caught, fastening them together; and inflatable Mylar and polyethylene plastic tubing. Also considered was a system in which a crewman, secured by a lanyard, would transfer into the open lunar excursion module. Another crewman in the open command module airlock would then reel in the lanyard to bring the modules together.

• Camera selected for Apollo mission photo documentation - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute.

  A 70-mm pulse camera was selected by NAA for mission photodocumentation. The camera was to be carried in the upper parachute compartment. Because of the lack of space and the need for a constant power supply for a 35-watt heating element, NAA was considering placing the camera behind the main display panel. The advantages of this arrangement were that the camera would require less power, be available for changing magazines, and could be removed for use outside the spacecraft.

  One 16-mm camera was also planned for the spacecraft. This camera would be positioned level with the commander's head and directed at the main display panel. It could be secured to the telescope for recording motion events in real time such as rendezvous, docking, launch and recovery of a lunar excursion module, and earth landing; it could be hand-held for extravehicular activity.

• Optimum configuration of Apollo transponder equipment - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Docking.

  A study was made by NAA to determine optimum location and configuration of the spacecraft transponder equipment. The study showed that, if a single deep space instrumentation facility transponder and power amplifier were carried in the command module instead of two complete systems in the service module, spacecraft weight would be reduced, the system would be simplified, and command and service module interface problems would be minimized. Spares in excess of normal would be provided to ensure reliability.

• Air recirculation system of Apollo command module rearranged - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  Air recirculation system components of the command module were rearranged to accommodate a disconnect fitting and lines for the center crewman's suit. To relieve an obstruction, the cabin pressure regulator was relocated and a design study drawing was completed.

• Final design of the command module forward heatshield release mechanism - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield. Final design of the command module forward heatshield release mechanism was completed by NAA..

• Design of heatshield for Apollo boilerplates completed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield. NAA completed the analysis and design of the Fibreglass heatshield. It duplicated the stiffness of the aluminum heatshield and would be used on all boilerplate spacecraft..

• Control layout of the command module aft compartment released - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  The control layout of the command module aft compartment was released by NAA. This revised drawing incorporated the new umbilical locations in the lower heatshield, relocated the pitch-and-yaw engines symmetrically, eliminated the ground support equipment tower umbilical, and showed the resulting repositioning of tanks and equipment.

• Emergency blow-out hatch study - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Hatch.

  NAA's evaluation of the emergency blow-out hatch study showed that the linear-shaped explosive charge should be installed on the outside of the command module, with a backup structure and an epoxy-foam-filled annulus on the inside of the module to trap fragmentation and gases. Detail drawings of the crew hatch were prepared for fabrication of actual test sections.

• Control layouts for Apollo command module windows completed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield. NAA completed control layouts for all three command module windows, including heatshield windows and sightlines. Structural penalties were investigated, window-panes sized, and a weight-comparison chart prepared..

• Deployment of the Apollo forward heatshield before tower jettison studied - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  After the determination of the basic design of the spacecraft sequencer schematic, the effect of the deployment of the forward heatshield before tower jettison was studied by NAA. The sequence of events of both the launch escape system and earth landing system would be affected, making necessary the selection of different sequences for normal flights and abort conditions. A schematic was prepared to provide for these sequencing alternatives.

• Project Officers for Apollo CSM and LEM contracts named - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. At MSC, J. Thomas Markley was appointed Project Officer for the Apollo spacecraft command and service modules contract, and William F. Rector was named Project Officer for the lunar excursion module contract..

• Heatshield for Apollo boilerplate 1 completed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block I. The heatshield for Apollo command module boilerplate model 1 was completed five days ahead of schedule..

• MIT ordered Honeywell computer for work on the Apollo spacecraft navigation system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  The MIT Instrumentation Laboratory ordered a Honeywell 1800 electronic computer from the Minneapolis- Honeywell Regulator Company's Electronic Data Processing Division for work on the Apollo spacecraft navigation system. After installation in 1963, the computer would aid in circuitry design of the Apollo spacecraft computer and would also simulate full operation of a spaceborne computer during ground tests.

• Apollo BP- 25 impact test in the Pacific Ocean - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Structural. The first completed boilerplate model of the Apollo command module, BP- 25, was subjected to a one-fourth-scale impact test in the Pacific Ocean near the entrance to Los Angeles Harbor. Three additional tests were conducted on August 9..

• Algol motor for Little Joe II booster - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. NASA selected the Aerojet-General Algol solid-propellant motor to power the Little Joe II booster, which would be used to flight-test the command and service modules of the Apollo spacecraft..

• NASA schedule for Apollo command and service modules - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  A NASA program schedule for the Apollo spacecraft command and service modules through calendar year 1965 was established for financial planning purposes and distributed to the NASA Office of Manned Space Flight, Marshall Space Flight Center, and MSC. The key dates were: complete service module drawing release, May 1, 1963; complete command module drawing release, June 15, 1963; manufacture complete on the first spacecraft, February 1, 1964; first manned orbital flight, May 15, 1965. This tentative schedule depended on budget appropriations.

• Reduction in reaction control thrust for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS. NAA suggested that the pitch, roll, and yaw rates required for the Apollo guidance and navigation system would permit reduction in the reaction control thrust..

• First Apollo boilerplate command module, BP-25, delivered for water recovery and handling tests - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery.

  The first Apollo boilerplate command module, BP-25, was delivered to MSC for water recovery and handling tests. Flotation, water stability, and towing tests were conducted with good results. J. Thomas Markley of MSC described all spacecraft structural tests thus far as "successful."

• Length of the Apollo service module increased - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Structural. The length of the Apollo service module was increased from 11 feet 8 inches to 12 feet 11 inches to provide space for additional fuel..

• Contractor for Apollo CM reaction controls changed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS. Responsibility for the design and manufacture of the reaction controls for the Apollo command module was shifted from The Marquardt Corporation to the Rocketdyne Division of NAA, with NASA concurrence..

• Limited testing planned of fire hazards in pure oxygen atmosphere for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS. A preliminary NAA report was completed on a literature search concerning fire hazards in 100 percent oxygen and oxygen-enriched atmospheres. This report showed that limited testing would be warranted..

• Apollo CM high-altitude abort attitude orientation studies completed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS.

  NAA completed attitude orientation studies, including one on the control of a tumbling command module (CM) following high-altitude abort above 125,000 feet. The studies indicated that the CM stabilization and control system would be adequate during the reentry phase with the CM in either of the two possible trim configurations.

• Apollo command module waste management system analysis completed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  The command module waste management system analysis, including a new selection valve, revised tubing lengths, odor removal filter, and three check valves, was completed by NAA for a 5 psia pressure. There was only a small change in the flow rates through the separate branches as a result of the change to 5 psia.

• Effects of crew motions on Apollo attitude control negligible - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance. An NAA study indicated that the effects of crew motions on spacecraft attitude control would be negligible..

• Preliminary studies determine Apollo radiation instrument location - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  Preliminary studies were made by NAA to determine radiation instrument location, feasibility of shadow-shielding, and methods of determining direction of incidence of radiation. Preliminary requirements were established for the number and location of detectors and for information display.

• Decision to redesign Apollo command module fuel cell radiator - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Fuel Cell. A final decision was made by NAA to redesign the command module fuel cell radiator and associated tubing to accommodate a 30-psi maximum pressure drop. Pratt & Whitney Aircraft Division agreed to redesign their pump for this level..

• Details of the Apollo spacecraft described - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Hatch.

  Robert R. Gilruth, Director of MSC, presented details of the Apollo spacecraft at the Institute of the Aerospace Sciences meeting in Seattle, Wash. During launch and reentry, the three-man crew would be seated in adjacent couches; during other phases of flight, the center couch would be stowed to permit more freedom of movement. The Apollo command module cabin would have 365 cubic feet of volume, with 22 cubic feet of free area available to the crew: "The small end of the command module may contain an airlock; when the lunar excursion module is not attached, the airlock would permit a pressure-suited crewman to exit to free space without decompressing the cabin. Crew ingress and egress while on earth will be through a hatch in the side of the command module."

• Apollo launch escape control system eliminated - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES.

  The launch escape thrust-vector-control system was replaced by a passive system using a "kicker" rocket as directed by NASA at the June 10-11 design review meeting, The rocket would be mounted at the top of the launch escape system tower and fired tangentially to impart the necessary pitchover motion during the initial phase of abort. The main motor thrust was revised downward from 180, 000 to 155, 000 pounds and aligned 2.8 degrees off the center line. A downrange abort direction was selected; during abort the spacecraft and astronauts would rotate in a heels over head movement.

• Basic Apollo CM airlock and docking design - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Hatch.

  The establishment of a basic command module (CM) airlock and docking design criteria were discussed by NAA and NASA representatives. While NASA preferred a closed-hatch, one-man airlock system, NAA had based its design on an open-hatch, two-man airlock operation.

  Another closed-hatch configuration under consideration would entirely eliminate the CM airlock. Astronauts transferring to and from the lunar excursion module would be in a pressurized environment constantly.

• First tests incorporating data acquisition in the Apollo test program - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute. The first tests incorporating data acquisition in the Apollo test program were conducted at El Centro, Calif. They consisted of monitoring data returned by telemetry during a parachute dummy-load test..

• Apollo design criteria for food reconstitution bags - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit. NAA established design criteria for materials and processes used in food reconstitution bags. An order was placed for polypropylene material with a contoured mouthpiece. This material would be machined and then heat-fused to a thermoplastic bag..

• Revised NAA Objectives Document - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  The revised NAA Summary Definitions and Objectives Document was released. This revision incorporated the lunar orbit rendezvous concept, without lunar excursion module integration, and a revised master phasing schedule, reflecting the deletion of the second-stage service module. The NAA Apollo Mission Requirements and Apollo Requirements Specifications were also similarly re-oriented and released.

• Layouts of Apollo CM telescope installation - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute.

  Layouts of a command module (CM) telescope installation in the unpressurized upper parachute compartment were completed by NAA. The concept was for the telescope to extend ten inches from the left side of the spacecraft. The light path would enter the upper bulkhead through the main display panel to an eyepiece presentation on the commander's side of the spacecraft. A static seal (one-half-inch-thick window) would be used to prevent leakage in the pressurized compartment. The installation was suitable for use in the lunar orbit rendezvous mission and would allow one man in the CM to accomplish docking with full visual control.

• Interim Apollo flight operation plan for Fiscal Year 1963 - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  An interim Apollo flight operation plan for Fiscal Year 1963, dated August 28, calling for funding of $489.9 million, was transmitted to NASA Headquarters from MSC. System requirements were under study to determine the feasibility of cost reduction to avoid schedule slippage.

• Apollo mockups, and boilerplates deleted - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. NASA deleted five Apollo mockups, three boilerplate spacecraft, and several ground support equipment items from the NAA contract because of funding limitations..

• Apollo boilerplate model BP-1 accepted by NASA - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block I.

  Apollo command module boilerplate model BP-1 was accepted by NASA and delivered to the NAA Engineering Development Laboratory for land and water impact tests. On September 25, BP-1 was drop-tested with good results. Earth-impact attenuation and crew shock absorption data were obtained.

• Fire in a simulated Air Force space cabin - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  Fire broke out in a simulated space cabin at the Air Force School of Aerospace Medicine, Brooks Air Force Base, Tex., on the 13th day of a 14-day experiment to determine the effects of breathing pure oxygen in a long-duration space flight. One of the two Air Force officers was seriously injured. The cause of the fire was not immediately determined. The experiment was part of a NASA program to validate the use of a 5 psia pure oxygen atmosphere for the Gemini and Apollo spacecraft.

• Wooden mockup of Apollo command module received - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  MSC reported that it had received a completed wooden mockup of the interior arrangement of the Apollo command module (CM). An identical mockup was retained at NAA for design control. Seven additional CM and service module (SM) mockups were planned: a partial SM and partial adapter interface, CM for exterior cabin equipment, complete SM, spacecraft for handling and transportation (two), crew support system, and complete CSM's. A mockup of the navigation and guidance equipment had been completed. A wooden mockup of the lunar excursion module exterior configuration was fabricated by NAA as part of an early study of spacecraft compatibility requirements.

• Apollo command module boilerplate model BP-3 shipped - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. Apollo command module boilerplate model BP-3, showing the arrangement of the cabin interior, was shipped to MSC..

• Apollo White Sands Missile Range space facility announced - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM SPS.

  J. Thomas Markley, command and service module Project Officer at MSC, announced details of the space facility to be established by NASA at White Sands Missile Range (WSMR). To be used in testing the Apollo spacecraft's propulsion and abort systems, the WSMR site facilities would include two static-test-firing stands, a control center blockhouse, various storage and other utility buildings, and an administrative services area.

• Deletion and improvement of equipment reduced the weight of the Apollo CSM by 1,239 pounds - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute, CSM Television.

  Deletion of non-critical equipment and improvement of existing systems reduced the weight of the command and service modules by 1,239 pounds, with a target reduction of 1,500 pounds.

  Among the items deleted from the command module (CM) were exercise and recreation equipment, personal parachutes and parachute containers located in the couches, individual survival kits, solar radiation garments, and eight-ball displays. A telescope, cameras and magazines considered scientific equipment, and a television monitor were deleted from the CM instrumentation system.

• First Apollo Little Joe II launch to be for qualification - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. General Dynamics/Convair recommended and obtained NASA's concurrence that the first Little Joe II launch vehicle be used for qualification, employing a dummy payload..

• External natural environment of the Apollo spacecraft reconsidered - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  The external natural environment of the Apollo spacecraft as defined in the December 18, 1961, Statement of Work had been used in the early Apollo design work. The micrometeoroid, solar proton radiation, and lunar surface characteristics were found to be most critical to the spacecraft design.

• Meteoroid test and ballistic ranges established for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Structural.

  MSC reported that meteoroid tests and ballistic ranges had been established at the Ames Research Center, Langley Research Center, and NAA. These facilities could achieve only about one half of the expected velocity of 75,000 feet per second for the critical-sized meteoroid. A measured improvement in the capability to predict penetration would come from a test program being negotiated by NAA with General Motors Corporation, whose facility was capable of achieving particle velocities of 75,000 feet per second.

• Three fuel cells to supply power for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Fuel Cell.

  MSC reported that the three liquid-hydrogen-liquid-oxygen fuel cells would supply the main and emergency power through the Apollo mission except for the earth reentry phase. Two of the fuel cells would carry normal electrical loads and one would supply emergency power. Performance predictions had been met and exceeded in single-cell tests. Complete module tests would begin during the next quarter. The liquid-hydrogen liquid-oxygen reactants for the fuel cell power supply were stored in the supercritical state in spherical pressure vessels. A recent decision had been made to provide heat input to the storage vessels with electrical heaters rather than the water-glycol loop. Three zinc-silver oxide batteries would supply power for all the electrical loads during reentry and during the brief periods of peak loads. One of the batteries was reserved exclusively for the postlanding phase. Eagle Picher Company, Joplin, Mo., had been selected in August as subcontractor for the batteries.

• Apollo lunar excursion module guidance system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  MSC reported that the lunar excursion module guidance system was expected to use as many components as possible identical to those in the command and service modules. Studies at the MIT Instrumentation Laboratory indicated that the changes required would simplify the computer and continue the use of the same inertial measurement unit and scanning telescope.

• Apollo wind tunnel program in eighth month - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield. The Apollo wind tunnel program was in its eighth month. To date, 2,800 hours of time had been used in 30 government and private facilities..

• Apollo training requirements planning 40 percent complete - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  MSC reported that Apollo training requirements planning was 40 percent complete. The preparation of specific materials would begin during the first quarter of 1964. The crew training equipment included earth launch and reentry, orbital and rendezvous, and navigation and trajectory control part-task trainers, which were special-purpose simulators. An early delivery would allow extensive practice for the crew in those mission functions where crew activity was time-critical and required development of particular skills. The mission simulators had complete mission capability, providing visual as well as instrument environments. Mission simulators would be located at MSC and at Cape Canaveral.

• Arnold facilities to be used for development of the Apollo reaction control and propulsion systems - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM SPS.

  MSC reported that Arnold Engineering Development Center facilities at Tullahoma, Tenn., were being scheduled for use in the development of the Apollo reaction control and propulsion systems. The use of the Mark I altitude chamber for environmental tests of the command and service modules was also planned.

