The RD-180 engine
Posted: February 19, 2002

A two-nozzle RD-180 engine sits on display. Photo: Pratt & Whitney
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 (933,400 lb thrust) 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, staged combustion cycle and LOX rich turbine drive, delivers a 10 percent performance increase over current operational U.S. booster engines and provide clean reusable operation.

Lockheed Martin selected the RD-180 engine to provide the booster propulsion for its Atlas 3 launch vehicle and its candidate for the U.S. Air Force's Evolved Expendable Launch Vehicle (EELV).

The RD-180 is a staged combustion cycle engine that burns liquid oxygen and kerosene propellants. The two thrust chambers can gimbal +-8 degrees. The engine has a health monitoring and life prediction system. Minimized interfaces are needed with launch pad and vehicle (pneumatic and hydraulic systems self contained, electrical panels consolidated, thrust frame to simplify mechanical interface).

The engine offers environmentally clean operations with staged combustion oxidizer rich preburner, and oxidizer start and shutdown modes that eliminate coking and unburned kerosene pollution potential.

Forty to 100 percent continuous throttling provides potential for real time trajectory matching and engine checkout on the pad before launch commit.

RD-180 facts  
Nominal thrust (sea level) 860,200 lb
(vacuum) 933,400 lb
Specific impulse (sea level) 311.3 sec
Vacuum specific impulse 337.8 sec
Chamber pressure 3,722 psia
Nozzle area ratio 36.87:1
Mixture ratio 2.72
Length 140 in.
Diameter 118 in.
Throttle range 40-100%
Total system dry weight 11,889 lb
Source: Pratt & Whitney/NPO Energomash

Flight data file
Vehicle: Atlas 3B (AC-204)
Payload: EchoStar 7
Launch date: Feb. 21, 2002
Launch window: 7:13-8:14 a.m. EST (1213-1314 GMT
Launch site: SLC-36B, Cape Canaveral AFS, Fla.
Satellite broadcast: Telstar 6, Trans. 22, C-band

Pre-launch briefing
Launch timeline - Chart with times and descriptions of events to occur during the launch.

Ground track - See the trajectory the rocket will follow during its flight.

Atlas 3B vehicle data - Overview of the rocket to be used in this launch.

EchoStar 7 - Description of this direct-to-home TV broadcasting satellite.

Atlas index - A directory of our previous Atlas launch coverage.