Encyclopedia Astronautica

Izotov N2O4/UDMH rocket engine. 131 kN. Production from 1964. Isp=325s. Single chamber engine for UR-100 stage 2. Gas generator cycle with two large turbine exhaust pipes. First flight 1965.

Photos available in Russian Arms Cat. (Gives thrust as 15,200 kgf, Ispvac=326))

Application: UR-100 stage 2.

AKA: 15D13; 8D419; 8D423.
Status: Design 1964.
Thrust: 131.00 kN (29,449 lbf).
Specific impulse: 325 s.
Burn time: 184 s.
Number: 282 .

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Associated Countries
Associated Spacecraft
  • LK-700 Russian manned lunar lander. Chelomei's direct-landing alternative to Korolev's L3 manned lunar landing design. Developed at a low level 1964 to 1974, reaching mockup and component test stage. More...

See also
Associated Launch Vehicles
  • UR-100 Russian intercontinental ballistic missile. The UR-100 lightweight ICBM was the Soviet answer to the US Minuteman and was deployed in larger numbers than any other in history. It remained an enigma outside of intelligence circles in the West until after the collapse of the Soviet Union. It allowed the Soviet Union to match, and then surpass the United States in strategic deterrent capability. As such it was Vladimir Chelomei's crowning legacy to his country. More...

Associated Manufacturers and Agencies
  • Izotov Russian manufacturer of rocket engines. Izotov Design Bureau, Russia. More...

Associated Propellants
  • 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...

  • Haeseler, Dietrich, "Personal communication", 1998 December..

Associated Stages
  • 8S817 N2O4/UDMH propellant rocket stage. Loaded/empty mass 8,611/900 kg. Thrust 131.45 kN. Vacuum specific impulse 325 seconds. Orevo has sectioned hardware. Total mass, thrust accurate; Isp, empty mass and burn time estimated. Source: Placard, Orevo. More...

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