Isayev Nitric acid/Kerosene rocket engine. 131.2 kN. R-17. Out of production. Designation unknown. First flight 1961.
Thrust (sl): 131.210 kN (29,497 lbf). Thrust (sl): 13,380 kgf. Engine: 120 kg (260 lb). Propellant Formulation: AK27I/TM185. Thrust to Weight Ratio: 111.49.
Status: Out of production.
More... - Chronology...
Unfuelled mass: 120 kg (260 lb).
Height: 1.49 m (4.88 ft).
Diameter: 0.77 m (2.52 ft).
Thrust: 131.20 kN (29,495 lbf).
First Launch: 1958-64.
Number: 15 .
Associated Launch Vehicles
R-17 Russian short-range ballistic missile. The final refinement of the R-11 design, the R-17, was exported widely and became infamous around the world by its ASCC reporting name - "Scud". It was perhaps the most famous ballistic missile of the post-war period due to its use in the Iran-Iraq 'War of the Cities' and the Gulf War. This was the definitive production version of what was essentially a storable-propellant rocket with the performance of the V-2. The original design was by Makeyev but the missile itself was produced by the Votkinsk Machine Building Plant. More...
Associated Manufacturers and Agencies
Nitric acid/Kerosene Drawing on the German World War II Wasserfall rocket, nitric acid (HNO3) became the early storable oxidiser of choice for missiles and upper stages of the 1950's. To overcome various problems with its use, it was necessary to combine the nitric acid with N2O4 and passivation compounds. These formulae were considered extremely secret at the time. By the late 1950's it was apparent that N2O4 by itself was a better oxidiser. Therefore nitric acid was almost entirely replaced by pure N2O4 in storable liquid fuel rocket engines developed after 1960. Rocket propellant RP-1, or its foreign equivalents, is a straight-run kerosene fraction, which is subjected to further treatment, i.e., acid washing, sulphur dioxide extraction. Thus, unsaturated substances which polymerise in storage are removed, as are sulphur-containing hydrocarbons. More...
Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
Siddiqi, Asif A, Soviet Space Web Page, 1999 via Dietrich Haeseler. Web Address when accessed: here.
R-17 Nitric acid/Kerosene propellant rocket stage. Loaded/empty mass 5,385/1,645 kg. Thrust 93.10 kN. Vacuum specific impulse 251 seconds. Developed from Russian storable fuel tactical missile. Original R-11 designed by Korolev OKB, subsequent developments by Makeyev OKB. Using calculations of Gerald Bull, stretched and clustered as basis of Iraqi ICBM/satellite launch vehicle. More...
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