Yuzhnoye N2O4/UDMH rocket engine. 77.630 kN. Tsyklon 2 and 3 stage 3; Ikar. Developed 2005. Isp=330s. High pressure fuel was used to gimbal the engine in two planes, replacing four thrust vector engines on the basic RD-861.
An improved version of the RD-861 engine first described in a 2005 brochure. High pressure fuel was used to gimbal the engine in two planes, replacing the four thrust vector engines of earlier models. Mass of the engine increased, but specific impulse was increased by 15.6 s; the number of restarts in flight was increased to three; and the burn time was tripled. The mixture ratio was controlled with an accuracy of ±1.0%.
Application: Tsyklon 2 and 3 stage 3; Ikar.
Engine: 194 kg (427 lb). Oxidizer to Fuel Ratio: 2.41. Restarts: 3.
Status: Developed 2005.
More... - Chronology...
Height: 1.56 m (5.11 ft).
Diameter: 1.53 m (5.01 ft).
Thrust: 77.63 kN (17,452 lbf).
Specific impulse: 330 s.
Burn time: 370 s.
First Launch: 2003.
Associated Launch Vehicles
Tsiklon-2 Ukrainian orbital launch vehicle. A government decree of 24 August 1965 ordered development by Yangel of a version of his R-36 rocket to orbit Chelomei's IS (Istrebitel Sputnik) ASAT and US (Upravlenniye Sputnik) naval intelligence satellites. The Tyklon 2 definitive operational version replaced the 11K67 launch vehicle from 1969 and was an adaptation of the 8K69 (SS-9) two stage ICBM. The IS and US Raketoplan-derived payloads had their own engines for insertion into final orbit. More...
Tsiklon-3 Ukrainian orbital launch vehicle. The Tsyklon 3 was developed in 1970-1977 as a part of a program to reduce the number of Soviet booster types. The first two stages were derived from the 8K68 version of the R-36 ICBM, while the restartable third stage was derived from that of the R-36-O. Compared to the Tsyklon 2, the launch vehicle increased payload to 4 metric tons, provided for completely automated launch operations, and had increased orbital injection accuracy. More...
Associated Manufacturers and Agencies
Yuzhnoye Ukrainian manufacturer of rockets, spacecraft, and rocket engines. Yangel Design Bureau, Dnepropetrovsk, Ukraine. More...
N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...
Tsyklon 2-3 N2O4/UDMH propellant rocket stage. Loaded/empty mass 3,200/400 kg. Thrust 77.96 kN. Vacuum specific impulse 317 seconds. Integral portion of payload. More...
Tsyklon 3-3 N2O4/UDMH propellant rocket stage. Loaded/empty mass 4,600/1,407 kg. Thrust 78.71 kN. Vacuum specific impulse 317 seconds. More...
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