Encyclopedia Astronautica

Glushko Lox/LCH4 rocket engine. 2089 kN. Developed 1996-on. Proposed variant of RD-192. Gas generator cycle. Gimbaling +/- 8 degree in two planes. Status 1998 was project based on RD-191 protoype, development estimated for four years. Isp=341s.

Chamber Pressure: 245.00 bar. Oxidizer to Fuel Ratio: 3.

Status: Developed 1996-on.
Height: 3.62 m (11.87 ft).
Diameter: 1.45 m (4.75 ft).
Thrust: 2,089.00 kN (469,625 lbf).
Specific impulse: 341 s.
Specific impulse sea level: 311 s.
First Launch: 1996-.

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Associated Countries
See also
Associated Manufacturers and Agencies
  • Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...

Associated Propellants
  • Lox/LCH4 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. Liquid methane has been proposed as a propellant by the Russians. More...

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