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Hyperion SSTO
Hyperion SSTO - Hyperion SSTO Launch Vehicle

Credit: © Mark Wade. 3,013 bytes. 183 x 352 pixels.



Family: VTOVL. Country: USA. Status: Study 1968.

Yet another of Philip Bono's single-stage-to-orbit designs of the 1960's, using a plug-nozzle engine for ascent and as a re-entry heat shield. Hyperion would have taken 18,100 kg of payload or 110 passengers to orbit or on 45 minute flights to any point on earth. Hyperion used a sled for launch, which would have seriously hurt its utility. The sled gave a 300 m/s boost to the vehicle before it ascended to orbit. The sled would have 3 km of straight course, followed by 1 km up a mountainside, with a 3 G acceleration.


Specifications

LEO Payload: 18,100 kg. to: 185 km Orbit. at: 28.0 degrees. Liftoff Thrust: 628,000 kgf. Total Mass: 470,000 kg. Core Diameter: 16.0 m. Total Length: 31.0 m. Development Cost $: 1,500.00 million. in 1968 average dollars. Launch Price $: 0.33 million. in 1968 price dollars. Flyaway Unit Cost $: 40.00 million. in 1968 unit dollars. Cost comments: Costs are those indicated by Bono. For this reason he felt rocket-powered intercontinental transport was competitive with SST's or aircraft.



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