This page no longer updated from 31 October 2001.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

RD-180 -

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

Gross Mass: 195,628 kg. Empty Mass: 13,725 kg. Thrust (vac): 423,052 kgf. Isp: 337 sec. Burn time: 132 sec. Propellants: Lox/Kerosene Isp(sl): 311 sec. Diameter: 3.1 m. Span: 3.0 m. Length: 29.0 m. Country: USA/Russia. No Engines: 1. RD-180 Status: Development.

Atlas booster and sustainer engine arrangement replaced by Glushko engines developed for Zenit. Not capable of single stage to single stage to orbit capability (an Internet spaceflight urban myth). The single-stage Atlas IIIA booster uses a high-performance RD-180 propulsion system produced by a U.S./Russian joint venture (RD AMROSS) comprised of Pratt & Whitney (U.S.) and NPO Energomash (Russia). The RD-180 burns liquid oxygen and RP-1 propellant and develops a lift-off (sea-level) thrust of 2.6 MN. The RD-180 throttles to various levels during atmospheric ascent to effectively manage the air-loads experienced by the vehicle enabling minimum Atlas vehicle and launch site infrastructure changes. Additionally, throttling results in satellite experienced flight environments that are nearly identical to Atlas IIAS.

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Last update 12 March 2001.
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