Encyclopedia Astronautica
RD-0215


Kosberg N2O4/UDMH rocket engine. 2450 kN. Developed 1962-65 for heavy Chelomei launcher (UR-900?) stage 1. Isp=310s. Engine unit consisting of 1 RD-0217 for tank pressurization and three RD-0216. Hardware not hot-tested.

Engine unit (DU) consisting of 1 RD-0217 for tank pressurization and three RD-0216. Intended for stage 1 of heavy launcher by Chelomei. Development stopped, hardware not hot-tested. Staged combustion cycle with ox.-rich gas generator.

Application: Planned heavy launcher (UR-700 ?) stage 1.

Characteristics

Chambers: ?.

Status: Developed 1962-65.
Diameter: 2.00 m (6.50 ft).
Thrust: 2,450.00 kN (550,780 lbf).
Specific impulse: 310 s.
Specific impulse sea level: 280 s.
Burn time: 102 s.
First Launch: 1962-65.

More... - Chronology...


Associated Countries
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
  • Kosberg Russian manufacturer of rocket engines. Kosberg 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...

Bibliography
  • Golubev, A A, KB KhimAvtomatiki - Straniy Istorii, Vol. 1, Voronezh 1995 via Dietrich Haeseler.

Associated Stages
  • 8S816 N2O4/UDMH propellant rocket stage. Loaded/empty mass 32,799/3,000 kg. Thrust 868.80 kN. Vacuum specific impulse 310 seconds. Orevo has sectioned hardware. Total mass, sea level thrust accurate; Isp, empty mass and burn time estimated. Source: Placard, Orevo. More...

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