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S2.720
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Other Designations: S2.720. Designer: Isayev. Application: Engine for SAM-missile V-755. Propellants: Nitric acid/Amine. Thrust(vac): 34.300 kN (7,711 lbf). Thrust(sl): 34.300 kN (7,711 lbf). Isp (sea level): 233 sec. Burn time: 55 sec. Mass Engine: 48 kg (105 lb). Diameter: 0.48 m (1.56 ft). Length: 0.95 m (3.10 ft). Chambers: 1. Chamber Pressure: 64.00 bar. Oxidizer to Fuel Ratio: 3.23. Thrust to Weight Ratio: 73.64. Country: Russia. Status: Out of Production. Pump-fed engine. Used in engine unit of a special apparatus. Pump-fed engine. 20,4 kN sea level.
Bibliography and Further Reading - Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...
- Kudryavtsev, V M, et.al., Osnovy Teorii i Rascheta, Moscow, Vysshaya Shkola, 1993 via Dietrich Haeseler. ISBN: 5060025624. Russian-language textbook on rocket theory; contains some information on Russian rocket engines. More at amazon.com...
- Shirokorad, A, Rakety nad Morem, Second Edition, Tekhnika I Vooruzhenie, Moscow 11-12, 1997 via Dietrich Haeseler.
- Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
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