Encyclopedia Astronautica

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

LEO Payload: 454,500 kg (1,002,000 lb) to a 325 km orbit in 1985 dollars. Flyaway Unit Cost $: 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.

AKA: One stage Orbital Space Truck.
Status: Study 1963.
Gross mass: 5,670,400 kg (12,501,000 lb).
Payload: 454,500 kg (1,002,000 lb).
Height: 69.00 m (226.00 ft).
Diameter: 21.30 m (69.80 ft).
Thrust: 68,496.90 kN (15,398,716 lbf).
Apogee: 325 km (201 mi).

More... - Chronology...

Associated Countries
Associated Engines
  • Chamber/single nozzle Notional lox/lh2 rocket engine. 13,231 kN. Study 1963. Isp=455s. Before moving to favored plug nozzle designs, Bono at Douglas considered having multiple combustion chambers exhaust into a single large nozzle to obtained Improved Specific Impulse. More...

See also
  • OOST Bono's earliest design for an expendable single-stage-to-orbit LH2/Lox booster. The baseline version used conventional engines. More...
  • SSTO Category of launch vehicles. Single Stage To Orbit. More...
  • VTOVL The concept of a reusable single-stage-to-orbit Vertical Take-Off Vertical Landing (VTOVL) launch vehicle that would reenter and return to its launch site for turnaround and relaunch was first proposed by Philip Bono in the 1960's. The appealing simplicity of the concept has been offset by the technological risk in developing it. The problem with any single-stage-to-orbit concept is that if the empty weight of the final vehicle has been underestimated it will not be able to deliver any payload to orbit, or even reach orbit. Since weight growth of up to 20% is not unknown in aerospace projects, this is a very real threat which has made both NASA and private investors reluctant to invest the billions of dollars it would take to develop a full-scale flight vehicle. More...

Associated Manufacturers and Agencies
  • Douglas American manufacturer of rockets, spacecraft, and rocket engines. Boeing Huntington Beach, Huntington Beach, CA, USA. More...

Associated Stages
  • OOST ISI Lox/LH2 propellant rocket stage. Loaded/empty mass 5,125,000/292,000 kg. Thrust 85,386.00 kN. Vacuum specific impulse 455 seconds. More...

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