RD-0750
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Kosberg LOx/LH2/kerosene rocket engine. Alternative for Angara central stage, MAKS. Developed 1997-. 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 / 451 sec.
Throttled thrust(vac): 794.600 kN (178,633 lbf). Chamber Pressure: 190.00 bar. Oxidizer to Fuel Ratio: 4.
Related
- Country
- Russia
- Propellants
- Lox/Kerosene/LH2, Lox/LH2
- Agency
- Kosberg bureau