• Structural design of the Apollo command module 65 percent complete - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Structural. Release of the structural design of the Apollo command module was 65 percent complete; 100 percent release was scheduled for January 1 963..

• Reliability goal for the Apollo mission set at 90% - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  MSC reported that the reliability goal for design purposes in the spacecraft Statement of Work for the Apollo mission was 0.9. The probability that the crew would not be subjected to conditions in excess of the stated limits was 0.9, and the probability that the crew would not be subjected to emergency limits was 0.999. The initial Work Statement apportionment for the lunar excursion module was 0.984 for mission success and 0.9995 for crew safety. Other major system elements would require reapportionment to reflect the lunar orbit mission.

• Apollo spacecraft weights - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, LM Weight.

  The Apollo spacecraft weights had been apportioned within an assumed 90,000 pound limit. This weight was termed a "design allowable." A lower target weight for each module had been assigned. Achievement of the target weight would allow for increased fuel loading and therefore greater operational flexibility and mission reliability. The design allowable for the command module was 9,500 pounds; the target weight was 8,500 pounds. The service module design allowable was 11,500 pounds; the target weight was 11,000 pounds. The S-IVB adapter design allowable and target weight was 3,200 pounds. The amount of service module useful propellant was 40,300 pounds design allowable; the target weight was 37,120 pounds. The lunar excursion module design allowable was 25,500 pounds; the target weight was 24,500 pounds.

• Apollo pad abort boilerplate command module BP-6 scheduled for delivery by mid-April 1963 - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES. The pad abort boilerplate command module, BP-6, to qualify the launch escape system, was scheduled for delivery to White Sands Missile Range by mid-April 1963. A pad abort test of BP-6 was scheduled for May 15, 1963..

• Honeywell subcontract for Apollo stabilization and control system amended - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance. The Minneapolis-Honeywell Regulator Company letter subcontract for the Apollo stabilization and control system was suspended by NAA and amended in accordance with the current design concepts,.

• RCA to build the data acquisition and communications subsystem for Project Fire - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: FIRE. Republic Aviation Corporation selected the Radio Corporation of America to design and build the data acquisition and communications subsystem for Project Fire..

• Apollo drogue parachutes wind tunnel tests - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute. MSC Director Robert R. Gilruth reported to the Manned Space Flight Management Council that the Apollo drogue parachutes would be tested in the Langley Research Center wind tunnels..

• Incandescent lamps to be used for the Apollo command module - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  Incandescent lamps would be used for floodlighting the command module because they weighed less than fluorescent lamps and took up less space while increasing reliability and reducing system complexity. A 28- volt lamp was most desirable because of its compatibility with the spacecraft 28-volt dc power system. Laboratory tests with a 28-volt incandescent lamp showed that heat dissipation would not be a problem in the vacuum environment but that a filament or shock mount would have to be developed to withstand vibration. An incandescent quartz lamp was studied because of its small size and high concentration of light.

• New launch escape tower configuration designed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES.

  A new launch escape tower configuration with an internal structure that would clear the launch escape motor exhaust plume at 30,000 feet was designed and analyzed by NAA. Exhaust impingement was avoided by slanting the diagonal members in the upper bay toward the interior of the tower and attaching them to a ring.

• Study of Apollo reentry temperatures - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute, CSM Recovery.

  NAA completed a study of reentry temperatures. Without additional cooling, space suit inlet temperatures were expected to increase from 50 degrees F at 100,000 feet to 90 degrees F at spacecraft parachute deployment. The average heat of the command module inner wall was predicted not to exceed 75 degrees F at parachute deployment and 95 degrees F on landing, but then to rise to nearly 150 degrees F.

• Digital computer program for calculating Apollo command module loads - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield, CSM Recovery. An NAA digital computer program for calculating command module heatshield and couch system loads and landing stability was successful. Results showed that a five-degree negative-pitch attitude was preferable for land landings..

• Apollo personal communications system to have a duplex capability with a simplex backup - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications.

  The revised NAA recommendation for a personal communications system consisted of a duplex capability with a simplex backup. Simultaneous transmission of voice and biomedical data with a break-in capability would be possible. Two changes in spacecraft VHF equipment would be needed: a dual-channel in place of a single-channel receiver, and a diplexer for use during duplex operation.

• Valves of the Apollo CM environmental control system modified for 5.0 psia oxygen - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  The valves of the command module (CM) environmental control system were modified to meet the 5.0 psia oxygen operating requirements. All oxygen partial pressure controls were deleted from the system and the relief pressure setting of 7 +/- 0.2 psia was changed to 6 +/- 0.2 psia. The CM now could be repressurized from 0 to 5.0 psia in one hour.

• Apollo CM blowout emergency escape hatch not needed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Hatch, CSM Parachute, CSM Recovery.

  Elimination of the requirement for personal parachutes nullified consideration of a command module (CM) blowout emergency escape hatch. A set of quick-acting latches for the inward-opening crew hatch would be needed, however, to provide a means of egress following a forced landing. The latches would be operable from outside as well as inside the pressure vessel. Outside hardware for securing the ablative panel over the crew door would be required as well as a method of releasing the panel from inside the CM.

• Proposed designs for Apollo view port covers prepared - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  Proposed designs for view port covers on the crew-hatch window, docking ports, and earth landing windows were prepared by NAA. Design planning called for these port covers to be removed solely in the space environment. (Crew members would not use such windows during launch and reentry phases.) NAA,

• NAA completed the firm-cost proposal for the definitive Apollo program - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. NAA completed the firm-cost proposal for the definitive Apollo program and submitted it to NASA. MSC had reviewed the contract package and negotiated a program plan position with NAA..

• Technique for separating the Apollo command and service modules during an abort - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS.

  The technique tentatively selected by NAA for separating the command and service modules from lower stages during an abort consisted of firing four 2000-pound-thrust posigrade rockets mounted on the service module adapter. With this technique, no retrorockets would be needed on the S-IV or S-IVB stages. Normal separation from the S-IVB would be accomplished with the service module reaction control system.

• Study proposed moving the crew and couches - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery.

  An NAA study on the shift of the command module center of gravity during reentry proposed moving the crew and couches about ten inches toward the aft equipment bay and then repositioning them for landing impact.

  A review of body angles used for the current couch geometry disclosed that the thigh-to-torso angle could be closed sufficiently for a brief period during reentry to shorten the overall couch length by the required travel along the Z-Z axis. The more acute angle was desirable for high g conditions. This change in the couch adjustment range, as well as a revision in the lower leg angle to gain structure clearance, would necessitate considerable couch redesign.

• Preliminary design of Apollo CM crew accessories and survival equipment - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit. NAA completed the release of the layout and preliminary design of command module crew accessories and survival equipment..

• Walls of the Apollo spacecraft to provide most of the radiation shielding required for the crew - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield. William L. Gill, Chief of Crew Systems Division's Radiation Branch, MSC, said that the walls of the Apollo spacecraft would provide most of the radiation shielding required for the crew. Astronauts would have special shielding devices only for their eyes..

• Raytheon contracted for the Apollo spacecraft guidance computer - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance. The Manned Spacecraft Center (MSC) and the Raytheon Company came to terms on the definitive contract for the Apollo spacecraft guidance computer..

• Westinghouse to build power conversion units for the Apollo command module - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Electrical.

  North American Aviation, Inc., selected the Aerospace Electrical Division of Westinghouse Electric Corporation to build the power conversion units for the command module (CM) electrical system. The units would convert direct current from the fuel cells to alternating current.

• Firings of the prototype Apollo service propulsion engine completed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM SPS.

  The Aerojet-General Corporation reported completion of successful firings of the prototype service propulsion engine. The restartable engine, with an ablative thrust chamber, reached thrusts up to 21,500 pounds. (Normal thrust rating for the service propulsion engine is 20,500.)

• Four injured when an electrical spark ignited a fire in a Navy altitude chamber - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Electrical.

  Four Navy officers were injured when an electrical spark ignited a fire in an altitude chamber, near the end of a 14-day experiment at the U.S. Navy Air Crew Equipment Laboratory, Philadelphia, Pa. The men were participating in a NASA experiment to determine the effect on humans of breathing pure oxygen for 14 days at simulated altitudes.

• Requirements for the Apollo CSM stabilization and control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance. North American defined requirements for the command and service modules (CSM) stabilization and control system..

• Contract to Ling-Temco-Vought to develop the velocity package for Project Fire - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: FIRE.

  NASA awarded a $2.56 million contract to Ling-Temco-Vought, Inc. (LTV), to develop the velocity package for Project Fire, to simulate reentry from a lunar mission. An Atlas D booster would lift an instrumented payload (looking like a miniature Apollo CM) to an altitude of 122,000 meters (400,000 feet). The velocity package would then fire the reentry vehicle into a minus 15 degree trajectory at a velocity of 11,300 meters (37,000 feet) per second. On December 17, Republic Aviation Corporation, developer of the reentry vehicle, reported that design was 95 percent complete and that fabrication had already begun.

• First Apollo CM inertial reference integrating gyro - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  AC Spark Plug Division of General Motors Corporation assembled the first CM inertial reference integrating gyro (IRIG) for final tests and calibration. Three IRIGs in the CM navigation and guidance system provided a reference from which velocity and attitude changes could be sensed. Delivery of the unit was scheduled for February 1963.

• Problems with the Apollo CM's aerodynamic characteristics - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute, CSM Recovery.

  North American reported several problems involving the CM's aerodynamic characteristics; their analysis of CM dynamics verified that the spacecraft could - and on one occasion did - descend in an apex-forward attitude. The CM's landing speed then exceeded the capacity of the drogue parachutes to reorient the vehicle; also, in this attitude, the apex cover could not be jettisoned under all conditions. During low-altitude aborts, North American went on, the drogue parachutes produced unfavorable conditions for main parachute deployment.

• New heatshield design for the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield. Extensive material and thermal property tests indicated that a Fiberglas honeycomb matrix bonded to the steel substructure was a promising approach for a new heatshield design for the CM..

• Motorola to produce the Apollo spacecraft S-band transponder - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications.

  Collins Radio Company selected Motorola, Inc., Military Electronics Division, to develop and produce the spacecraft S-band transponder. The transponder would aid in tracking the spacecraft in deep space; also, it would be used to transmit and receive telemetry signals and to communicate between ground stations and the spacecraft by FM voice and television links. The formal contract with Motorola was awarded in mid-February 1963.

  Also, Collins awarded a contract to the Leach Corporation for the development of command and service module (CSM) data storage equipment. The tape recorders must have a five-hour capacity for collection and storage of data, draw less than 20 watts of power, and be designed for in-flight reel changes.

• Contract for wind tunnel tests of the Apollo spacecraft - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. MSC awarded a $222,000 contract to the Air Force Systems Command for wind tunnel tests of the Apollo spacecraft at its Arnold Engineering Development Center, Tullahoma, Tenn..

• Changes in the layout of the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Hatch, CSM Heat Shield, CSM Recovery.

  North American made a number of changes in the layout of the CM:

  • Putting the lithium hydroxide canisters in the lower equipment bay and food stowage compartments in the aft equipment bay.
  • Regrouping equipment in the left-hand forward equipment bay to make pressure suit disconnects easier to reach and to permit a more advanced packaging concept for the cabin heat exchanger.
  • Moving the waste management control panel and urine and chemical tanks to the right-hand equipment bay.
  • Revising the aft compartment control layout to eliminate the landing impact attenuation system and to add tie rods for retaining the heatshield.
  • Preparing a design which would incorporate the quick release of the crew hatch with operation of the center window (drawings were released, and target weights and criteria were established).
  • Redesigning the crew couch positioning mechanism and folding capabilities.
  • Modifying the footrests to prevent the crew's damaging the sextant.

• Photographic equipment needed for Apollo missions - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  The MSC Apollo Spacecraft Project Office (ASPO) outlined the photographic equipment needed for Apollo missions. This included two motion picture cameras (16- and 70-mm) and a 35-mm still camera. It was essential that the camera, including film loading, be operable by an astronaut wearing pressurized gloves. On February 25, 1963, NASA informed North American that the cameras would be government furnished equipment.

• Spacesuited astronaut use of Apollo navigation equipment studied - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  At a meeting held at Massachusetts Institute of Technology (MIT) Instrumentation Laboratory, representatives of MIT, MSC, Hamilton Standard Division, and International Latex Corporation examined the problem of an astronaut's use of optical navigation equipment while in a pressurized suit with helmet visor down. MSC was studying helmet designs that would allow the astronaut to place his face directly against the helmet visor; this might avoid an increase in the weight of the eyepiece. In February 1963, Hamilton Standard recommended adding corrective devices to the optical system rather than adding corrective devices to the helmet or redesigning the helmet. In the same month, ASPO set 52.32 millimeters 2.06 inches as the distance of the astronaut's eye away from the helmet. MIT began designing a lightweight adapter for the navigation instruments to provide for distances of up to 76.2 millimeters (3 inches).

• North American released the Request For Proposals on the Apollo mission simulator - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Simulator.

  With NASA's concurrence, North American released the Request For Proposals on the Apollo mission simulator. A simulated CM, an instructor's console, and a computer complex now supplanted the three part- task trainers originally planned. An additional part-task trainer was also approved. A preliminary report describing the device had been submitted to NASA by North American. The trainer was scheduled to be completed by March 1964.

• First static firing of the Apollo tower jettison motor - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES. The first static firing of the Apollo tower jettison motor, under development by Thiokol Chemical Corporation, was successfully performed..

• Apollo spacecraft systems modifications to achieve a 100-day Earth- orbital capability. - . Nation: USA. Related Persons: Maynard. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo X.

  Owen E. Maynard, Head of MSC's Spacecraft Integration Branch, reported on his preliminary investigation of the feasibility of modifying Apollo spacecraft systems to achieve a 100-day Earth- orbital capability. His investigation examined four basic areas: (1) mission, propulsion, and flight time; (2) rendezvous, reentry, and landing; (3) human factors; and (4) spacecraft command and communications. Although modifications to some systems might be extensive- and would involve a considerable weight increase for the vehicle-such a mission using Apollo hardware was indeed feasible.

• Approaches for sea-markers to indicate the location of the Apollo spacecraft after a water landing - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery.

  Northrop Corporation's Ventura Division, prime contractor for the development of sea-markers to indicate the location of the spacecraft after a water landing, suggested three possible approaches:

  1. A shotgun shell type that would dispense colored smoke.
  2. A floating, controlled-rate dispenser (described as an improvement on the current water-soluble binder method).
  3. A floating panel with relatively permanent fluorescent qualities.
  Northrop Ventura recommended the first method, because it would produce the strongest color and size contrast and would have the longest life for its weight.

• Vacuum chamber required at Florida to test Apollo spacecraft systems during prelaunch checkout - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS. MSC officials, both in Houston and at the Preflight Operations Division at Cape Canaveral, agreed on a vacuum chamber at the Florida location to test spacecraft systems in a simulated space environment during prelaunch checkout..

• First working model of the Apollo CM crew couch was demonstrated - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  The first working model of the crew couch was demonstrated during an inspection of CM mockups at North American. As a result, the contractor began redesigning the couch to make it lighter and simpler to adjust. Design investigation was continuing on crew restraint systems in light of the couch changes. An analysis of acceleration forces imposed on crew members during reentry at various couch back and CM angles of attack was nearing completion.

• Apollo spacecraft atmosphere of pure oxygen at 5 psia acceptable - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  MSC Director Robert R. Gilruth reported to the MSF Management Council that tests by Republic Aviation Corporation, the U.S. Air Force School of Aerospace Medicine SAM at Brooks Air Force Base, Tex., and the U.S. Navy Air Crew Equipment Laboratory (ACEL) at Philadelphia, Pa., had established that, physiologically, a spacecraft atmosphere of pure oxygen at 3.5 newtons per square centimeter (five pounds per square inch absolute (psia)) was acceptable. During the separate experiments, about 20 people had been exposed to pure oxygen environments for periods of up to two weeks without showing adverse effects. Two fires had occurred, one on September 10 at SAM and the other on November 17 at ACEL. The cause in both cases was faulty test equipment. On July 11, NASA had ordered North American to design the CM for 3.5 newtons per square centimeter (5-psia), pure-oxygen atmosphere.

