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.)

Bibliography and Further Reading

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. Asif Siddiqi presents material that could not be fit into his monumental 'Challenge to Apollo'. Accessed at: http://home.earthlink.net/~cliched/main_space.html.

Russian Space Industry, Federation of American Scentists Web Pages, 1998 via Dietrich Haeseler. Accessed at: http://www.fas.org/spp/civil/russia/.

Contact us with any corrections, additions, or comments.

Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.

© Mark Wade, 1997 - 2007 except where otherwise noted.

Encyclopedia Astronautica
topic index
0 - A - B - C - D - E - F - G - H - I - J - K - L - M - N - O - P - Q - Ra - Re - Sa - Sf - Sp - T - U - V - W - X - Y - Z