Isayev R-17

Designer: Isayev. Developed in: 1958-64. Application: R-17. Propellants: Nitric acid/Kerosene. Thrust(vac): 131.200 kN (29,495 lbf). Thrust(sl): 131.210 kN (29,497 lbf). Mass Engine: 120 kg (260 lb). Diameter: 0.77 m (2.52 ft). Length: 1.49 m (4.88 ft). Chambers: 1. Thrust to Weight Ratio: 111.49. Country: Russia. Status: Out of production. First Flight: 1961. Last Flight: 2004. Flown: 15.

Designation unknown.

Isayev R-17 used on Rocket Stages

Used on stage: R-17. on launch vehicle: R-17.

Used on stage: R-17. on launch vehicle: Tamouz.

Used on stage: R-17. on launch vehicle: Tamouz.

Used on stage: R-17. on launch vehicle: Tamouz.

Bibliography and Further Reading

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 Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.

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

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