• Apollo CM boilerplate (BP) 3 delivered - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute, CSM Recovery. North American delivered CM boilerplate (BP) 3, to Northrop Ventura, for installation of an earth-landing system. BP-3 was scheduled to undergo parachute tests at El Centro, Calif., during early 1963..

• Honeywell submitted proposal for the Apollo stabilization and control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance. The Minneapolis-Honeywell Regulator Company submitted to North American cost proposal and design specifications on the Apollo stabilization and control system, based upon the new Statement of Work drawn up on December 17..

• Static fireing of launch escape system pitch-control motors - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES. Lockheed Propulsion Company successfully static fired four launch escape system pitch-control motors. In an off-the-pad or low-altitude abort, the pitch-control motor would fix the trajectory of the CM after its separation from the launch vehicle..

• First test firings of the Apollo CM reaction control engines - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS. North American's Rocketdyne Division completed the first test firings of the CM reaction control engines..

• Radiation to develop the Apollo CM telemetry system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications.

  North American selected Radiation, Inc., to develop the CM pulse code modulation (PCM) telemetry system. The PCM telemetry would encode spacecraft data into digital signals for transmission to ground stations. The $4.3 million contract was officially announced on February 15, 1963.

• Contract for Apollo CSM C-band transponder to American Car and Foundry - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications.

  The contract for the development and production of the CSM C-band transponder was awarded to American Car and Foundry Industries, Inc., by Collins Radio Company. The C-band transponder was used for tracking the spacecraft. Operating in conjunction with conventional, earth-based, radar equipment, it transmitted response pulses to the Manned Space Flight Network,

• Reliability-crew safety design reviews for the Apollo CM environmental control system (ECS) - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  In the first of a series of reliability-crew safety design reviews on all systems for the CM, North American examined the spacecraft's environmental control system (ECS). The Design Review Board approved the overall ECS concept, but made several recommendations for further refinement. Among these were:

  • The ECS should be made simpler and the system's controls should be better marked and located.
  • Because of the pure oxygen environment, all flammable materials inside the cabin should be eliminated.
  • Sources of possible atmospheric contamination should be further reviewed, with emphasis upon detecting and controlling such toxic gases inside the spacecraft.

• Convair contract negotiations for the Apollo Little Joe II launch vehicle - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  NASA and General Dynamics/Convair (GD/C) began contract negotiations on the Little Joe II launch vehicle, which was used to flight-test the Apollo launch escape system. The negotiated cost was nearly $6 million. GD/C had already completed the basic structural design of the vehicle.

• Static firings of the Apollo launch escape motor - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES. North American reported three successful static firings of the launch escape motor. The motor would pull the CM away from the launch vehicle if there were an abort early in a mission..

• Operational factors in Apollo water and land landings - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery.

  MSC Flight Operations Division examined the operational factors involved in Apollo water and land landings. Analysis of some of the problems leading to a preference for water landing disclosed that:

  • Should certain systems on board the CM fail, the spacecraft could land as far as 805 kilometers 500 miles from the prime recovery area. This contingency could be provided for at sea, but serious difficulties might be encountered on land.
  • Because Apollo missions might last as long as two weeks, weather forecasting for the landing zone probably would be unreliable.
  • Hypergolic fuels were to remain on board the spacecraft through landing. During a landing at sea, the bay containing the tanks would flood and seawater would neutralize the liquid fuel or fumes from damaged tanks. On land, the possibility of rupturing the tanks was greater and the danger of toxic fumes and fire much more serious.
  • Should the CM tumble during descent, the likelihood of serious damage to the spacecraft was less for landings on water.
  • On land, obstacles such as rocks and trees might cause serious damage to the spacecraft.
  • The spacecraft would be hot after reentry. Landing on water would cool the spacecraft quickly and minimize ventilation problems.
  • The requirements for control during reentry were less stringent in a sea landing, because greater touchdown dispersions could be allowed.
  • Since the CM must necessarily be designed for adequate performance in a water landing all aborts during launch and most contingencies required a landing at sea , the choice of water as the primary landing surface could relieve some constraints in spacecraft design.

• General arrangement of the Apollo CM instrument panel - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit. MSC reported that the general arrangement of the CM instrument panel had been designed to permit maximum manual control and flight observation by the astronauts..

• Contract for large vacuum chambers for Apollo testing - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  MSC awarded a $3.69 million contract to the Radio Corporation of America

  RCA Service Company to design and build two vacuum chambers at MSC. The facility was used in astronaut training and spacecraft environmental testing. using carbon arc: lamps, the chambers simulated the sun's intensity, permitting observation of the effects of solar heating encountered on a lunar mission. At the end of July, MSC awarded RCA another contract (worth $3,341,750) for these solar simulators.

• Existing C-band tracking radars to be modified to increase range for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications.

  After studying the present radar coverage provided by ground stations for representative Apollo trajectories, North American recommended that existing C-band radars be modified to increase ranging limits. The current capability for tracking to 920 kilometers (500 nautical miles), while satisfactory for near-earth trajectories, was wholly inadequate for later Apollo missions. Tracking capability should be extended to 59,000 kilometers (32,000 nautical miles), North American said; and to improve tracking accuracy, transmitter power and receiver sensitivity should be increased.

• Airborne Instruments Laboratory contracted for Apollo CM recovery antenna system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery. North American awarded Airborne Instruments Laboratory, a division of Cutler-Hammer, Inc., a contract for the CM recovery antenna system. NAA,.

• Apollo CM reentry heating rates discussed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  Representatives of North American, Langley Research Center, Ames Research Center, and MSC discussed CM reentry heating rates. They agreed on estimates of heating on the CM blunt face, which absorbed the brunt of reentry, but afterbody heating rates were not as clearly defined. North American was studying Project Mercury flight data and recent Apollo wind tunnel tests to arrive at revised estimates.

• Digital up-data link for Gemini acceptable for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications.

  Christopher C. Kraft, Jr., of MSC's Flight Operations Division (FOD), advised ASPO that the digital up-data link being developed for the Gemini program appeared acceptable for Apollo as well. In late October 1962, representatives of FOD and ASPO had agreed that an independent up-data link a means by which the ground could feed current information to the spacecraft's computer during a mission was essential for manned Apollo flights. Kraft proposed that the Gemini-type link be used for Apollo as well, and on June 13 MSC ordered North American to include the device in the CM.

• Two aerodynamic strakes added to Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield, CSM LES.

  Two aerodynamic strakes were added to the CM to eliminate the danger of a hypersonic apex-forward trim point on reentry. (During a high-altitude launch escape system (LES) abort, the crew would undergo excessive g forces if the CM were to trim apex forward. During a low-altitude abort, there was the potential problem of the apex cover not clearing the CM. The strakes, located in the yaw plane, had a maximum span of one foot and resulted in significant weight penalties. Additional Details: here....

• Crew mobility evaluation of the ILC Apollo pressure suit conducted - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  The first evaluation of crew mobility in the International Latex Corporation (ILC) pressure suit was conducted at North American to identify interface problems. Three test subjects performed simulated flight tasks inside a CM mockup. CM spatial restrictions on mobility were shown. Problems involving suit sizes, crew couch dimensions, and restraint harness attachment, adjustment, and release were appraised. Numerous items that conflicted with Apollo systems were noted and passed along to ILC for correction in the continuing suit development program.

• Apollo CM heatshield development program - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  NASA authorized North American to extend until June 10 the CM heatshield development program. This gave the company time to evaluate and recommend one of the three ablative materials still under consideration. The materials were subjected to tests of thermal performance, physical and mechanical properties, and structural compatibility with the existing heatshield substructure. North American sought also to determine the manufacturing feasibility of placing the materials in a Fiberglas honeycomb matrix bonded to a steel substructure.

• Full-scale firings of redesigned Apollo service propulsion engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM SPS. Aerojet-General Corporation, Sacramento, Calif., began full-scale firings of a service propulsion engine with a redesigned injector baffle..

• Definitive contract let to Raytheon Company for command module (Apollo CM) onboard digital computer - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  MSC issued a definitive contract for $15,029,420 to the Raytheon Company, Space and Information Systems Division, to design and develop the CM onboard digital computer. The contract was in support of the MIT Instrumentation Laboratory, which was developing the Apollo guidance and navigation systems. Announcement of the contract was made on February 11.

• The first inertial reference integrating gyro for Apollo was accepted - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance. The first inertial reference integrating gyro produced by AC Spark Plug was accepted by NASA and delivered to the MIT Instrumentation Laboratory..

• North American Apollo impact test facility completed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Structural.

  The North American Apollo impact test facility at Downey, Calif., was completed. This facility consisted mainly of a large pool with overhead framework and mechanisms for hydrodynamic drop tests of the CM. Testing at the facility began with the drop of boilerplate 3 on March 11.

• Bell to provide propellant tanks for the Apollo CSM reaction control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS.

  North American selected Bell Aerosystems Company to provide propellant tanks for the CSM reaction control system. These tanks were to be the "positive expulsion" type (i.e., fuel and oxidizer would be contained inside flexible bladder; pressure against one side of the device would force the propellant through the RCS lines).

• Apollo CM boilerplate 19 shipped - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute. North American shipped CM boilerplate 19 to Northrop Ventura for use as a parachute test vehicle..

• MSC issued a Request for Proposals (due by March 13) for a radiation altimeter system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  MSC issued a Request for Proposals (due by March 13) for a radiation altimeter system. Greater accuracy than that provided by available radar would be needed during the descent to the lunar surface, especially in the last moments before touchdown. Preliminary MSC studies had indicated the general feasibility of an altimeter system using a source-detector-electronics package. After final selection and visual observation of the landing site, radioactive material would be released at an altitude of about 30 meters 100 feet and allowed to fall to the surface. The detector would operate in conjunction with electronic circuitry to compute the spacecraft's altitude. Studies were also under way at MSC on the possibility of using laser beams for range determination.

• Batteries independent of the main electrical system in the Apollo CM to fire all pyrotechnics - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Electrical. MSC ordered North American to provide batteries, wholly independent of the main electrical system in the CM, to fire all pyrotechnics aboard the spacecraft..

• Apollo centrifuge facility - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Simulator. NASA selected Ford, Bacon, and Davis, Inc., to design MSC's flight acceleration facility, including a centrifuge capable of spinning a simulated CM and its crew at gravity forces equal to those experienced in space flight..

• Elgin subcontract for central timing equipment for the Apollo spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  Elgin National Watch Company received a subcontract from North American for the design and development of central timing equipment for the Apollo spacecraft. (This equipment provided time-correlation of all spacecraft time-sensitive events. Originally, Greenwich Mean Time was to be used to record all events, but this was later changed.

• Apollo solid parachute from Pioneer Parachute - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute.

  As a parallel to the existing Northrop Ventura contract, and upon authorization by NASA, North American awarded a contract for a solid parachute program to the Pioneer Parachute Company. (A solid parachute is one with solid (unbroken) gores; the sole opening in the canopy is a vent at the top. Ringsail parachutes (used on the Northrop Ventura recovery system) have slotted gores. In effect, each panel formed on the gores becomes a "sail.")

• Contract to Perkin-Elmer for an Apollo carbon dioxide measurement system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  MSC awarded a $67,000 contract to The Perkin-Elmer Corporation to develop a carbon dioxide measurement system, a device to measure the partial carbon dioxide pressure within the spacecraft's cabin. Two prototype units were to be delivered to MSC for evaluation. About seven months later, a $249,000 definitive contract for fabrication and testing of the sensor was signed.

• Disadvantages of the land recovery mode for Apollo missions - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery.

  The Mission Analysis Branch (MAB) of MSC's Flight Operations Division cited the principal disadvantages of the land recovery mode for Apollo missions. Of primary concern was the possibility of landing in an unplanned area and the concomitant dangers involved. For water recovery, the main disadvantages were the establishment of suitable landing areas in the southern hemisphere and the apex-down flotation problem. MAB believed no insurmountable obstacles existed for either approach.

• North American completed Apollo boilerplate (BP) 9 - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES.

  North American completed construction of Apollo boilerplate (BP) 9, consisting of launch escape tower and CSM. It was delivered to MSC on March 18, where dynamic testing on the vehicle began two days later. On April 8, BP-9 was sent to MSFC for compatibility tests with the Saturn I launch vehicle.

• First Block I Apollo pulsed integrating pendulum accelerometer delivered - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  The first Block I Apollo pulsed integrating pendulum accelerometer, produced by the Sperry Gyroscope Company, was delivered to the MIT Instrumentation Laboratory. (Three accelerometers were part of the guidance and navigation system. Their function was to sense changes in spacecraft velocity.)

• Apollo CM boilerplate (BP) 6 moved to the Apollo Test Preparation Interim Area at Downey - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES.

  North American moved CM boilerplate (BP) 6 from the manufacturing facilities to the Apollo Test Preparation Interim Area at Downey, Calif. During the next several weeks, BP-6 was fitted with a pad adapter, an inert launch escape system, and a nose cone, interstage structure, and motor skirt.

• First Little Joe II completed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Electrical.

  General Dynamics Convair completed structural assembly of the first launcher for the Little Joe II test program. During the next few weeks, electrical equipment installation, vehicle mating, and checkout were completed. The launcher was then disassembled and delivered to WSMR on April 25, 1963.

• North American analyzed lighting conditions in the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  North American analyzed lighting conditions in the CM and found that glossy or light-colored garments and pressure suits produced unsatisfactory reflections on glass surfaces. A series of tests were planned to define the allowable limits of reflection on windows and display panel faces to preclude interference with crew performance.

• Meeting to define Apollo CM-space suit interface problem areas - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo CSM, CSM ECS.

  A meeting was held at North American to define CM-space suit interface problem areas. Demonstrations of pressurized International Latex suits revealed poor crew mobility and task performance inside the CM, caused in part by the crew's unavoidably interfering with one another.

  Other items received considerable attention: A six-foot umbilical hose would be adequate for the astronaut in the CM. The location of spacecraft water, oxygen, and electrical fittings was judged satisfactory, as were the new couch assist handholds. The astronaut's ability to operate the environmental control system (ECS) oxygen flow control valve while couched and pressurized was questionable. Therefore, it was decided that the ECS valve would remain open and that the astronaut would use the suit control valve to regulate the flow. It was also found that the hand controller must be moved about nine inches forward.

• Beginning of Apollo CM environmental control system tests - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  MSC announced the beginning of CM environmental control system tests at the AiResearch Manufacturing Company simulating prelaunch, ascent, orbital, and reentry pressure effects. Earlier in the month, analysis had indicated that the CM interior temperature could be maintained between 294 K (70 degrees F) and 300 K (80 degrees F) during all flight operations, although prelaunch temperatures might rise to a maximum of 302 K (84 degrees F).

• Allison to fabricate the Apollo SM fuel and oxidizer tanks - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM SPS. North American selected two subcontractors to build tankage for the SM: Allison Division of General Motors Corporation to fabricate the fuel and oxidizer tanks; and Airite Products, Inc., those for helium storage..

• Revised angles for the crew couch in the Apollo CM considered - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  To provide a more physiologically acceptable load factor orientation during reentry and abort, MSC was considering revised angles for the crew couch in the CM. To reduce the couch's complexity, North American had proposed adjustments which included removable calf pads and a movable head pad.

• Preference for a fixed Apollo CM crew couch - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  At a North American design review, NASA representatives expressed a preference for a fixed CM crew couch. This would have the advantages of simplified design, elimination of couch adjustments by the crew, and better placement of the astronauts to withstand reentry loads. NASA authorized North American to adopt the concept following a three-week study by the company to determine whether a favorable center of gravity could be achieved without a movable couch.

  Use of the fixed couch required relocation of the main and side display panels and repositioning of the translational and rotational hand controllers. During rendezvous and docking operations, the crew would still have to adjust their normal body position for proper viewing.

• Link to build Apollo lunar mission simulators - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Simulator.

  North American awarded a $9.5 million letter contract to the Link Division of General Precision, Inc., for the development and installation of two spacecraft simulators, one at MSC and the other at the Launch Operations Center. Except for weightlessness, the trainers would simulate the entire lunar mission, including sound and lighting effects.

• North American simplified the Apollo CM water management system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery.

