RD-0120M
RD-0120 Engine
Credit - © Mark Wade
Manufacturer Name: RD-0120M. Government Designation: 11D122A. Designer: Kosberg. Developed in: 1987-1991. Application: Energia-M core stage. Propellants: Lox/LH2. Thrust(vac): 1,961.000 kN (440,850 lbf). Thrust(sl): 1,517.100 kN (341,058 lbf). Isp: 455 sec. Isp (sea level): 372 sec. Burn time: 600 sec. Mass Engine: 3,450 kg (7,600 lb). Diameter: 2.42 m (7.93 ft). Length: 4.55 m (14.92 ft). Chambers: 1. Chamber Pressure: 218.00 bar. Area Ratio: 85.70. Oxidizer to Fuel Ratio: 6.00. Thrust to Weight Ratio: 57.97. Country: Russia. Status: Development ended 1993. First Flight: 1987. Flown: 8.00.

From 1987 KBKhA worked on upgrading the 11D122 (RD-0120) engine for Energia-M launcher, including the possibility to throttle the engine down to 28% thrust. The original RD-0120 engines are mothballed at Baikonur.

RD-0120M used on Rocket Stages

Bibliography and Further Reading
  • Haeseler, Dietrich, Information material from Chemical Automatics Design Bureau, Voronezh 1993 via Dietrich Haeseler.
 
 
 
 
 
 
 
 
 
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