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Orbital launch vehicle. Year: 1959. Country: USA. Status: Study 1961. A two-stage all-Lox/LH2 vehicle proposed for the USAF SLV-4 requirement. Ruled out because it did not use the large segmented solids then favored by the USAF and its think tanks. The design apparently used five J-2 engines in the first stage, and a single J-2 in the second stage. Manufacturer: Convair. LEO Payload: 7,300 kg (16,000 lb). to: 480 km Orbit. at: 28.00 degrees. Associated Spacecraft: Dynasoar. Total Mass: 278,290 kg (613,520 lb). Core Diameter: 5.08 m (16.66 ft). Total Length: 47.00 m (154.00 ft). Span: 13.50 m (44.20 ft).
Bibliography and Further Reading - Godwin, Robert, editor, Dyna-Soar: Hypersonic Strategic Weapons System, Collector's Guide Publishing, Ontario, Canada, 2003.. ISBN: 1896522955. Collection of contemporary documents covering the development and death of Dyna-Soar, as well as a DVD with video of promotional films and systems tests. More at amazon.com...
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