  North American simplified the CM water management system by separating it from the freon system. A 4.5- kilogram (10-pound) freon tank was installed in the left-hand equipment bay. Waste water formed during prelaunch and boost, previously ejected overboard, could now be used as an emergency coolant. The storage capacity of the potable water tank was reduced from 29 to 16 kilograms (64 to 36 pounds) and the tank was moved to the lower equipment bay to protect it from potential damage during landing. These and other minor changes caused a reduction in CM weight and an increase in the reliability of the CM's water management system.

• Simmonds Precision build electronic propellant gauge for Apollo service propulsion system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM SPS.

  North American chose Simmonds Precision Products, Inc., to design and build an electronic measurement and display system to gauge the service propulsion system propellants. Both a primary and a backup system were required by the contract, which was expected to cost about 2 million.

• Changes in Apollo boilerplate 22 LES test - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES. On the basis of wind tunnel tests and analytical studies, North American recommended a change in the planned test of the launch escape system (LES) using boilerplate 22. . Additional Details: here....

• Contract for solid propellant motors for the Apollo launch escape system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES. North American signed a 6 million definitive contract with Lockheed Propulsion Company for the development of solid propellant motors for the launch escape system. Work on the motors had begun on February 13, 1962, when Lockheed was selected..

• Apollo spacecraft landing and recovery procedures reviewed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery.

  At ASPO's request, Wayne E. Koons of the Flight Operations Division visited North American to discuss several features of spacecraft landing and recovery procedures. Koon's objective, in short, was to recommend a solution when ASPO and the contractor disagreed on specific points, and to suggest alternate courses when the two organizations agreed. A question had arisen about a recovery hoisting loop. Neither group wanted one, as its installation added weight and caused design changes. In another area, North American wanted to do an elaborate study of the flotation characteristics of the CM. Koons recommended to ASPO that a full-scale model of the CM be tested in an open-sea environment.

  There were a number of other cases wherein North American and ASPO agreed on procedures which simply required formal statements of what would be done. Examples of these were:

  • Spacecraft reaction control fuel would be dumped before landing (in both normal and abort operations)
  • The "peripheral equipment bay" would be flooded within 10 minutes after landing
  • Location aids would be dye markers and recovery antennas.

• Qualification drop test series for the earth landing system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute, CSM Recovery.

  At El Centro, Calif., Northrop Ventura conducted the first of a series of qualification tests for the Apollo earth landing system (ELS). The test article, CM boilerplate 3, was dropped from a specially modified Air Force C-133. The test was entirely successful. The ELS's three main parachutes reduced the spacecraft's rate of descent to about 9.1 meters (30 feet) per second at impact, within acceptable limits.

• Carbon dioxide sensors to be part of Apollo environmental control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS. NASA authorized North American to procure carbon dioxide sensors as part of the environmental control system instrumentation on early spacecraft flights..

• Contract to Westinghouse for study of potential physiological damage by cosmic radiation - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Electrical. In support of NASA's manned space flight programs, Ames Research Center awarded a $150,000 contract to Westinghouse Electric Corporation for a one-year study of potential physiological damage in space caused by cosmic radiation..

• Problems with side-arm controller location and armrest design inside the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  North American demonstrated problems with side-arm controller location and armrest design inside the CM. Major difficulties were found when the subject tried to manipulate controls while wearing a pressurized suit. North American had scheduled further study of these design problems.

• Apollo lunar landing mission duration profiles approved - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  MSC Director Robert R. Gilruth reported to the MSF Management Council that the lunar landing mission duration profiles, on which North American would base the reliability design objectives for mission success and crew safety and which assumed a 14-day mission, had been documented and approved. The contractor had also been asked to study two other mission profile extremes, a 14-day mission with 110-hour transearth and translunar transfer times and the fastest practicable lunar landing mission.

• Three methods of providing a recovery hoisting loop on the Apollo CM considered - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute, CSM Recovery.

  The Operational Evaluation and Test Branch of MSC's Flight Operations Division considered three methods of providing a recovery hoisting loop on the CM: loop separate from the spacecraft and attached after landing, use of the existing parachute bridle, and loop installed as part of the CM equipment similar to Mercury and Gemini. Studies showed that the third method was preferable.

• Major change to the Little Joe II launch vehicle - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  NASA and General Dynamics Convair negotiated a major change on the Little Joe II launch vehicle contract. It provided for two additional launch vehicles which would incorporate the attitude control subsystem (as opposed to the early fixed-fin version). On November 1, MSC announced that the contract amendment was being issued. NASA Headquarters' approval followed a week later.

• Most Apollo CM subsystem designs frozen - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. Most CM subsystem designs frozen..

• ITT to provide battery chargers for the Apollo CSM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Electrical. North American announced that it had selected ITT's Industrial Products Division to provide battery chargers for the CSM, designed for an operational lifetime of 40,000 hours..

• Definitive Apollo contract with North American delivered to NASA Headquarters - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. The $889.3 million definitive Apollo contract with North American was delivered to NASA Headquarters for review and approval. The target date for approval was extended to June 30..

• Recommendations on Apollo postlanding water survival equipment - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  The Operational Evaluation and Test Branch of MSC's Flight Operations Division made the following recommendations on Apollo postlanding water survival equipment:

  • Development should continue on a three-man life raft for the Apollo mission.
  • A 12-hour-duration dye marker packet should be passively deployed on impact. An additional 18 hours of dye marker should be stored in the survival kit.
  • Two radio beacons of the type being developed for Gemini should be included in the survival kit.
  • Water egress safety features in the Mercury and Gemini space suits should be included in the Apollo space suit.
  • All Apollo equipment which might be involved in water egress, survival, and recovery situations should be configured for water landings.

• Up-data link (UDL) to be included on the Apollo LEM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications, LM Communications.

  Christopher C. Kraft, Jr., of the MSC Flight Operations Division, urged that an up-data link (UDL) be included on the LEM. In general, the UDL would function when a great deal of data had to be transmitted during a time-critical phase. It would also permit utilization of the ground operational support system as a relay station for the transmission of data between the CM and LEM. In case of power failure aboard the LEM, the UDL could start the computer faster and more reliably than a manual voice link, and it could be used to resume synchronization in the computer timing system.

• Backup testing program completed on alternate ablative materials for the Apollo CM heatshield - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  North American completed a backup testing program (authorized by MSC on November 20, 1962) on a number of ablative materials for the CM heatshield. Only one of the materials (Avcoat 5026-39) performed satisfactorily at low temperatures. During a meeting on June 18 at MSC, company representatives discussed the status of the backup heatshield program. This was followed by an Avco Corporation presentation on the primary heatshield development. As a result, MSC directed North American to terminate its backup program. Shortly thereafter, MSC approved the use of an airgun to fill the honeycomb core of the heatshield with ablative material.

• Skip lunar reentry trajectories studied for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery. The Mission Analysis Branch (MAB) of MSC's Flight Operations Division studied the phenomenon of a spacecraft's "skip" when reentering the earth's atmosphere from lunar trajectories and how that skip relates to landing accuracies.. Additional Details: here....

• Definitive contract for the navigation and guidance equipment for the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance. NASA Headquarters approved a definitive contract for $35,844,550 with AC Spark Plug for the manufacture and testing of navigation and guidance equipment for the CM. This superseded a letter contract of May 30, 1962..

• Mockup review of the Apollo mission simulator - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Simulator. At its plant in Binghampton, N. Y., Link Division of General Precision, Inc., held a mockup review of the Apollo mission simulator. A number of modifications in the instructor's console were suggested..

• Definitive contract with Allison for the Apollo service propulsion system propellant tanks - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM SPS. North American signed (and NASA approved) a definitive contract with Allison Division of General Motors for the service propulsion system propellant tanks..

• Avien to develop the steerable S-band antenna for the Apollo CSM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications. North American awarded a contract, valued at $2.8 million, to Avien, Inc., to develop the steerable S-band antenna for the CSM..

• Design of the Apollo CM's stabilization and control system frozen - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance. North American officially froze the design of the CM's stabilization and control system..

• First full-scale firing of the Apollo SM engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Electrical.

  The first full-scale firing of the SM engine was conducted at the Arnold Engineering Development Center. At the start of the shutdown sequence, the engine thrust chamber valve remained open because of an electrical wiring error in the test facility. Consequently the engine ran at a reduced chamber pressure while the propellant in the fuel line was exhausted. During this shutdown transient, the engine's nozzle extension collapsed as a result of excessive pressure differential across the nozzle skin.

• Apollo CSM data storage equipment modified to incorporate a fast-dump capability - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications. The CSM data storage equipment was modified to incorporate a fast-dump capability. Data could thus be recorded at a low speed for later playback at high speed to ground stations..

• Apollo Pioneer tri-conical solid parachutes canceled - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute. A cluster of two Pioneer tri-conical solid parachutes was tested; both parachutes failed. Because of this unsatisfactory performance, the Pioneer solid-parachute program was officially canceled on July 15..

• Apollo mission success predictions continued to be less than the apportioned values - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS. North American reported that mission success predictions continued to be less than the apportioned values. For example, the environmental control subsystem had a predicted mission reliability of 0.9805, compared to a 0.997675 apportionment..

• Apollo CM boilerplate 6 shipped - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. North American shipped Apollo CM boilerplate 6 and its ground support equipment to WSMR..

• Review of the Apollo CM main display console - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit. North American held a review of the CM main display console, which would be compatible with the fixed couch and new panel location. The contractor's drawings and comments by the astronauts were then reviewed by MSC..

• Several restraint systems for the sleeping area in the equipment bay area of the Apollo CM studied - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  North American reported that it had tried several types of restraint systems for the sleeping area in the equipment bay area of the CM. A "net" arrangement worked fairly well and was adaptable to the constant wear garment worn by the crew. However, North American believed that a simpler restraint system was needed, and was pursuing several other concepts.

• Prototype engine for the Apollo SM reaction control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS. The Marquardt Corporation began testing the prototype engine for the SM reaction control system. Preliminary data showed a specific impulse slightly less than 300 seconds..

• Little Joe II qualification test vehicle shipped - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. The Little Joe II qualification test vehicle was shipped from the General Dynamics Convair plant to WSMR, where the test launch was scheduled for August..

• Testing of the launch escape system pitch control motor - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES. North American reported that Lockheed Propulsion Company had successfully completed development testing of the launch escape system pitch control motor..

• Apollo launch escape system with a redundant tower separation device - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES. MSC authorized North American to fit the launch escape system with a redundant tower separation device. This equipment incorporated an explosive bolt and shaped charge cutter..

• ASPO reported that a different type of stainless steel would be used for the Apollo CM heatshield - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  ASPO reported that a different type of stainless steel would be used for the CM heatshield. The previous type proved too brittle at cryogenic temperatures. Aside from their low temperature properties, the two metals were quite; similar and no fabrication problems were anticipated.

• Modifications to the basic Apollo spacecraft to extend capabilities to a 100-day orbital lifetime. - . Nation: USA. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo X. At the request of NASA Hq, MSC contracted with North American to determine what engineering modifications to the basic Apollo spacecraft would be required to extend that vehicle's mission capabilities to a 100-day orbital lifetime.. Additional Details: here....

• Definitive contract for Apollo command and service modules signed - . Nation: USA. Related Persons: Webb. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  NASA Administrator James E. Webb signed the definitive contract with North American for the development of the Apollo CSM. This followed by almost two years North American's selection as prime contractor, The $938.4 million cost-plus-fixed-fee agreement was the most valuable single research and development contract in American history. The contract called for the initial production (i.e., through May 15, 1965) of 11 mockups, 15 boilerplate vehicles, and 11 production articles.

• Mobility tests of the Apollo prototype space suit - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo CSM, CSM Cockpit.

  MSC Crew Systems Division conducted mobility tests of the Apollo prototype space suit inside a mockup of the CM. Technicians also tested the suit on a treadmill. The subjects' carbon dioxide buildup did not exceed two percent; their metabolic rates were about 897,000 joules (850 BTU) per hour at vent pressure, 1,688,000 joules at 2.4 newtons per square centimeter (1,600 BTU at 3.5 psi), and 2,320,000 joules at 3.5 newtons per square centimeter (2,200 BTU at 5.0 psi).

• Mission constraints on the flexibility possible with Apollo lunar launch operations studied - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  John P. Bryant, of the Flight Operations Division's (FOD) Mission Analysis Branch (MAB), reported to FOD that the branch had conducted a rough analysis of the effects of some mission constraints upon the flexibility possible with lunar launch operations. (As a base, MAB used April and May 1968, called "a typical two-month period.") First, Bryant said, MAB used the mission rules demanded for the Apollo lunar landing (e.g., free-return trajectory; predetermined lunar landing sites; and lighting conditions on the moon - "by far the most restrictive of the lot"). Next, MAB included a number of operational constraints, ones "reasonably representative of those expected for a typical flight," but by no means an "exhaustive" list:

  • A minimum daily launch window of three hours.
  • A 26-degree maximum azimuth variation.
  • An earth landing within 40 degrees of the equator.
  • A minimum of three successive daily launch windows.
  • A daylight launch with at least three hours of daylight following liftoff.
  • Transposition and docking in sunlight.
  • Use of but one of the two daily windows available for translunar injection.
  Bryant advised that, taken just by themselves, these various constraints, both mission and operational, had a "restrictive effect" and that operational flexibility was thereby "dramatically curtailed." Moreover, "there are still a number of possible constraints which have not been considered which could still further affect the size of the ultimate launch window" (and the list was "increasing almost daily"): requirements for tracking coverage and for lighting during rendezvous and reentry; and restrictions imposed by solar activity, launch environment, and - no small matter - weather conditions at the launch site.

  "The consequences," Bryant concluded, "of imposing an ever-increasing number of these flight restrictions is obvious - the eventual loss of almost all operational flexibility. The only solution is . . . (a) meticulous examination of every constraint which tends to reduce the number of available launch opportunities," looking toward eliminating "as many as possible."

• Apollo CM ablation heatshield thicknesses for lunar reentry defined - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield. North American defined the maximum, nominal, and minimum CM ablation heatshield thicknesses for lunar reentry. The maximum and minimum limits represented variations that might arise as studies progressed..

• Design of control panel for the Apollo CM was 90 percent complete - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit. MSC reported that design of the control and displays panel for the CM was about 90 percent complete. North American was expected to release the design by September 20. Qualification testing of the panels would begin around December 1..

• Series of water impact tests recommended for the Apollo CM's recovery systems - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute, CSM Recovery.

  MSC Flight Operations Division (FOD) recommended a series of water impact tests to establish confidence in the CM's recovery systems under a variety of operating conditions. FOD suggested several air drops with water landings under various test conditions. Among these were release of the main parachutes at impact, deployment of the postlanding antennas, actuation of the mechanical location aids, and activation of the recovery radio equipment.

• Contract with Kollsman for Apollo CM guidance and navigation optical equipment - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  MSC announced a $7.658 million definitive contract with Kollsman Instrument Corporation for the CM guidance and navigation optical equipment, including a scanning telescope, sextant, map and data viewer, and related ground support equipment. MSC had awarded Kollsman a letter contract on May 28, 1962, and had completed negotiations for the definitive contract on March 29, 1963. "The newly signed contract calls for delivery of all hardware to AC Spark Plug by August 1, 1964."

• Apollo CM boilerplate destroyed during tests - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute.

  At El Centro, Calif., CM boilerplate (BP) 3, a parachute test vehicle, was destroyed during tests simulating the new BP-6 configuration (without strakes or apex cover). Drogue parachute descent, disconnect, and pilot mortar fire appeared normal. However, one pilot parachute was cut by contact with the vehicle and its main parachute did not deploy. Because of harness damage, the remaining two main parachutes failed while reefed. Investigation of the BP-3 failure resulting in rigging and design changes on BP-6 and BP-19.

• Apollo CM to be able to charge the 28-volt portable life support system battery - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo CSM, CSM Cockpit.

  MSC ordered North American to make provisions in the CM to permit charging the 28-volt portable life support system battery from the spacecraft battery charger.

  On the following day, the Center informed North American also that a new mechanical clock timer system would be provided in the CM for indicating elapsed time from liftoff and predicting time to and duration of various events during the mission.

