Orbital launch vehicle. 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:- Godwin, Robert, editor, Dyna-Soar: Hypersonic Strategic Weapons System, Collector's Guide Publishing, Ontario, Canada, 2003..