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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 ROOST ISI Part of Bono
ROOST Improved
ROOST Improved Specific Impulse
Credit: © Mark Wade American SSTO orbital launch vehicle. Bono's first design for a reusable single stage to orbit LH2/LOx booster, using Improved Specific Impulse approach: many engines feeding into single large nozzle.
AKA: Reusable One stage Orbital Space Truck. Status: Study 1963. Payload: 454,500 kg (1,002,000 lb). Thrust: 81,697.40 kN (18,366,306 lbf). Gross mass: 6,763,400 kg (14,910,700 lb). Height: 81.00 m (265.00 ft). Diameter: 21.30 m (69.80 ft). Apogee: 325 km (201 mi).
LEO Payload: 454,500 kg (1,002,000 lb) to a 325 km orbit. Flyaway Unit Cost 1985$: 154.000 million.
Stage Data - ROOST ISI
- Stage 1. 1 x ROOST ISI. Gross Mass: 6,218,000 kg (13,708,000 lb). Empty Mass: 435,000 kg (959,000 lb). Thrust (vac): 101,842.000 kN (22,894,992 lbf). Isp: 455 sec. Burn time: 249 sec. Isp(sl): 365 sec. Diameter: 21.30 m (69.80 ft). Span: 21.30 m (69.80 ft). Length: 67.10 m (220.10 ft). Propellants: Lox/LH2. No Engines: 18. Engine: Chamber/single nozzle. Status: Study 1963.
Family: orbital launch vehicle, SSTO. Country: USA. Engines: Chamber/single nozzle. Stages: ROOST ISI stage. Agency: Douglas. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
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