• Gemini, Apollo, and X-20 studied for military space missions. - . Nation: USA. Spacecraft: Apollo CSM, Dynasoar, Gemini, MOL.

  The President's Scientific Advisory Committee requested a briefing from the Air Force on possible military space missions, biomedical experiments to be performed in space, and the capability of Gemini, Apollo, and the X-20 vehicles to execute these requirements.

• Tone warning signal added to the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit. A tone warning signal was added to the CM instrumentation system. If a system malfunctioned, this warning would be heard through both the master caution and warning subsystem and the astronauts' earphones..

• AiResearch awarded contract for the Apollo CM environmental system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS. The AiResearch Manufacturing Company announced that it had been awarded a $20 million definitive contract for the CM environmental system. (AiResearch had been developing the system under a letter contract since 1961..

• Automatic radiator control added to the Apollo CM's environmental control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  North American incorporated an automatic radiator control into the CM's environmental control system to eliminate the need for crew attention during lunar orbit.

  Recent load analysis at North American placed the power required for a 14-day mission at 577 kilowatt-hours, a decrease of about 80 kilowatt-hours from earlier estimates.

• Changes in the Apollo CM's landing requirements - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute, CSM Recovery.

  MSC made several changes in the CM's landing requirements. Impact attenuation would be passive, except for that afforded by the crew couches and the suspension system. The spacecraft would be suspended from the landing parachutes in a pitch attitude that imposed minimum accelerations on the crew. A crushable structure to absorb landing shock was required in the aft equipment bay area.

• Television camera in the Apollo CM modified so that ground personnel could observe the astronauts - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Television.

  MSC advised North American that the television camera in the CM was being modified so that ground personnel could observe the astronauts and flight operations. Television images would be transmitted directly to earth via the Deep Space Instrumentation Facility.

• Qualification testing began on fuel tanks for the service propulsion system (SPS) - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM SPS.

  Qualification testing began on fuel tanks for the service propulsion system (SPS). The first article tested developed a small crack below the bottom weld, which was being investigated, but pressurization caused no expansion of the tank. During mid-October, several tanks underwent proof testing. And, on November 1, the first SPS helium tank was burst-tested.

• Combustion stability in the Apollo service propulsion engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery. ASPO established criteria for combustion stability in the service propulsion engine. The engine had to recover from any instability, whether induced or spontaneous, within 20 milliseconds during qualification testing..

• Apollo weight reduction suggestions - . Nation: USA. Related Persons: Hohmann, Bernhard. Program: Apollo. Spacecraft: Apollo CSM, LM Weight, LM Weight.

  An MSC Spacecraft Technology Division Working Group reexamined Apollo mission requirements and suggested a number of ways to reduce spacecraft weight: eliminate the free-return trajectory; design for slower return times; use the Hohmann descent technique, rather than the equal period orbit method, yet size the tanks for the equal period mode; eliminate the CSM/LEM dual rendezvous capability; reduce the orbital contingency time for the LEM (the period of time during which the LEM could remain in orbit before rendezvousing with the CSM); reduce the LEM lifetime.

• Apollo CM humidity study - . Nation: USA. Program: Apollo. Flight: Mercury MA-9. Spacecraft: Apollo CSM, CSM ECS. Because of an electrical equipment failure on Mercury MA-9, North American began a CM humidity study. . Additional Details: here....

• The second prototype space suit was received by MSC's Crew Systems Division - . Nation: USA. Related Persons: Young. Program: Apollo. Spacecraft: A7L, Apollo CSM, CSM Hatch.

  The second prototype space suit was received by MSC's Crew Systems Division. Preliminary tests showed little improvement in mobility over the first suit. On October 24-25, a space suit mobility demonstration was held at North American. The results showed that the suit had less shoulder mobility than the earlier version, but more lower limb mobility. Astronaut John W. Young, wearing the pressurized suit and a mockup portable life support system (PLSS), attempted an egress through the CM hatch but encountered considerable difficulty. At the same time, tests of the suit-couch- restraint system interfaces and control display layout were begun at the Navy's Aviation Medical Acceleration Laboratory centrifuge in Johnsville, Pa. Major problems were restriction of downward vision by the helmet, extension of the suit elbow arm beyond the couch, and awkward reach patterns to the lower part of the control panel. On October 30-November 1, lunar task studies with the suit were carried out at Wright-Patterson Air Force Base in a KC-135 aircraft at simulated lunar gravity. Mobility tests were made with the suit pressurized and a PLSS attached.

• NASA-Industry Apollo Executives Group - . Nation: USA. Related Persons: Mueller. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  The NASA-Industry Apollo Executives Group, composed of top managers in OMSF and executives of the major Apollo contractors, met for the first time. The group met with George E. Mueller, NASA Associate Administrator for Manned Space Flight, for status briefings and problem discussions. In this manner, NASA sought to make executives personally aware of major problems in the program.

• Marquardt production of reaction control engines for the SM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS.

  The Marquardt Corporation received a definitive $9,353,200 contract from North American for development and production of reaction control engines for the SM. Marquardt, working under a letter contract since April 1962, had delivered the first engine to North American that November.

• Advantages outlined of Apollo CSM's HF transceiver capability - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications.

  MSC Flight Operations Division outlined the advantages inherent in the CSM's capability to use the HF transceiver during earth orbit. The HF transceiver would allow the CSM to communicate with any one tracking station at any time during earth orbit, even when the spacecraft had line-of-sight (LOS) contact with only one or two ground stations in some orbits. It would give the astronauts an additional communications circuit. Most important, this HF capability could alert the network about any trouble in the spacecraft and give the Flight Director more time to make a decision while the spacecraft was out of LOS communication with the ground stations.

• Apollo vibration test system from LTV accepted - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Structural.

  MSC accepted the final items of a $237,000 vibration test system from the LTV Electronics Division to be used in testing spacecraft parts.

  On this same day, MSC awarded a $183,152 contract to Wyle Laboratories to construct a high-intensity acoustic facility, also for testing spacecraft parts. The facility would generate noise that might be encountered in space flight.

• Results of a three-month study on radiation instrumentation - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  North American presented to MSC the results of a three-month study on radiation instrumentation. Three general areas were covered: radio-frequency (RF) warning systems, directional instrumentation, and external environment instrumentation. The company concluded that, with the use of an RE system, astronauts would receive about two hours' notice of any impending solar proton event and could take appropriate action. Proper orientation of the spacecraft could reduce doses by 17 percent, but this could be accomplished only by using a directional detection instrument. There was a 70 percent chance that dosages would exceed safe limits unless such an instrument was used. Consequently North American recommended prompt development.

  Despite the contractor's findings, MSC concluded that there was no need for an RE warning system aboard the spacecraft, believing that radiation warning could be handled more effectively by ground systems. But MSC did concur in the recommendation for a combined proton direction and external environment detection system and authorized North American to proceed with its design and development.

• Apollo Pad Abort Mission 1 - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES, CSM Parachute.

  Apollo Pad Abort Mission I (PA-1), the first off-the-pad abort test of the launch escape system (LES), was conducted at WSMR. PA-1 used CM boilerplate 6 and an LES for this test.

  All sequencing was normal. The tower-jettison motor sent the escape tower into a proper ballistic trajectory. The drogue parachute deployed as programmed, followed by the pilot parachute and main parachutes. The test lasted 165.1 seconds. The postflight investigation disclosed only one significant problem: exhaust impingement that resulted in soot deposits on the CM.

• Test mission - . Nation: USA. Agency: NASA. Apogee: 2.00 km (1.20 mi).

• Drop test to evaluate dual drogue parachute for Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute.

  At El Centro, Calif., a drop test was conducted to evaluate a dual drogue parachute arrangement for the CM. The two drogues functioned satisfactorily. The cargo parachute used for recovery, however, failed to fully inflate, and the vehicle was damaged at impact. This failure was unrelated to the test objectives.

• Meeting reviewed the tower flap versus canard concept for the Apollo earth landing system (ELS) - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute, CSM Recovery.

  A joint North American-MSC meeting reviewed the tower flap versus canard concept for the earth landing system (ELS). During a low-altitude abort, MSC thought, the ELS could be deployed apex forward with a very high probability of mission success by using the tower flap configuration. The parachute system proposed for this mode would be very reliable, even though this was not the most desirable position for deploying parachutes. Dynamic stability of the tower flap configuration during high- altitude aborts required further wind tunnel testing at Ames Research Center. Two basic unknowns in the canard system were deployment reliability, and the probability of the crew's being able to establish the flight direction and trim the CM within its stability limits for a safe reentry. Design areas to be resolved were a simple deployment scheme and a spacecraft system that would give the crew a direction reference.

  MSC directed North American to proceed with the tower flap as its prime effort, and attempt to solve the stability problem at the earliest possible date. MSC's Engineering and Development Directorate resumed its study of both configurations, with an in-depth analysis of the canard system, in case the stability problem on the tower flap could not be solved by the end of the year.

• Emergency impact limits for Apollo spacecraft design - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  ASPO revised the normal and emergency impact limits (20 and 40 g, respectively) to be used as human tolerance criteria for spacecraft design. (These limits superseded those established in the August 14, 1963, North American contract and subsequent correspondence.)

• All production drawings for the Apollo CM ECS released - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  All production drawings for the CM environmental control system were released. - AiResearch Manufacturing Company reported the most critical pacing items were the suit heat exchanger, cyclic accumulator selector valve, and the potable and waste water tanks.

• Eight-day trial of the prototype Apollo diet - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  North American conducted an eight-day trial of the prototype Apollo diet. Three test subjects, who continued their normal activities rather than being confined, were given performance and oxygen consumption tests and lean body mass and body compartment water evaluations. The results showed insignificant changes in weight and physiology.

• Probe and drogue docking concept adopted for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Docking.

  At a meeting of the Apollo Docking Interface Panel, North American recommended and Grumman concurred that the center probe and drogue docking concept be adopted.MSC emphasized that docking systems must not compromise any other subsystem operations nor increase the complexity of emergency operations. In mid-December, MSC/ASPO notified Grumman and North American of its agreement. At the same time, ASPO laid down docking interface ground rules and performance criteria which must be incorporated into the spacecraft specifications.

  There would be two ways for the astronauts to get from one spacecraft to the other. The primary mode involved docking and passage through the transfer tunnel. An emergency method entailed crew and payload transfer through free space. The CSM would take an active part in translunar docking, but both spacecraft must be able to take the primary role in the lunar orbit docking maneuver. A single crewman must be able to carry out the docking maneuver and crew transfer.

• North American final report on extended missions for the Apollo spacecraft. - . Nation: USA. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo X.

  North American issued the final report of its study for MSC on extended missions for the Apollo spacecraft. In stressing the supreme importance of man's role in the exploration of space-and the uncertainties surrounding the effects of prolonged exposure to the zero-gravity environment of space-the company suggested that an Earth-orbital laboratory would be an ideal vehicle for such long-term experimental evaluation, with missions exceeding a year's duration. Additional Details: here....

• Active thermal control system for Apollo SM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Structural.

  MSC reviewed a North American proposal for adding an active thermal control system to the SM to maintain satisfactory temperatures in the propulsion and reaction control engines. The company's scheme involved two water-glycol heat transport loops with appropriate nuclear heaters and radiators. During December, MSC directed North American to begin preliminary design of a system for earth orbit only. Approval for spacecraft intended for lunar missions was deferred pending a comprehensive review of requirements.

• Simulated meteoroid impact tests on the Apollo heatshield - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  Ames Research Center performed simulated meteoroid impact tests on the Avco Corporation heatshield structure. Four targets of ablator bonded to a stainless steel backup structure were tested. The ablator, in a Fiberglas honeycomb matrix, was 4.369 millimeters (0.172 inch) thick in two targets and 17.424 millimeters (0.686 inch) thick in the other two. Each ablator was tested at 116.48 K (-250 degrees F) and at room temperature, with no apparent difference in damage.

  Penetration of the thicker targets was about 13.970 millimeters (0.55 inch). In the thinner targets, the ablator was pierced. Debris tore through the steel honeycomb and produced pinholes on the rear steel sheet. Damage to the ablator was confined to two or three honeycomb cells and there was no cracking or spalling on the surface.

  Tests at Ames of thermal performance of the ablation material under high shear stress yielded favorable preliminary results.

• Design review of the Apollo CSM part-task trainer - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Simulator. A design review of the CSM part-task trainer was held at North American. Briefings included general design criteria and requirements, physical configuration, simulation models, and scheduling. The trainer was expected to be operational in December 1964..

• Apollo SLA was shortened - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. Primarily to save weight, the length of the adapter was shortened to 853 centimeters (336 inches), as recommended by Grumman..

• Operational demands upon Apollo CM from separation to splashdown - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. The MSC Operations Planning Division (OPD) reviewed the operational demands upon the CM from the time of CM-SM separation until splashdown. OPD concluded that the CM should be designed to operate for 45 minutes during this phase of the mission..

• Safety for Apollo of breathing 100 percent oxygen at 5 psi for 30 days proven - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  MSC and the U.S. Air Force Aerospace Medical Division completed a joint manned environmental experiment at Brooks Air Force Base, Tex. After spending a week in a sea-level atmospheric environment, the test subjects breathed 100 percent oxygen at 3.5 newtons per square centimeter (5 psi) at a simulated altitude of 8,230 meters (27,000 feet) for 30 days. They then reentered the test capsule for observation in a sea-level environment for the next five days. This experiment demonstrated that men could live in a 100 percent oxygen environment under these conditions with no apparent ill effects.

• Adequacy of the Apollo CM RCS for automatic reentry - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS. North American completed a study to determine, for automatic modes of reentry, adequacy of the current CM reaction control system (RCS) and compatibility of the RCS with other reentry subsystems..

• Apollo CM environmental control system redesign - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo CSM, CSM ECS.

  MSC directed North American to redesign the CM environmental control system compressor to provide 0.283 cubic meters (10 cubic feet) of air per minute to each space suit at 1.8 newtons per square centimeter (3.5 psi), 16.78 kilograms (37 pounds) per hour total.

• Bioinstrumentation channels to the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  MSC directed North American to assign bioinstrumentation channels to the CM for early manned flights for monitoring the crew's pulse rate, blood pressure, respiration, and temperature. These readings could be obtained simultaneously on any one crew member and by switching from man to man for monitoring the entire crew.

• Feasibility of unmanned Apollo earth orbit mission without a guidance system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery.

  The System Engineering Division (SED) examined the feasibility of performing an unmanned earth orbital mission without the guidance and navigation system. SED concluded that the stabilization and control system could be used as an attitude reference for one to two orbits and would have accuracies at retrofire suitable for recovery. The number of orbits depended upon the number of maneuvers performed by the vehicle, since the gyros tended to drift.

• First three prototype Apollo fuel cells delivered - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Fuel Cell. Pratt and Whitney Aircraft delivered the first three prototype-A fuel cells to North American..

• Three U S Air Force test pilots in a simulated seven- day lunar landing mission - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Simulator.

  Three U. S. Air Force test pilots began a five-week training period at the Martin Company leading to their participation in a simulated seven- day lunar landing mission. This was part of Martin's year-long study of crew performance during simulated Apollo missions (under a $771,000 contract from NASA).

• Spacecraft communications problems - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications.

  At an MSC-North American meeting, spacecraft communications problems were reviewed. Testing had indicated that considerable redesign was essential to ensure equipment operation in a high-humidity environment. Also antenna designs had created several problem areas, such as the scimitar antenna's causing the CM to roll during reentry. The amount of propellant consumed in counteracting this roll exceeded reentry allowances. Further, because the CM could float upside down, the recovery antenna might be pointed at the ocean floor. In fact, many at this meeting doubted whether the overall communications concept was satisfactory "without having detailed ground receiver characteristics." The situation derived from "one of the primary problems in the area of communications system design . . . the lack of functional requirements specifications."

• Apollo crew food could be eaten in a semi-liquid form during emergency pressurized operation - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  ASPO and the Astronaut Office agreed to provide the crew with food that could be eaten in a liquid or semi-liquid form during emergency pressurized operation. This would permit considerable reduction in the diameter of the emergency feeding port in the helmet visor.

• Feasibility of manual maneuver required by the Apollo canard abort system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES.

