Encyclopedia Astronautica

Kosberg lox/lh2/kerosene rocket engine. 1412 kN. Alternative for Angara central stage, MAKS. Developed 1997-. Isp=455s. Tripropellant derivative of RD-0120. Some components tested in RD-0120TD technology demonstration in cooperation with Aerojet.

Two modes: LOX/LH2-Kerosene and LOX/LH2. Chamber pressure 190 / 85 bar. O:F ratio 4.0 / 6.0. The original source gave different thrust and specific impulse items. Those shown here are from the 2007 KBKhA web site (original values thrust 1720 kN / 780 kN, specific impulse 418 sec / 451sec.

Application: Alternative for Angara central stage, MAKS.


Throttled thrust(vac): 794.600 kN (178,633 lbf). Chamber Pressure: 190.00 bar. Oxidizer to Fuel Ratio: 4.

AKA: RD-0650TF; RD-0750.
Status: Developed 1997-.
Thrust: 1,412.00 kN (317,430 lbf).
Specific impulse: 455 s.
Specific impulse sea level: 415 s.
First Launch: 1997-.

More... - Chronology...

Associated Countries
See also
Associated Manufacturers and Agencies
  • Kosberg Russian manufacturer of rocket engines. Kosberg 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 Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
  • Novosti kosmonavtiki, Issues. 21-22, 1998 via Dietrich Haeseler.
  • KBKhA Web Site, Web Address when accessed: here.

Home - Browse - Contact
© / Conditions for Use