Engine Model: S2.713. Other Designations: S2.713. Designer: Isayev. Developed in: 1956-61. Application: R-13 (SS-N-4). Propellants: Nitric acid/Amine. Thrust(vac): 252.200 kN (56,697 lbf). Chambers: 1 + 4. Oxidizer to Fuel Ratio: 3.48. Country: Russia. Status: Out of Production. First engine to employ gas generator on main propellants. One main and four vernier thrusters. (Mixture derived ratio from tank content.)
S2.713 used on Rocket Stages
- Used on stage: R-13. on launch vehicle: R-13.
Bibliography:- Russian Space Industry, Federation of American Scentists Web Pages, 1998 via Dietrich Haeseler. Web Address when accessed: http://www.fas.org/spp/civil/russia/.
- Shirokorad, A, Rakety nad Morem, Second Edition, Tekhnika I Vooruzhenie, Moscow 11-12, 1997 via Dietrich Haeseler.
- Siddiqi, Asif A, Soviet Space Web Page, 1999 via Dietrich Haeseler. Web Address when accessed: http://home.earthlink.net/~cliched/main_space.html.