  MSC's Systems Engineering Division met with a number of astronauts to get their comments on the feasibility of the manual reorientation maneuver required by the canard abort system concept. The astronauts affirmed that they could accomplish the maneuver and that manual control during high-altitude aborts was an acceptable part of a launch escape system design. They pointed out the need to eliminate any possibility of sooting of the windows during normal and abort flight. Although the current design did not preclude such sooting, a contemplated boost protective cover might satisfy this requirement.

• Phase II follow-on extended Apollo system studies. - . Nation: USA. Related Persons: Faget. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo X.

  Following completion of feasibility studies of an extended Apollo system at MSC, Edward Z. Gray, Advanced Manned Missions Program Director at Headquarters, told MSC's Maxime A. Faget, Director of Engineering and Development, to go ahead with phase II follow-on studies. Gray presented guidelines and suggested tasks for such a study, citing his desire for two separate contracts to industry to study the command and service modules and various concepts for laboratory modules.

• First Apollo fuel cell delivered by Pratt and Whitney - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Fuel Cell.

  The first fuel cell module delivered by Pratt and Whitney Aircraft to North American was started and put on load. The module operated normally and all test objectives were accomplished. Total operating time was four hours six minutes, with one hour at each of four loads-20, 30, 40, and 50 amperes. The fuel cell was shut down without incident and approximately 1,500 cubic centimeters (1.6 quarts) of water were collected.

• Plans for testing the Apollo heatshield under reentry conditions - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: FIRE.

  MSC and Bellcomm agreed upon a plan for testing the Apollo heatshield under reentry conditions. Following Project Fire and Scout tests, the Saturn IB would be used to launch standard "all-up" spacecraft into an elliptical orbit; the SM engine would boost the spacecraft's velocity to 8,839 meters

  (29,000 feet) per second. Additional Details: here....

• Equipment stowage location tests in Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Docking.

  Two astronauts took part in tests conducted by North American to evaluate equipment stowage locations in CM mockup 2. Working as a team, the astronauts simulated the removal and storage of docking mechanisms. Preliminary results indicated this equipment could be stowed in the sleeping station. When his suit was deflated, the subject in the left couch could reach, remove, and install the backup controllers if they were stowed in the bulkhead, couch side, or headrest areas. When his suit was pressurized, he had difficulty with the bulkhead and couch side locations. The subject in the center couch, whose suit was pressurized, was unable to be of assistance.

• Design completed of all components of Apollo CM ECS - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS. AiResearch Manufacturing Company reported that it had completed design effort on all components of the CM environmental control system..

• LEM missed rendezvous comm problems - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications, CSM Docking.

  Grumman was studying problems of transmitting data if the LEM missed rendezvous with the CSM after lunar launch. This meant that the LEM had to orbit the moon and a data transmission blackout would occur while the LEM was on the far side of the moon. There were two possible solutions, an onboard data recorder or dual transmission to the CSM and the earth. This redundancy had not previously been planned upon, however.

• Design review of the Apollo CM reaction control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS.

  A design review of the CM reaction control system (RCS) was held. Included was a discussion of possible exposure of the crew to hazardous fumes from propellants if the RCS ruptured at earth impact. For the time being, the RCS design would not be changed, but no manned flights would be conducted until the matter had been satisfactorily resolved. A detailed study would be made on whether to eliminate, reduce, or accept this crew safety hazard.

• Visibility requirements on the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  NASA and North American discussed visibility requirements on the CM and came to the following conclusions: the contractor would provide four portholes in the protective shroud so the astronauts could see through both side and forward viewing windows, and ensure that all windows were clean after launch escape tower separation. North American proposed the addition to Block II CM of a collimated optical device for orientation and alignment during docking. MSC Flight Crew Operations Directorate recommended that mirrors be added to increase external and internal field of vision.

• Contract amendment to North American for buildings for the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. MSC issued a $9.2 million contract amendment to North American for the construction and modification of buildings at Downey, Calif., and for research and development work on the CM..

• Qualification testing of components of the Apollo CM environmental control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS. The AiResearch Manufacturing Company began qualification testing of the first group of components of the CM environmental control system..

• Design review of crew systems checkout for the Apollo CM waste management system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  A design review of crew systems checkout for the CM waste management system was held at North American. As a result, MSC established specific requirements for leakage flow measurement and for checkout at North American and Cape Kennedy. The current capability of the checkout unit restricted it to measuring only gross leakage of segments of the system.

  Further analysis of the management system was necessary to determine changes needed in the checkout unit.

• Honeywell developed an all-attitude display unit for the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  Minneapolis-Honeywell Regulator Company reported it had developed an all-attitude display unit for the CM to monitor the guidance and navigation system and provide backup through the stabilization and control system. The Flight Director Attitude Indicator (or "eight-ball") would give enough information for all spacecraft attitude maneuvers during the entire mission to be executed manually, if necessary.

• Status of the tower flap versus the canard Apollo launch escape vehicle (LEV) configurations - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES.

  Engineers from ASPO and Engineering and Development Directorate (EDD) discussed the current status of the tower flap versus the canard launch escape vehicle (LEV) configurations. Their aim was to select one of the two LEV configurations for Block I spacecraft. ASPO and EDD concluded that the canard was aerodynamically superior; that arguments against the canard, based on sequencing, mechanical complexity, or schedule effect, were not sufficient to override this aerodynamic advantage; and that this configuration should be adopted for Block I spacecraft. However, further analysis was needed to choose the design for the Block II LEV.

• Apollo Block II CSM configuration based on three classes of changes - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  The Block II CSM configuration was based on three classes of changes: mandatory changes necessary to meet the

  1. Functional requirements of the lunar mission.
  2. Manufacturing or fabrication changes (identified only with improved fabrication techniques).
  3. Technically desirable and weight reduction changes.

• Apollo boilerplate (BP) 13 spacecraft delivered - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  Boilerplate (BP) 13 spacecraft was flown from North American, Downey, Calif., to MSC's Florida Operations facility at Cape Kennedy, where the vehicle was inspected and checked out. On April 2, the spacecraft and launch escape system were moved to the pad and mated to the launch vehicle, SA-6. After exhaustive testing, a Flight Readiness Review on May 19 established that BP-13 was ready for launch.

• Apollo SM RCS to have emergency deorbit capability - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS. MSC ordered North American to design the SM's reaction control system with the capability for emergency retrograde from earth orbit..

• Crew transfer tests using a mockup of the Apollo CM/LEM transfer tunnel - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Hatch.

  North American completed its initial phase of crew transfer tests using a mockup of the CM/LEM transfer tunnel. Subjects wearing pressure suits were suspended and counterbalanced in a special torso harness to simulate weightlessness; hatches and docking mechanisms were supported by counterweight devices. The entire tunnel mockup was mounted on an air-bearing, frictionless table. Preliminary results showed that the crew could remove and install the hatches and docking mechanisms fairly easily.

• Apollo potable water system was changed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS. The potable water system was changed to meter both hot and cold water in one-ounce increments to provide accurate measurements for food rehydration. The previous water valve was a full-flow tap..

• Plan for changing the relationship of the Apollo navigation and guidance contractors - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  MSC completed and forwarded to NASA Headquarters a plan for changing the relationship of the navigation and guidance contractors. AC Spark Plug would become the principal contractor, with the Raytheon Company and Kollsman Instrument Corporation as subcontractors. MIT would still have primary responsibility for system design and analysis.

• During a lunar mission, fuel cells in the Apollo CSM would produce 220 liters of potable water - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Fuel Cell. MSC announced that, during a 14-day lunar mission, fuel cells in the Apollo CSM would produce about 220 liters (60 gallons) of potable water while furnishing power to operate the electronic equipment..

• Second Little Joe II launch vehicle delivered - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. General Dynamics Convair delivered to White Sands Missile Range (WSMR) the second Little Joe II launch vehicle, the first Little Joe II scheduled to fly with a production Apollo spacecraft..

• Motorola proposal for the Apollo Unified S-band Test Program - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications.

  Motorola, Inc., submitted a proposal to NASA for the Apollo Unified S-band Test Program, a series of tests on the unified S-band transponder and premodulation processor. Motorola had already begun test plans, analytical studies, and fabrication of special test equipment.

• Apollo tower flap configuration issues - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES. Trajectory analyses by North American indicated that, with the tower flap configuration, it was highly probable that crew acceleration limits would be exceeded during high-altitude abort..

• Dynamic testing of the Apollo docking subsystem - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Docking.

  North American submitted to ASPO a proposal for dynamic testing of the docking subsystem, which called for a full-scale air-supported test vehicle. The contractor estimated the program cost at $2.7 million for facilities, vehicle design, construction, and operation.

• Studies of the dangers of meteoroids and radiation in the Apollo program - . Nation: USA. Related Persons: Mueller. Program: Apollo. Spacecraft: A7L, Apollo CSM, CSM Cockpit.

  George E. Mueller, NASA Associate Administrator for Manned Space Flight, summarized recent studies of the dangers of meteoroids and radiation in the Apollo program. Data from the Explorer XVI satellite and ground observations indicated that meteoroids would not be a major hazard. Clouds of protons ejected by solar flares would present a risk to astronauts, but studies of the largest solar flares recorded since 1959 showed that maximum radiation dosages in the CM and the Apollo space suit would have been far below acceptable limits (set in July 1962 by the Space Science Board of the National Academy of Sciences). Cosmic rays would not be a hazard because of their rarity. Radiation in the Van Allen belts was not dangerous because the spacecraft would fly through the belts at high speeds.

• Apollo earth landings to be primarily on water - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery.

  At a NASA-North American Technical Management Meeting at Downey, Calif., North American recommended that Apollo earth landings be primarily on water. On the basis of analytical studies and impact tests, the contractor had determined that "land impact problems are so severe that they require abandoning this mode as a primary landing mode." In these landings, North American had advised, it was highly probable that the spacecraft's impact limits would be surpassed. In fact, even in water landings "there may be impact damage which would result in leakage of the capsule." (ASPO Manager Joseph F. Shea, at this meeting, "stated that MSC concurs that land impact problems have not been solved, and that planning to utilize water impact is satisfactory."

  Three days later, Shea reported to the MSC Senior Staff that Apollo landings would be primarily on water. The only exceptions, he said, would be pad aborts and emergency landings. With this question of "wet" versus "dry" landing modes settled, Christopher C. Kraft, Jr., Assistant Director for Flight Operations, brought up the unpleasant problem of the CM's having two stable attitudes while afloat - and especially the apex-down one. This upside-down attitude, Kraft emphasized, submerged the vehicle's recovery antennas and posed a very real possibility of flooding in rough seas. Shea countered that these problems could be "put to bed" by using some type of inflatable device to upright the spacecraft.

• Configuration for the Apollo launch escape vehicle - . Nation: USA. Related Persons: Shea. Program: Apollo. Spacecraft: Apollo CSM, CSM LES.

  At a NASA-North American technical management meeting, the tower flap versus canard configuration for the launch escape vehicle was settled. ASPO Manager Joseph F. Shea decided that canards should be the approach for Block I vehicles, with continued study on eliminating this device on Block II vehicles.

• Apollo boilerplate (BP) 19 drop tested - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute.

  Boilerplate (BP) 19 was drop tested at El Centro, Calif., simulating flight conditions and recovery of BP-12. A second BP-19 drop, on April 8, removed all constraints on the BP-12 configuration and earth landing system. Another aim, to obtain information on vehicle dynamics, was not accomplished because of the early firing of a backup drogue parachute.

• Amendments to AC Spark Plug contract for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  MSC and AC Spark Plug negotiated amendments to AC's contract for a research and development program for inertial reference integrating gyroscopes. The amendments covered cost overruns, an additional 30 pieces of hardware, and conversion of the contract to an incentive-fee type (target price, $3.465 million; ceiling price, $3.65 million).

• Mockup of the crew transfer tunnel reviewed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Docking.

  At North American, a mockup of the crew transfer tunnel was reviewed informally. The mockup was configured to the North American-proposed Block II design (in which the tunnel was larger in diameter and shorter in length than on the existing spacecraft). MSC asked the contractor to place an adapter in the tunnel to represent the physical constraints of the current design, which would permit the present design to be thoroughly investigated and to provide a comparison with the Block II proposal.

• Apollo CM ECS component testing completed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS. AiResearch Manufacturing Company completed testing on development components of the CM environmental control system. Specifications for components had been submitted to North American..

• Design review of the Apollo CM heatshield substructure - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  North American held a design review of the CM heatshield substructure. Use of titanium in place of stainless steel was being evaluated as part of a weight reduction study for the Block II spacecraft. Added reliability and a weight saving of several hundred pounds might be achieved thereby. Three factors would be considered: the brittleness of stainless steel at extremely cold temperatures, the higher cost of titanium, and the verification of diffusion bonding of titanium honeycomb.

• First prototype of the Apollo CM reentry battery was delivered - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Electrical. The first prototype of the CM battery for use during reentry was delivered to North American by Eagle-Picher Industries, Inc..

• Apollo CM crew couches fixed except in zero-G flight phases - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit. NASA instructed North American to fix the CM crew couches along all axes during normal and emergency acceleration, except at impact. During nonacceleration mission phases, the couches would be adjustable for crew comfort..

• Hard boost protective cover for Apollo - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES. After the decision to use canards instead of tower flaps, North American returned to the concept of a hard boost protective cover. The tower jettison motor would remove the cover along with the tower..

• Apollo CM couch width studied - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit. MSC Crew Systems Division (CSD) evaluated a CM couch width of 58.4 centimeters (23 inches). CSD found that the couch hampered an astronaut's movement in an unpressurized suit and totally restricted him if his suit was pressurized..

• Breaking the Apollo CM windows for postlanding ventilation - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Hatch, CSM Recovery. Tests at North American demonstrated the possibility of using onboard tools to break the CM hatch windows for postlanding ventilation of the spacecraft..

• Groups of scientists to assist NASA in defining the scientific objectives of Project Apollo - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  NASA's Office of Space Science and Applications began organizing several groups of scientists to assist the agency in defining more specifically the scientific objectives of Project Apollo. In a number of letters to prominent American scientists, Associate Administrator for Space Science and Applications Homer E. Newell asked them to propose suitable experiments in such fields as geology, geophysics, geochemistry, biology, and atmospheric science. This broadly based set of proposals, Newell explained, is "for the purpose of assuring that the final Apollo science program is well balanced, as complete as possible, and that all potential investigators have been given an opportunity to propose experiments." The proposals would then be reviewed by subcommittees of NASA's Space Sciences Steering Committee.

• Narrower hatch configuration for Apollo Block II - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo CSM, CSM Block II.

  To verify a narrower hatch configuration proposed for Block II spacecraft, North American evaluated the capability of an astronaut wearing a pressurized space suit and a portable life support system to pass through the main hatch of the CM for extravehicular activities. Subjects were able to enter and leave the mockup without undue difficulty despite the presence of gravity.

• Because of pure oxygen atmosphere specified, Apollo requirements for component testing reviewed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Electrical.

  Because of the pure oxygen atmosphere specified for the spacecraft, North American reviewed its requirements for component testing. Recent evaluation of the CM circuit breakers had indicated a high probability that they would cause a fire. The company's reliability office recommended more flammability testing, not only on circuit breakers but on the control and display components as well. The reliability people recommended also that procurement specifications be amended to include such testing.

• Apollo CM might not withstand water impact - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Recovery. Impact tests indicated that, because of oscillations and consequent high angles of attack, the CM might not withstand water impact and could sink. North American planned a series of water impact tests using boilerplate 28 to study the problem..

• Apollo mated to Little Joe II launch vehicle - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES. CSM boilerplate 12 (with launch escape system) was mated to its Little Joe II launch vehicle..

• Shea summarized recent activities concerning the Block II spacecraft - . Nation: USA. Related Persons: Maynard, Shea. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  At the April 7-8 NASA-North American Technical Management Meeting (the first of these meetings to be held at MSC's new home, "NASA Clear Lake Site 1"), ASPO Manager Joseph F. Shea summarized his office's recent activities concerning the Block II spacecraft. He spelled out those areas that ASPO was investigating - which included virtually the whole vehicle between escape tower and service engine bell. Shea outlined procedures for "customer and contractor" to work out the definitive Block II design, aiming at a target date of mid-May 1965. These procedures included NASA's giving North American descriptions of its Block II work, estimates of weight reduction, and a set of ground rules for the Block II design. And to ensure that both sides cooperated as closely as possible in this work, Shea named Owen E. Maynard, Chief of MSC's Systems Engineering Division, and his counterpart at Downey, Norman J. Ryker, Jr., to "honcho" the effort.

