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astronautix.com S2.713


Other Designations: S2.713. Designer: Isayev. Developed in: 1956-61. Application: R-13 (SS-N-4). Propellants: Nitric acid/Amine Thrust(vac): 25,717 kgf. Thrust(vac): 252.20 kN. Chambers: 1 + 4. Oxidizer to Fuel Ratio: 3.48. Country: Russia. Status: Out of Production. References: 319 , 340 , 344 . Comments: First engine to employ gas generator on main propellants. One main and four vernier thrusters. (Mixture derived ratio from tank content.).
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Last update 12 March 2001.
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