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RD-180 -

Credit: Lockheed Martin. 14,267 bytes. 189 x 227 pixels.

Manufacturer Name: RD-180. Designer: Glushko. Developed in: 1993-99, 1992-. Application: AtlasIIAR stage 1. Used on stages: Atlas IIIA. Used on launch vehicles: Atlas IIIA, Atlas IIIB, Timberwind Centaur. Propellants: Lox/Kerosene Thrust(vac): 423,050 kgf. Thrust(vac): 4,152.00 kN. Isp: 338 sec. Isp (sea level): 311 sec. Burn time: 150 sec. Mass Engine: 5,393 kg. Diameter: 3.0 m. Length: 3.6 m. Chambers: 2. Chamber Pressure: 257.00 bar. Area Ratio: 36.87. Oxidizer to Fuel Ratio: 2.72. Country: Russia/USA. Status: Hardware. First Flight: 1999. References: 287 , 342 , 355 .

The RD-180 is a two thrust chamber derivative of the RD-170. It packages the high performance, operability, and reusability features of the RD-170 in a size to meet U.S. booster propulsion needs. The RD-180 is a total propulsion unit with hydraulics for control valve actuation and thrust vector gimbaling, pneumatics for valve actuation and system purging, and a thrust frame to distribute loads, all self contained as part of the engine. The engine, employing a LOX lead start, stage combustion cycle and LOX rich turbine drive, will deliver a 10 percent performance increase over current operational U.S. booster engines and provide clean reusable operation. Only the main turbo-pump assembly and boost pumps require development and they are scalable from the RD-120 and RD-170 units. All other components are taken directly from the RD-170. The RD-180 was developed in 42 months at a small fraction of the cost of a typical U.S. new engine development. This engine will power Lockheed Martin's Atlas III and Evolved Expendable Launch Vehicle (EELV). General Description:

Used in the Atlas IIIA and developed in 1993-1999. This is double chamber motor is 1/2 of the RD-173 so is cheap and fast to develop, 70% of the parts come directly fromRD-170, main new development is turbopump. Throttle range 40-100%.

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Last update 12 March 2001.
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