RD-180 engines for a first stage of “Atlas” launch-vehicle

            In the beginning 1996 the NPO Energomash’ project of RD-180 engine was recognized as the winner of competition on development and delivery of the engine of a first stage for the upgraded “Atlas” launch-vehicle of the US aerospace company Lockheed Martin. It is the dual-chamber engine with afterburning of oxidizer-rich preburner’ gas, with thrust vector control thanks to gimballing of each chamber in two planes, with a capability to provide deep throttling of engine thrust in flight. The given design bases on the well proven designs of units and parts of RD-170/171 engines. The creation of the powerful engine of a first stage was carried out in the shortest possible time, and development - on small quantity of hardware. Having signed contract on engine development in summer 1996, the first fire test of the engine – prototype was conducted in November 1996, and in April 1997 - fire test of the nominal engine. In 1997-1998 the set of fire tests of the engine in a structure of a stage of the launch-vehicle was successfully conducted in USA. The certification of the engine for use in a structure of “Atlas 3” launch-vehicle was completed in spring 1999. The maiden launch of “Atlas 3” launch-vehicle with RD-180 engine was conducted in May 2000. The certification of the engine for use in a structure of the “Atlas 5” launch-vehicle was completed in summer 2001. The maiden flight of “Atlas 5” launch-vehicle with the RD-180 engine was conducted in August 2002.

Main parameters of RD-180 engine

Liquid propellant rocket engine with afterburning of oxidizer-rich gas

Propellant                                               liquid oxygen + kerosene