This page no longer updated from 31 October 2001. Latest version can be found at 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.

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Last update 12 March 2001.
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© Mark Wade, 2001 .