Encyclopedia Astronautica 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 Rook engine AKA: Rook; Rook II; Rook IIIA; Rook IIIB. Status: Out of production. Date: 1960. Number: 1 . Thrust: 300.00 kN (67,440 lbf). Gross mass: 1,057 kg (2,330 lb). Unfuelled mass: 186 kg (410 lb). Burn time: 5.50 s. Diameter: 0.44 m (1.44 ft). The Rook motor was 0.43 m in diameter and 5.28 m long. It contained a case-bonded charge of 846 kg of non-aluminized plastic propellant giving a total impulse of 1760 kN-seconds in 5.6 seconds; with a maximum thrust of 323 kN and a specific impulse of 213 seconds. The motor was capable of withstanding the 40g acceleration it provided during firing. It was employed as the first propulsion stage of the Leopard and Jaguar (Jabiru) supersonic test vehicles, and by itself in single-stage test applications. Thrust (sl): 313.000 kN (70,365 lbf).
Country: UK. Launch Vehicles: Rook, Leopard, Jaguar 1, RAF Jaguar, Jaguar 2, Rook IIIA, Jabiru 2, Jabiru 3. Propellants: Solid. Stages: Rook engine. Agency: RO, Royal Ordnance. Bibliography: 572. 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 � 1997-2016 Mark Wade - Contact � / Conditions for Use |
