NPO Enerogmash Museum, November 1992
Credit: © Dietrich Haeseler
AKA: 8D21. Status: Developed 1965-77. Date: 1965-77. Thrust: 96.67 kN (21,732 lbf). Unfuelled mass: 183 kg (403 lb). Specific impulse: 400 s. Burn time: 750 s. Height: 1.89 m (6.20 ft). Diameter: 0.98 m (3.21 ft).
Engine: 183 kg (403 lb). Chamber Pressure: 117.60 bar. Area Ratio: 108.7. Thrust to Weight Ratio: 54.6448087431694. Oxidizer to Fuel Ratio: 2.7. Coefficient of Thrust vacuum: 1.14369823635204. Coefficient of Thrust sea level: .25.
|RD-302 Glushko exotic LF2/Ammonia rocket engine. Developed 1960-69. Successor to RD-303 and predecessor to RD-301. Staged combustion cycle.|
|RD-303 Glushko exotic LF2/Ammonia rocket engine. Developed 1960-65. Predecessor to RD-302 and RD-301.|
|RD-502 Glushko H2O2/Pentaborane rocket engine. Experimental upper stage engine. Developed 1960-66. Experimental upper stage engine. Program stopped due to toxicity of propellants. Intended for Proton upper stage. First flight 1966.|
|RD-350 Glushko exotic LF2/LH2 rocket engine. Design concept 1963-. Studied by Glushko as engine concept with high-energy propellants.|
|RD-550 Glushko exotic rocket engine. Experimental upper stage engine. Developed 1963-70. Propellants LOx/30% Beryllium+Pentaborane in 70% Hydrazine.|