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|Rombus SSTO - Rombus SSTO Launch Vehicle|
Credit: © Mark Wade. 3,380 bytes. 215 x 438 pixels.
Family: VTOVL. Country: USA. Status: Study 1965. Other Designations: Reusable Orbital Module-Booster & Utility Shuttle.
Bono original design for ballistic single-stage-to-orbit (not quite - it dropped liquid hydrogen tanks on the way up) heavy lift launch vehicle. The recoverable vehicle would re-enter, using its actively-cooled plug nozzle as a heat shield.
LEO Payload: 450,000 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 8,134,200 kgf. Total Mass: 6,363,000 kg. Core Diameter: 24.0 m. Total Length: 29.0 m. Launch Price $: 25.00 million. in 1965 price dollars. Cost comments: Reflight price -$ 25 per pound - after twenty flights. Bono expected the cost per flight to drop to $ 10 per pound ($ 10 million per flight) after 100 re-uses!.
- Stage Number: 0. 8 x Rombus Tank Gross Mass: 110,544 kg. Empty Mass: 14,172 kg. Thrust (vac): 0 kgf. Isp: 459 sec. Burn time: 130 sec. Isp(sl): 359 sec. Diameter: 7.6 m. Span: 7.6 m. Length: 30.5 m. Propellants: Lox/LH2 No Engines: 0. None
- Stage Number: 1. 1 x Rombus Gross Mass: 5,102,041 kg. Empty Mass: 226,757 kg. Thrust (vac): 10,400,000 kgf. Isp: 459 sec. Burn time: 215 sec. Isp(sl): 359 sec. Diameter: 16.0 m. Span: 24.4 m. Length: 29.0 m. Propellants: Lox/LH2 No Engines: 1. Plug-Nozzle Rombus
- 36 - Gatland, Kenneth and Bono, Philip, Frontiers of Space, Macmillan, New York, 1969.
|Rombus SSTO - Rombus SSTO Launch Vehicle Cutaway|
Credit: © Mark Wade. 5,202 bytes. 417 x 440 pixels.
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Last update 12 March 2001.
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