This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
astronautix.com RD-0120
RD-0120 Engine
RD-0120 Engine - The original RD-0120 engines, Russian equivalent to the US Space Shuttle Main Engine, are mothballed at Baikonur. Despite various proposals for their use, future production is unlikely.

Credit: © Mark Wade. 15,530 bytes. 162 x 288 pixels.

Manufacturer Name: RD-0120. Government Designation: 11D122. Other Designations: RO-200. Designer: Kosberg. Developed in: 1976-90. Application: Energia core stage. Used on stages: Albatros Carrier Aircraft, Energia Core, Energia EUS, Interim HOTOL, Vulkan 1. Used on launch vehicles: Albatros, Energia, Interim HOTOL, Vulkan. Propellants: Lox/LH2 Thrust(vac): 200,000 kgf. Thrust(vac): 1,961.00 kN. Isp: 455 sec. Isp (sea level): 359 sec. Burn time: 600 sec. Mass Engine: 3,450 kg. Diameter: 2.4 m. Length: 4.5 m. Chambers: 1. Chamber Pressure: 218.00 bar. Area Ratio: 85.70. Oxidizer to Fuel Ratio: 6.00. Country: Russia. Status: Out of Production. First Flight: 1987. Last Flight: 1988. Flown: 10. References: 308 .

First operational Russian cryogenic systems. Starting point was US SSME, resulting in engine of similar size, thrust, and specific impulse. Feed Method: 35,000 rpm dual-stage turbopumps on each chamber. A single pre-burner burns fuel-rich at 527 Celsius to drive the single-shaft high pressure turbopump. Some of the pre-burner gas drives the oxygen low pressure pump. the fuel low pressure pump is driven by GH2 from the main chamber cooling loop.. Throttle range is 45%. Throat dia 261 mm, exit dia 2420 mm. The original RD-0120 engines are mothballed at Baikonur.

Back to Index
Last update 12 March 2001.
Definitions of Technical Terms.
Contact Mark Wade with any corrections or comments.
Conditions for use of drawings, pictures, or other materials from this site..
© Mark Wade, 2001 .