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R-3A
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Gross Mass: 19,900 kg (43,800 lb). Empty Mass: 3,500 kg (7,700 lb). Thrust (vac): 434.400 kN (97,657 lbf). Isp: 235 sec. Burn time: 83 sec. Propellants: Lox/Alcohol. Isp(sl): 210 sec. Diameter: 1.65 m (5.42 ft). Span: 3.50 m (11.40 ft). Length: 20.00 m (65.00 ft). Country: Russia. No Engines: 1. Engine: RD-102. Status: Development ended 1951. Further incremental upgrade of R-2. Payload 500 kg. Range 935 km. Developed from 1949 to October 1951. Cancelled, work combined with 8K14 development.
Used on Launch Vehicles:
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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