Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9 A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z Soyuz-U  Soyuz LV Credit: NASA AKA: 11A511U;A-2;Sapwood;SL-4;Soyuz;Soyuz 11A511U. Status: Active. First Launch: 1973-05-18. Last Launch: 2017-02-22. Number: 442 . Payload: 7,200 kg (15,800 lb). Thrust: 4,030.00 kN (905,980 lbf). Gross mass: 310,000 kg (680,000 lb). Height: 50.67 m (166.24 ft). Diameter: 2.95 m (9.67 ft). Apogee: 200 km (120 mi). Soyuz-U was a standardized, modernized version of the R-7 launch vehicle with higher performance first and second stage engines. Improvements were made to the launch complexes, including unified test-launch ground support equipment. The booster was first used for the Apollo-Soyuz launches. Military applications included Zenit and Yantar military reconnaissance satellites. Soyuz 11A511U used chilled higher density fuel in the core stage to improve payload. This became the most-widely used version, launching a range of military and manned spacecraft for over thirty years. Starsem Official Description Considered in Russian terminology to be a three-stage vehicle, Soyuz is composed of a lower portion consisting of four boosters (first stage) and a central core stage (second stage); and an upper portion, composed of a third stage, payload adapter and fairings. Liquid oxygen and kerosene are used as propellants for the complete Soyuz launch vehicle. The four first stage boosters are assembled laterally around the second stage central core. The boosters are identical and cylindrical-conic in shape -- with the oxygen tank in the upper cone-shaped portion and the kerosene tank in the lower cylindrical portion. Ignition of the boosters and second stage central core occur simultaneously on the ground. When the boosters have completed their powered flight during ascent, they are separated and the core second stage continues to function. The boosters' NPO Energomash RD-107 engines have four main chambers and a set of two gimbaled vernier thrusters. Three-axis flight control is ensured by the four sets of vernier thrusters. The RD 107 engines' main chambers, like the vernier thrusters, are fed by a turbopump, which is powered by gasses generated from the catalytic decomposition of hydrogen peroxide in a gas generator. A pyrotechnic ignition switch provides ignition for the RD-107 engines. Booster separation occurs when the predefined velocity is reached, and occurs at about 118 seconds after lift-off. An NPO Energomash RD 108 engine powers the Soyuz second stage. This engine differs from those of the boosters by the presence of four vernier thrusters, which are necessary for three-axis flight control after booster separation. An equipment bay located on top of the second stage operates during the entire flight of the first stage-second stages. The third stage is linked to the second stage by a latticework structure. When the second stage's powered flight is complete, the third stage engine is ignited. Separation of the two stages occurs by the direct ignition forces of the third stage engine. A single-turbopump RD 0110 engine from KB KhA powers the Soyuz third stage. It is fuelled by gases coming from the combustion of propellants through a generator. At the turbine exit, the gases are recovered to feed four vernier thrusters to ensure three-axis flight control. The third stage engine is fired for about 240 seconds, and cut-off occurs when the calculated velocity increment is reached. The upper section with payload is separated by springs. The third stage then performs an avoidance maneuver by opening an outgassing valve in the liquid oxygen tank. Soyuz launcher tracking and telemetry is provided through systems in the second and third stages. These two stages have their own radar transponder systems for ground tracking. Individual telemetry transmitters are in each stage. Launcher health status is downlinked to ground stations along the flight path. Telemetry and tracking data are transmitted to the TsUP mission control center near Moscow, where the incoming data flow is recorded. Partial real-time data processing and plotting is performed for flight following and initial performance assessment. All flight data is analyzed and documented within a few hours after launch.
LEO Payload: 7,200 kg (15,800 lb) to a 200 km orbit at 51.60 degrees. Payload: 6,220 kg (13,710 lb) to a 240 km 51.8 deg orbit. Launch Price $: 40.000 million in 1999 dollars. Stage Data - Soyuz 11A511U
More at: Soyuz-U. Family: orbital launch vehicle. Country: Russia. Engines: RD-0110, RD-107-11D511, RD-108-11D512. Spacecraft: Oscar, Nauka, Zenit-2M satellite, Zenit-4MK, Zenit-4MT, Energia satellite, Soyuz 7K-T, Bion, Soyuz 7K-TM, Yantar-2K, Soyuz 7K-T/A9, Soyuz 7K-S, Zenit-4MKT, Soyuz 7K-MF6, Zenit-6U, Zenit-4MKM, Salyut 6, Progress, Soyuz T, Yantar-4K1, KRT-10, Resurs F1-17F41, Yantar-1KFT, Salyut 7, Astrozond, Yantar-4KS1, Efir, Zenit-8, ISS, Foton, Mir, Soyuz TM, Resurs F1-14F40, Resurs F2, Resurs F1-14F43, Pion, Orlets-1, Progress M, GFZ-1, AMOS, Inspector, PS Model, Mirka, YES, Resurs F1M, Globalstar, Yamal, Progress M1, IRDT, Cluster 2, Progress M-SO, Soyuz TMA, Nanosputnik. Projects: ASTP, Orlets, Resurs, Salyut. Launch Sites: Baikonur, Baikonur LC1, Plesetsk, Baikonur LC31, Plesetsk LC41/1, Plesetsk LC43/4, Plesetsk LC43/3, Plesetsk LC16/2. Stages: Soyuz 11A511U2-2, Molniya 8K78M-0, Molniya 8K78M-1. Agency: Korolev bureau.
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