• Phase I tests of the Apollo SM engine completed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM SPS.

  Firings at the Arnold Engineering Development Center (AEDC) and at Aerojet-General Corporation's Sacramento test site completed Phase I development tests of the SM propulsion engine. The last simulated altitude test at AEDC was a sustained burn of 635 seconds, which demonstrated the engine's capability for long-duration firing. Preliminary data indicated that performance was about three percent below specification, but analysis was in progress to see if it could be improved.

• Dale D Myers named North American's program manager for the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. Dale D. Myers, North American's Space and Information Systems Division vice president, succeeded John W. Paup as the contractor's program manager for the CM..

• Flotation attitude studied for Apollo CM's - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II. ASPO asked North American to investigate the possibility of designing apex-upright, stable flotation attitude into Block I and Block II CM's..

• Apollo changes for Block II - . Nation: USA. Related Persons: Shea. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  Joseph F. Shea, ASPO Manager, in a letter to North American's Apollo Program Manager, summarized MSC's review of the weight status of the Block I and the design changes projected for Block II CSM's.

  The Block II design arose from the need to add docking and crew transfer capability to the CM. Reduction of the CM control weight (from 9,500 to 9,100 kilograms (21,000 to 20,000 pounds)) and deficiencies in several major subsystems added to the scope of the redesign. Additional Details: here....

• Preliminary study on removal of one of three fuel cells from the Block II Apollo CSM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  North American conducted a preliminary study on removal of one of three fuel cells from the Block II CSM. The contractor predicted a total weight saving of about 168 kilograms (370 pounds), with potential indirect reductions in the cryogenic systems, but this change would require a significant increase in reliability.

• Simulations to evaluate Apollo astronauts' ability to perform attitude change maneuvers - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  North American completed the first of a series of simulations to evaluate the astronauts' ability to perform attitude change maneuvers under varying rates and angles. Subjects were tested in a shirtsleeve environment and in vented and pressurized International Latex Corporation state-of-the-art pressure suits. The subjects had considerable difficulty making large, multi-axis attitude corrections because the pressurized suit restricted manipulation of the rotational hand controller.

• Apollo CM heatshield design philosophy modified - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  After completing estimates of the heating conditions for a series of MIT guided reentry trajectories, the MSC Engineering and Development Directorate recommended that the heatshield design philosophy be modified from the current "worst possible entry" to the "worst possible entry using either the primary or backup guidance mode." North American had drawn up the requirements early in 1962, with the intent of providing a heatshield that would not be a constraint on reentry. However, it was now deemed extremely unlikely that an entry, employing either the primary or backup guidance mode, would ever experience the heat loads that the contractor had designed for earlier. The ablator weight savings, using the MIT trajectories, could amount to several hundred pounds.

• Contract with Philco for Apollo spacecraft flight control support - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  NASA definitized the letter contract with the Philco Corporation Techrep Division for spacecraft flight control support. The definitive contract covered the period from September 16, 1963, through March 31, 1965, and the total cost-plus-fixed-fee was $720,624.

• Mockup inspection and review for Block II Apollo CSM - . Nation: USA. Related Persons: Johnson, Caldwell, Slayton. Program: Apollo. Spacecraft: Apollo CSM, CSM Block I.

  At Downey, Calif., MSC and North American officials conducted a mockup review on the Block I CSM. Major items reviewed were:

  • Cabin interior (complete except for hatches, display panel lighting, survival equipment, umbilical connections, and zero-g restraints).
  • CM exterior (complete except for hatches and boost protective cover).
  • Earth landing system.
  • Launch escape system.
  • SM.
  One hundred and eleven request for change forms were submitted to the mockup review board, composed of Robert O. Piland (Chairman), Christopher C. Kraft, Jr., Donald K. Slayton, Caldwell C. Johnson, Owen E. Maynard, and Clinton L. Taylor of MSC; and H. G. Osbon and Charles H. Feltz of North American.

  For the first time, three representative Apollo space suits were used in the CM couches. Pressurized suit demonstrations, with three suited astronauts lying side by side in the couches, showed that the prototype suit shoulders and elbows overlapped and prevented effective operation of the CM displays and controls. Previous tests, using only one suited subject, had indicated that suit mobility was adequate. Gemini suits, tested under the same conditions, proved much more usable. Moreover, using Gemini suits for Apollo earth orbital missions promised a substantial financial saving. As a result of further tests conducted in May, the decision was made to use the Gemini suits for these missions. The existing Apollo space suit contract effort was redirected to concentrate on later Apollo flights. A redesign of the Apollo suit shoulders and elbows also was begun.

• Saturn 6 - . Payload: Apollo CSM Boilerplate 13. Mass: 16,900 kg (37,200 lb). Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft Bus: Apollo. Spacecraft: Apollo CSM, CSM Structural. Decay Date: 1964-06-01 . USAF Sat Cat: 800 . COSPAR: 1964-025A. Apogee: 204 km (126 mi). Perigee: 179 km (111 mi). Inclination: 31.7000 deg. Period: 88.20 min. Apollo Saturn Mission A-101, using CM BP-13 atop SA-6 Saturn I launch vehicle, launched at Cape Kennedy, Fla., to prove spacecraft/launch vehicle compatibility. Boilerplate CSM, LM adapter, LES. LES jettison demonstrated..

• Mandatory changes to Apollo Block I and Block II spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block I, CSM Block II. NASA directed North American Aviation, Inc. (NAA), to make certain mandatory changes to both Block I and Block II spacecraft systems..

• Orbital laboratory using Apollo-developed components for military applications. - . Nation: USA. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo X.

  Commenting on Republican Presidential candidate Barry Goldwater's views on the space program, Warren Burkett, science writer for the Houston Chronicle, observed that a great deal of research being conducted as part of NASA's Apollo program could be of direct value to the military services. Burkett contended that an orbital laboratory using Apollo-developed components could be used for such military applications as patrol and orbital interception. He suggested that, with Apollo, NASA was generating an inventory of 'off-the-shelf' space hardware suitable for military use if needed.

• Apollo X spacecraft to be used in Earth orbit for extended duration biomedical and scientific flights. - . Nation: USA. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo X.

  MSC's Spacecraft Integration Branch proposed an Apollo 'X' spacecraft to be used in Earth orbit for biomedical and scientific missions of extended duration. The spacecraft would consist of the lunar Apollo spacecraft and its systems, with minimum modifications consisting- of redundancies and spares. The concept provided for a first-phase mission which would consider the Apollo 'X' a two-man Earth-orbiting laboratory for a period of 14 to 45 days. The spacecraft would be boosted into a 370-km orbit by a Saturn IB launch vehicle. Additional Details: here....

• Saturn 7 - . Payload: Apollo CSM Boilerplate 15. Mass: 16,700 kg (36,800 lb). Nation: USA. Agency: NASA Houston. Program: Apollo. Class: Moon. Type: Manned lunar spacecraft. Spacecraft Bus: Apollo. Spacecraft: Apollo CSM, CSM Structural. Decay Date: 1964-09-22 . USAF Sat Cat: 883 . COSPAR: 1964-057A. Apogee: 215 km (133 mi). Perigee: 181 km (112 mi). Inclination: 31.7000 deg. Period: 88.50 min. Apollo systems test. Third orbital test. First closed-loop guidance test..

• Formal inspection of Block II Apollo CSM mockup - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II. NAA conducted formal inspection and review of Block II CSM mockup..

• Spring-activated pop-up antenna for the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications. North American switched to a spring-activated pop-up antenna for the command module (CM) high-frequency recovery radio..

• Plan to verify the Apollo CM's radiation shielding - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  MSC's Apollo Spacecraft Program Office (ASPO) approved a plan (put forward by the MSC Advanced Spacecraft Technology Division to verify the CM's radiation shielding. Checkout of the radiation instrumentation would be made during manned earth orbital flights. The spacecraft would then be subjected to a radiation environment during the first two unmanned Saturn V flights. These missions, 501 and 502, with apogees of about 18,520 km (10,000 nm), would verify the shielding. Gamma probe verification, using spacecraft 008, would be performed in Houston during 1966. Only Block I CM's would be used in these ground and flight tests. Radiation shielding would be unaffected by the change to Block II status.

• Two additional Apollo spacecraft checkout ground stations - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. MSC submitted a Request for Proposals to General Electric Company (GE) for two additional spacecraft acceptance checkout ground stations. Eight million dollars was the estimated cost of the added equipment..

• Apollo part task trainers canceled - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Simulator. ASPO notified Grumman and North American that it had canceled requirements for Apollo part task trainers..

• Apollo CM instrument changes recommended - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block I.

  On the basis of reentry simulations, North American recommended several CM instrument changes. An additional reaction control system display was needed, the company reported. Further, the flight attitude and the stabilization and control system indicators must be modified to warn of a system failure before it became catastrophic. The entry monitor system for Block I spacecraft would have to be replaced and the sample g-meter was not wholly satisfactory.

• Block I Apollo CM's heat rejection capability inadequate - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block I. Analysis by MSC of the performance of the environmental control system radiators for Block I CM's placed their heat rejection capability at 4,000 Btus per hr, far below the anticipated mission load of 7,220.. Additional Details: here....

• Electrical power requirements for the guidance and control systems in Block II Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  North American and MIT Instrumentation Laboratory representatives met in Houston to discuss electrical power requirements for the guidance and control systems in Block II CMs. They had determined the additional electrical power needed for the guidance and control system 24 volts was available,

• Qualification testing of the reentry batteries for the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  Eagle-Picher Company completed qualification testing on the 25-amperehour reentry batteries for the CM. Shortly thereafter, Eagle-Picher received authorization from North American to proceed with design and development of the larger 40-ampere-hour batteries needed for the later Block I and all Block II spacecraft.

• First Apollo guidance system shipped - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  In a letter to NASA Administrator James E. Webb, AC Spark Plug reported that the first Apollo guidance system completed acceptance testing and was shipped at 11:30 p.m. and arrived at Downey, California, early the following day. AC reported that in more than 2,000 hours of operation they had found the system to be "remarkably reliable, accurate and simple to operate."

• Apollo guidance and control interfaces - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  The Guidance and Control Implementation Sub-Panel of the MSC-MSFC Flight Mechanics Panel defined the guidance and control interfaces for Block I and II missions. In Block II missions the CSM's guidance system would guide the three stages of the Saturn V vehicle; it would control the S- IVB (third stage) and the CSM while in earth orbit; and it would perform the injection into a lunar trajectory. In all of this, the CSM guidance backed up the Saturn ST-124 platform. Actual sequencing was performed by the Saturn V computer.

• Castings for the Apollo CM data storage equipment to be of aluminum - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Structural.

  Because they were unable to find a satisfactory means of plating the magnesium castings for the CM data storage equipment (to fulfil the one percent salt spray requirement), Collins Radio Company and the Leach Corporation were forced to use aluminum as an alternative. This change would increase the weight of the structure by about 2.3 kg (5 lbs) and, perhaps even more significant, could produce flutter when the recorder was subjected to vibration tests. These potential problems would be pursued when a finished aluminum casting was available.

• Three Apollo fuel cells operated in a simulated space vacuum - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Fuel Cell. Three Pratt and Whitney fuel cells were operated in a simulated space vacuum at North American for 19, 20, and 21 hours. This was the first time three cells were operated as an electrical power generating subsystem..

• Block II Apollo CSM entry monitor subsystem compatibility - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  North American and Honeywell reviewed the Block II CSM entry monitor subsystem's compatibility with the stabilization and control system. The proposed configuration, they found, combined maximum reliability with minimum size and weight and would provide adequate mission performance.

• IBM contract for the Apollo backup computer - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance. MSC and International Business Machines Corporation (IBM) negotiated a $1,500,000 fixed-price contract for the Apollo guidance and navigation system backup computer..

• Supplemental agreement on the Apollo CSM - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM. On October 19, a supplemental agreement in the amount of $115,000,000 was issued to North American, bringing the total funded amount of the CSM contract to $1,136,890,000..

• No lunar mapping or survey capability necessary for Apollo - . Nation: USA. Related Persons: Shea. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo MSS.

  In response to inquiries from General Samuel C. Phillips, Apollo Program Deputy Director, ASPO Manager Joseph F. Shea declared that, for Apollo, no lunar mapping or survey capability was necessary. Shea reported that the Ranger, Surveyor, and Lunar Orbiter programs should give ample information about the moon's surface. For scientific purposes, he said, a simpler photographic system could be included without requiring any significant design changes in the spacecraft.

• Heavy black deposits discovered on the environmental control system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  Heavy black deposits were discovered on the environmental control system (ECS) cold plates when they were removed from boilerplate 14. Several pinholes were found in the cold plate surfaces, and the aluminum lines were severely pitted. This was, as ASPO admitted, a matter of "extreme concern" to the ECS design people at North American, because the equipment had been charged with coolant for only three weeks. This evidence of excessive corrosion reemphasized the drawbacks of using ethylene glycol as a coolant.

• NASA definition studies of the Apollo X spacecraft planned during Fiscal Year 1965. - . Nation: USA. Related Persons: Seamans. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo X.

  In an interview for Missiles and Rockets magazine, Associate Administrator Robert C. Seamans, Jr., stated that NASA planned to initiate program definition studies of an Apollo X spacecraft during Fiscal Year 1965. Seamans emphasized that such a long-duration space station program would not receive funding for actual hardware development until the 1970s. He stressed that NASA's Apollo X would not compete with the Manned Orbiting Laboratory program: 'MOL is important for the military as a method of determining what opportunities there are for men in space. It is not suitable to fulfill NASA requirements to gain scientific knowledge.'

• North American to halt procurement of a Apollo CM simulator - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance.

  MSC ordered North American to halt procurement of a CM simulator. Instead, the company was to begin a simulator program using the two existing evaluator-type CMs in conjunction with the digital-analog computer facility. These evaluators would be used to verify the guidance and navigation and stabilization and control system software, and to analyze crew tasks and failure effects.

• Apollo mission programming - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  ASPO's Operations Planning Division defined the current Apollo mission programming as envisioned by MSC. The overall Apollo flight program was described in terms of its major phases: Little Joe II flights (unmanned Little Joe II development and launch escape vehicle development); Saturn IB flights (unmanned Saturn IB and Block I CSM development, Block I CSM earth orbital operations, unmanned LEM development, and manned Block II CSM/LEM earth orbital operations); and Saturn V flights (unmanned Saturn V and Block II CSM development, manned Block II CSM/LEM earth orbital operations, and manned lunar missions).

• Results of Scout test of the Apollo heatshield material - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  At Langley Research Center, representatives from Langley, MSC, Ames Research Center, Avco Corporation, and North American met to discuss their independent conclusions of the data gathered from the Scout test of the Apollo heatshield material and to determine whether a second test was advisable. Langley's report revealed that: the heatshield materials performed as predicted within the flight condition appropriate to Apollo; the excessive recession rates occurred during flight conditions which were more severe than those considered for the design of the heatshield or expected during Apollo reentries.

  Each group represented had a different interpretation of the reasons for the excessively high surface recession. The conclusion was that a second flight of the heatshield materials on the Scout would not particularly improve the understanding of the material's performance because of the limited variation in reentry trajectory and flight conditions obtainable with the Scout vehicle.

• Problems of bonding the secondary structure to the Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Structural.

  North American conferred with representatives from Shell Chemical Company, Narmco, Epoxylite, and Ablestick on the problems of bonding the secondary structure to the CM. They agreed on improved methods of curing and clamping to strengthen the bond and prevent peeling.

• Frst operational deployment of the launch escape system canards - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES.

  North American conducted the first operational deployment of the launch escape system canards. No problems were encountered with the wiring or the mechanism. Two more operational tests remained to complete the minimum airworthiness test program, a constraint on boilerplate 23.

• Flush-mounted VHF antennas recommended for the Block II Apollo CSM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II. After studying the merits of three flush-mounted versus two scimitar VHF antennas for the Block II CSM, the MSC Instrumentation and Electronics Systems Division recommended the flush-mounted type..

• Portable light assembly for the Apollo CM canceled - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo CSM, CSM Cockpit.

