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
OOST ISI
Part of Bono
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.
Back to top of page
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
© 1997-2019 Mark Wade - Contact
© / Conditions for Use