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R-3A stage
Part of A-4 Family
LOx/Alcohol propellant rocket stage. Further incremental upgrade of R-2. Payload 500 kg. Range 935 km. Developed from 1949 to October 1951. Cancelled, work combined with 8K14 development.

AKA: R-3A. Status: Development ended 1951. Thrust: 434.40 kN (97,657 lbf). Gross mass: 19,900 kg (43,800 lb). Unfuelled mass: 3,500 kg (7,700 lb). Specific impulse: 235 s. Specific impulse sea level: 210 s. Burn time: 83 s. Height: 20.00 m (65.00 ft). Diameter: 1.65 m (5.42 ft). Span: 3.50 m (11.40 ft).



Country: Russia. Engines: RD-102. Launch Vehicles: R-3A. Propellants: Lox/Alcohol.

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