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Engine Model: S2.720. 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:

  • Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
  • Kudryavtsev, V M, et.al., Osnovy Teorii i Rascheta, Moscow, Vysshaya Shkola, 1993 via Dietrich Haeseler.
  • 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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