Encyclopedia Astronautica

Glushko Lox/Kerosene/LH2 tripropellant engine. 1966 kN. Developed 1990's. Isp=407 / 452 s. Tripropellant engine, single chamber, derived from RD-701 project. Chamber pressure 294 / 124 bar. First flight 1999.

Mass excluding sensors, gimbal actuators and heat shield. Mass excluding sensors, gimbal actuators and heat shield.

Throttled thrust(vac): 782.000 kN (175,800 lbf). Thrust (sl): 1,720.100 kN (386,694 lbf). Thrust (sl): 175,403 kgf. Engine: 2,422 kg (5,339 lb). Chamber Pressure: 294.00 bar. Thrust to Weight Ratio: 82.77.

Status: Developed 1990's.
Unfuelled mass: 2,422 kg (5,339 lb).
Height: 3.81 m (12.49 ft).
Diameter: 1.77 m (5.80 ft).
Thrust: 1,966.00 kN (441,974 lbf).
Specific impulse: 407 s.
Specific impulse sea level: 356 s.
First Launch: 1990's.

More... - Chronology...

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

Associated Propellants
  • Lox/Kerosene/LH2 Tripropellant motors use high-density kerosene for the boost phase, then low-density, high-performance liquid hydrogen for the later stages of ascent. However the propellants are stored in separate tanks. The fuel density indicated is the average for the MAKS design, which burned 17,850 kg LH2 and 18,698 Kerosene to reach orbit using 175,758 kg of liquid oxygen oxidiser. More...

  • Russian Space Industry, Federation of American Scentists Web Pages, 1998 via Dietrich Haeseler. Web Address when accessed: here.

Home - Browse - Contact
© / Conditions for Use