Encyclopedia Astronautica

Glushko Lox/LCH4 rocket engine. 179 kN. Riksha-0 stage 2. Developed 1996-. Isp=378s. Upper stage version of RD-169 with larger nozzle. Gimbaling +/- 4 degree in two planes.

In 1996 prototype development was estimated to take four years from go-ahead. Nozzle expansion ratio is 150/0.036=4167.

Application: Riksha-0 stage 2.


Engine: 415 kg (914 lb). Chamber Pressure: 147.00 bar. Thrust to Weight Ratio: 43.97. Oxidizer to Fuel Ratio: 3.4.

Status: Developed 1996-.
Unfuelled mass: 415 kg (914 lb).
Height: 3.30 m (10.80 ft).
Diameter: 1.50 m (4.90 ft).
Thrust: 179.00 kN (40,240 lbf).
Specific impulse: 378 s.
First Launch: 1996-.

More... - Chronology...

Associated Countries
See also
Associated Launch Vehicles
  • Riksha Russian orbital launch vehicle. New design launch vehicle based on SLBM technology. More...

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...

  • Klepikov, Katorgin, Chvanov, "The New Generation of Rocket Engines, Operating by Ecologically Safe Propellant ...", IAF-Congress Turin, 1997, IAF-97-S.1.03 via Dietrich Haeseler.

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