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OOST ISI
Part of Bono Family
American SSTO orbital launch vehicle. Alternate version of OOST using Improved Specific Impulse approach: many engines feeding into single large nozzle.

AKA: One stage Orbital Space Truck. Status: Study 1963. Payload: 454,500 kg (1,002,000 lb). Thrust: 68,496.90 kN (15,398,716 lbf). Gross mass: 5,670,400 kg (12,501,000 lb). Height: 69.00 m (226.00 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$: 117.600 million.

Stage Data - OOST ISI

  • Stage 1. 1 x OOST ISI. Gross Mass: 5,125,000 kg (11,298,000 lb). Empty Mass: 292,000 kg (643,000 lb). Thrust (vac): 85,386.000 kN (19,195,536 lbf). Isp: 455 sec. Burn time: 248 sec. Isp(sl): 365 sec. Diameter: 21.30 m (69.80 ft). Span: 21.30 m (69.80 ft). Length: 57.90 m (189.90 ft). Propellants: Lox/LH2. No Engines: 15. Engine: Chamber/single nozzle. Status: Study 1963.

Family: orbital launch vehicle, SSTO. Country: USA. Engines: Chamber/single nozzle. Stages: OOST ISI stage. Agency: Douglas.



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