Kosberg Lox/Kerosene rocket engine. 54.520 kN. 8A92 Vostok stage 3, 8K72K stage 3 (block E-Vostok). Out of production. Developed in 15 months. Isp=323s. First flight 1960.
Application: 8A92 Vostok stage 3, 8K72K stage 3 (block E-Vostok).
Engine: 121 kg (266 lb). Chamber Pressure: 50.00 bar. Area Ratio: 79.4. Propellant Formulation: Lox/RG-1. Thrust to Weight Ratio: 45.95.
AKA: RD-448; RO-7; RD-0109; 8D719.
More... - Chronology...
Status: Out of production.
Unfuelled mass: 121 kg (266 lb).
Height: 1.58 m (5.18 ft).
Diameter: 0.76 m (2.49 ft).
Thrust: 54.52 kN (12,257 lbf).
Specific impulse: 324 s.
Burn time: 430 s.
First Launch: 1959-60.
Number: 154 .
Associated Launch Vehicles
Vostok 8K72K Russian orbital launch vehicle. R-7 ICBM with single-engine third stage, uprated from Luna launch vehicle and with forward fairing to accomodate Vostok/Zenit sized spacecraft. 8K72K, used for Vostok manned spacecraft launches and the first Zenit launch attempt. More...
Vostok 8A92 Russian orbital launch vehicle. The 8A92 was a modernized version of the Vostok booster used for launch of Zenit-2 reconnaisance satellites. More...
Vostok 8A92M Russian orbital launch vehicle. Second generation space systems required injection of lighter but higher-altitude Meteor and other satellite payloads into sun-synchronous orbits. The 8A92M version was developed for this purpose. First use was the Meteor launch on 29 June 1977. More...
Associated Manufacturers and Agencies
Kosberg Russian manufacturer of rocket engines. Kosberg Design Bureau, Russia. More...
Lox/Kerosene Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. In January 1953 Rocketdyne commenced the REAP program to develop a number of improvements to the engines being developed for the Navaho and Atlas missiles. Among these was development of a special grade of kerosene suitable for rocket engines. Prior to that any number of rocket propellants derived from petroleum had been used. Goddard had begun with gasoline, and there were experimental engines powered by kerosene, diesel oil, paint thinner, or jet fuel kerosene JP-4 or JP-5. The wide variance in physical properties among fuels of the same class led to the identification of narrow-range petroleum fractions, embodied in 1954 in the standard US kerosene rocket fuel RP-1, covered by Military Specification MIL-R-25576. In Russia, similar specifications were developed for kerosene under the specifications T-1 and RG-1. The Russians also developed a compound of unknown formulation in the 1980's known as 'Sintin', or synthetic kerosene. More...
Burya article, Lavochkin web site.
Haeseler, Dietrich, Visit to the museum of Chemical Automatics Design Bureau, Voronezh 1992 via Dietrich Haeseler.
Glushko, V P, Albom Konstruktsiy ZhRD, Vol. 1 1968, Vol. 3 & 4 1969 via Dietrich Haeseler.
Vostok 8A92-2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 7,775/1,440 kg. Thrust 54.90 kN. Vacuum specific impulse 326 seconds. More...
Vostok 8A92M-2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 8,100/1,100 kg. Thrust 54.52 kN. Vacuum specific impulse 326 seconds. More...
Vostok 8K72K-2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 7,775/1,440 kg. Thrust 54.52 kN. Vacuum specific impulse 326 seconds. More...
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