  MSC directed North American to halt development of a portable light assembly for the CM. It was not required, the Center said, because the spaceship's primary lighting system included extendable floodlights. Small lights on the fingertips of the space suit and a flashlight in the survival kit were also available if needed.

• Salt spray test on the Apollo CM television camera's magnesium housing - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Television.

  MSC conducted a week-long salt spray test on the CM television camera's magnesium housing. This was necessitated by similar tests on the Leach data storage structure, which had disclosed the inadequacy of that equipment's nickel plating. The television camera, with its protective coating (AMS 2478, Dow 17 treatment), withstood the ordeal quite well. MSC therefore decided that the magnesium housing was acceptable.

• First drop test of boilerplate 28 - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute.

  North American conducted the first drop test of boilerplate 28 at Downey, Calif. The test simulated the worst conditions that were anticipated in a three-parachute descent and water landing. The second drop, it was expected, would likewise simulate a landing on two parachutes. The drop appeared normal, but the spacecraft sank less than four minutes after hitting the water. Additional Details: here....

• Bellcomm evaluation of the q-ball in the Apollo emergency detection system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES.

  Bellcomm, Inc., presented its evaluation of the requirement for a q-ball in the emergency detection system. (The device, enclosed in the nose cone atop the launch escape tower, measured dynamic pressures and thus monitored the vehicle's angle of attack, and was designed to warn the crew of an impending breakup of the vehicle.) Bellcomm's findings confirmed that the q-ball was absolutely essential and that the device was ideally suited to its task.

• ITTcontract for S-band acquisition receivers for Apollo ground-based dish antennas - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Communications. International Telephone and Telegraph Corporation (ITT) Federal Laboratories' Astrionics Center received a $125,000 contract from Collins Radio for the S-band acquisition receivers that position the ground-based dish antennas toward the spacecraft..

• During 20-g loading test Apollo CM aft heatshield failed - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  During a mechanical loading test (simulating a 20-g reentry) the CM aft heatshield failed at 120 percent of maximum load. Structures and Mechanics Division engineers inspected the structure. They found that the inner skin had buckled, the damage extending three quarters of the way around the bolt circle that secured the heatshield to the spacecraft's inner structure. Their findings would be used along with data from the recent drop of boilerplate 28 to determine what redesign was necessary.

• Flashing light on the Apollo CSM, as an aid for visual rendezvous, not required - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  MSC informed North American that a flashing light on the CSM, as an aid for visual rendezvous, was not required. (A request for some such device had been generated at the Block II mockup review.) Houston's position was based on the current CSM/LEM configuration, which called for rendezvous radar on both spacecraft and the ability of both vehicles to effect the rendezvous using either its own radar or that in the target vehicle.

• Testing of the Apollo breadboard environmental control system discussed - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  Engineers from the MSC Crew Systems Division and from North American discussed testing of the breadboard environmental control system. During all flights - both manned and unmanned - North American must monitor the cabin atmosphere by gas chromatography and mass spectrography. The company should also compare the materials for the breadboard with those for Mercury, Gemini, and other applicable space chambers.

• Apollo guidance and navigation equipment contract amended - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Guidance. NASA and AC Spark Plug amended the company's contract for guidance and navigation equipment. The change embodied an incentive clause, based on a cost-schedule-performance scheme, and placed the estimated cost of the contract at $235,000,000..

• First firing of the service propulsion system engine - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Fuel Cell.

  Joseph G. Thibodaux, Jr., MSC Propulsion and Power Division, reported at an Apollo Engineering and Development technical management meeting that the first J-2 firing of the service propulsion system engine was conducted at White Sands Missile Range (WSMR). Two fuel cell endurance tests of greater than 400 hours were completed at Pratt and Whitney. MSC would receive a single cell for testing during the month.

• Disagreement on number of reentry tests to qualify Apollo CM heatshield - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  There appeared to be some confusion and/or disagreement concerning whether one or two successful Saturn V reentry tests were required to qualify the CM heatshield. A number of documents relating to instrumentation planning for the 501 and 502 flight indicated that two successful reentries would be required. The preliminary mission requirements document indicated that only a single successful reentry trajectory would be necessary. The decision would influence the measurement range capability of some heatshield transducers and the mission planning activity being conducted by the Apollo Trajectory Support Office. The Structures and Mechanics Division had been requested to provide Systems Engineering with its recommendation.

• Apollo boilerplate 28 aft heatshield showed shear failures - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield. More careful examination of the boilerplate 28 aft heatshield indicated that the shear failures were in the face sheet splices which were not in the same locations as the core splices..

• Lump considered for the Apollo CM's blunt face - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  In its search for some method of reducing water impact pressures, North American was considering adding a 15- to 30.5-cm (6- to 12-in) "lump" to the CM's blunt face. The spacecraft manufacturer was also investigating such consequent factors as additional wind tunnel testing, the effect on heatshield design, and impact upon the overall Apollo program.

• Requirements for visual docking aids on both of the Apollo spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Docking.

  MSC defined the requirements for visual docking aids on both of the Apollo spacecraft:

  • At a range of 305 m (1,000 ft), the astronaut must be able to see the passive spacecraft and determine its gross attitude.
  • From 61 m (200 ft) away, he must be able to judge the target's relative attitude and the alignment of his own vehicle.
  • And from this latter distance - and still solely through visual means the pilot must be able to calculate the distance between the two spacecraft and the closing rate.

• Apollo nuclear particle detection system - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit.

  After investigating the maximum radiation levels that were anticipated during Apollo earth orbit missions, North American confirmed the need for some type of nuclear particle detection system (NPDS). Except for periods of extremely high flux rates, the current design of the NPDS was considered adequate. During the same reporting period, North American awarded a contract to Philco to build the system.

• Apollo-Saturn Emergency Detection System Design Sub-Panel - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Electrical.

  The Emergency Detection System (EDS) Design Sub-Panel of the Apollo-Saturn Electrical Systems Integration Panel held its first meeting at North American's Systems and Information Division facility at Downey, Calif. A. Dennett of MSC and W. G. Shields of MSFC co-chaired the meeting.

  Personnel from MSC, MSFC, KSC, OMSF, and North American attended the meeting. Included in the discussions were a review of the EDS design for both the launch vehicle and spacecraft along with related ground support equipment; a review of the differences of design and checkout concepts; and a review of EDS status lights in the spacecraft.

• Displays and keyboards for the Apollo CSM and LEM not compatible - . Nation: USA. Related Persons: Slayton. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II, CSM Cockpit.

  MSC's Assistant Director for Flight Crew Operations, Donald K. Slayton, told the Apollo Program Manager that the current display and keyboard (DSKY) for the Block II CSM and for the LEM were not compatible with existing display panel design of both vehicles from the standpoint of lighting, nomenclature presentation, and caution warning philosophy. In his memorandum, Slayton pointed out mandatory operational requirements of the DSKY to ensure compatibility and consistency with the existing spacecraft display panel design.

  With reference to lighting, he said all numerics should be green, nomenclature and status lights white, and caution lights should be aviation yellow. All panel lighting should be dimmable throughout the entire range of brightness, including off.

  In regard to nomenclature, Slayton pointed out that abbreviations on the DSKY should conform to the North American Interface Control Document (ICD). The referenced ICD was being reviewed by Grumman and North American and was scheduled to be signed December 1, 1964.

  Referring to the caution and warning system, he pointed out that all caution lights on the DSKY should be gated into the primary navigation and guidance system (PNGS) caution light on the main instrument panel of both vehicles and into the PNGS caution light on the lower equipment bay panel of the CM.

  Slayton requested that preliminary designs of the DSKY panel be submitted to the Subsystem Managers for Controls and Displays for review and approval.

• Integrity of the Apollo CM's aft heatshield during water impacts - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  To solve the persisting problem of the integrity of the CM's aft heatshield during water impacts, MSC engineers were investigating several approaches: increasing the thickness of the face sheet (but with no change to the core itself); and replacing the stainless-steel honeycomb with a type of gridwork shell. Technicians felt that, of these two possibilities, the first seemed more efficient structurally.

• Lights on the fingertips of space suits adequate - . Nation: USA. Program: Apollo. Spacecraft: A7L, Apollo CSM, CSM Cockpit.

  MSC determined that the lights on the fingertips of the space suits were adequate to supplement the CM's interior lighting. Thus North American's efforts to develop a portable light in the spacecraft were canceled. The exact requirements for those fingertip lights now had to be defined. The astronauts preferred red bulbs, which would necessitate a redesign of the existing Gemini system. (See October 29-November 5.)

• Container design and stowage of survival kits in the Block II Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  Officials from North American and MSC Crew Systems Division defined the container design and stowage of survival kits in the Block II CM. The equipment would be packed in fabric rucksacks and would be installed in the spacecraft's stowage compartment. (This method eliminated a removable hard container used in the Block I vehicle and would save weight.)

• Formal go-ahead on the Apollo Block II spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II. North American received NASA's formal go-ahead on manufacture of the Block II spacecraft..

• Apollo CSM Configuration Control Panel - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Cockpit. The CSM Configuration Control Panel, at its first meeting, approved several engineering changes. Perhaps the most significant was the substitution of an elapsed time display for the clock on the main display console..

• Preliminaries for the formal Flight Readiness Review of Apollo boilerplate 23 - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute. A "pre-FRR" laid some preliminaries for the formal Flight Readiness Review (ERR) of boilerplate 23 (held at WSMR on December 4, 1964). . Additional Details: here....

• Radiator for the environmental control system in Apollo Block I inadequate - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block I.

  Crew Systems Division (CSD) engineers evaluated the radiator for the environmental control system in Block I CSM's. The division was certain that, because of that item's inadequacy, Block I missions would have to be shortened.

  During the same period, however, the Systems Engineering Division (SED) reported "progress" in solving the radiator problem. SED stated that some "disagreement" existed on the radiator's capability. North American predicted a five-day capability; CSD placed the mission's limit at about two days. SED ordered further testing on the equipment to reconcile this difference.

• Deployment angle of 45 degrees for the Apollo adapter panels - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  The Configuration Control Panel approved a deployment angle of 45 degrees for the adapter panels on Block I flights. North American anticipated no schedule impact. MSC and North American were jointly evaluating the acceptability of this angle for Block II missions as well. A most important consideration was the necessity to communicate via the CM's high-gain antenna during the transposition and docking phase of the flight.

• Serious thermal problem for equipment in the rear of the Apollo SM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield.

  Because of heat from the service propulsion engine (especially during insertion into lunar orbit), a serious thermal problem existed for equipment in the rear of the SM. Reviewing the rendezvous radar's installation, the Guidance and Control Division felt that a heatshield might be needed to protect the equipment. Similar problems might also be encountered with the steerable antenna.

• NASA to furnish VHF transmitter as a telemetry dump for all manned Block I flights - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  MSC informed North American that the Center would furnish a VHF transmitter to serve as a telemetry dump for all manned Block I flights. This would permit wide flexibility in testing the CSM S-band's compatibility with the Manned Space Flight Network prior to Block II missions.

• General Precision's Link Group contract for two Apollo LEM simulators - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Simulator.

  General Precision's Link Group received a $7 million contract from NASA, through a subcontract with Grumman, for two LEM simulators, one at Houston and the other at Cape Kennedy. Along with comparable equipment for the CSM (also being developed by Link), the machines would serve as trainers for Apollo astronauts. The devices would duplicate the interior of the spacecraft; and visual displays would realistically simulate every phase of the mission.

• Acceptance testing completed on three principal systems trainers for the Apollo CSM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  Acceptance testing was completed at Downey, California, on three principal systems trainers for the CSM (the environmental control, stabilization and control, and electrical power systems). The trainers were then shipped to Houston and installed at the site, arriving there December 8. They were constructed under the basic Apollo Spacecraft contract at a cost of $953,024.

• Canard thrusters for the Apollo launch escape system tested - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM LES.

  North American tested the canard thrusters for the launch escape system, using both single and dual cartridges. These tests were to determine whether the pressure of residual gases was sufficient to maintain the canards in a fully deployed position. Investigators found that residual pressures remained fairly constant; further, the firing of a single cartridge produced ample pressure to keep the canards deployed.

• Apollo X missions following completion of Apollo's prime goal of landing on the Moon. - . Nation: USA. Related Persons: Phillips, Samuel, Shea. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo X.

  In a letter to Apollo Program Director Samuel C. Phillips regarding tentative spacecraft development and mission planning schedules, Joseph F. Shea, Apollo Spacecraft Program Manager, touched upon missions following completion of Apollo's prime goal of landing on the Moon. Such missions, Shea said, would in general fall under the heading of a new program (such as Apollo X). Although defining missions a number of years in the future was most complex, Shea advised that MSC was planning to negotiate program package contracts with both North American and Grumman through Fiscal Year 1969, based upon the agency's most recent program planning schedules.

• Plans for mockups of the Block II Apollo CSM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II.

  MSC approved plans put forth by North American for mockups of the Block II CSM. For the crew compartment mockup, the company proposed using the metal shell that had originally been planned as a simulator. Except for the transfer tunnel and lighting, it would be complete, including mockups of all crew equipment. Additional Details: here....

• Design frozen of the Apollo drogue mortar - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute. MSC froze the design of the drogue mortar for the launch escape system. Laboratory qualification was scheduled to begin about the middle of the month. Qualification of the mortars for the pilot parachute would then follow..

• Dumping helium into cabin during an emergency studied - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM ECS.

  Engineering and medical experts of the Crew Systems Division reviewed dumping helium from the CM's gas chromatograph into the cabin during reentry or in a pad abort. Reviewers decided that the resultant atmosphere (9.995 kilonewtons (1.45 psi) helium and 31.349 kilonewtons (4.55 psia) oxygen) posed no hazard for the crew. Systems Engineering Division recommended, however, that dump time be reduced from 15 minutes to three, which could readily be done.

• Rotation angle of the adapter panels set at 45 degrees - . Nation: USA. Program: Apollo. Spacecraft Bus: Apollo CSM. Spacecraft: Apollo CSM.

  MSC ordered North American to fix the rotation angle of the adapter panels at 45 degrees. (This angle should give ample clearance during an SM abort.) Also, so that each panel would have two attenuators, North American should include such a device at each thruster location.

  On the same day, the Center directed North American to put a standard mechanical clock (displaying Greenwich Mean Time) in the lower equipment bay of the CM. (The spacecraft also had an elapsed time device on the main display console.)

• Apollo main parachute drop-tested - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Parachute.

  A single main parachute was drop-tested at El Centro, Calif., to verify the ultimate strength. The parachute was designed for a disreef load of 11,703 kg (25,800 lbs) and a 1.35 safety factor. The test conditions were to achieve a disreef load of 15,876 kg (35,000 lbs. Preliminary information indicated the parachute deployed normally to the reefed shape (78,017 kg (17,200 lbs) force), disreefed after the programmed three seconds, and achieved an inflated load of 16,193 kg (35,700 lbs), after which the canopy failed. Additional Details: here....

• Tooling concepts for the Apollo Block II spacecraft - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Structural.

  The resident Apollo office at North American discussed the company's tooling concepts for the Block II spacecraft with the chief of Marshall's Planning and Tool Engineering Division and the local Marshall representative. These reviewers agreed on the suitability of North American's basic approach. Though they recognized that the initial tooling cost would be high, they nonetheless felt that the total costs of manufacturing would not be appreciably affected. The substitution of mechanical for optical checking devices, it was agreed, would eliminate much of the "judgment factor" from the inspection process; mechanical checking also would assure uniformity of major components or subsystems.

• Positive expulsion tanks for Apollo CSM RCS failed tests - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM RCS. Because of faults in both design and in testing procedures, the positive expulsion tanks for the CSM reaction control system failed their verification tests (begun during the preceding month)..

• Mockup of the food stowage compartment - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Block II. Crew Systems Division received from North American a mockup of the proposed design of the food stowage compartment in the Block II CSM. This article would be used for packaging studies in preparation for the lower equipment bay mockup review in February..

• Flight test instrumentation compatible with heatshield of Apollo CM - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM, CSM Heat Shield. Ames researchers conducted 23 runs in the Center's wind tunnel to confirm the flight test instrumentation's compatibility with the aft heatshield of the CM. The instrumentation performed satisfactorily..