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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:
- Staged combustion cycle engine
- LOX/Kerosene propellants
- 2 thrust chambers (gimbal +8 )
- 1 oxygen rich preburner
- High pressure turbopump assembly
- 2 stage fuel pump
- single-stage oxygen pump
- single turbine
- Hypergolic ignition
- Self contained hydraulic system (valves, TVC) powered with kerosene from fuel pump
- Health monitoring and life prediction system
- Automated flight preparation (after installation on the vehicle, all operations are automated through launch)
- Minimized interfaces with launch pad and vehicle (pneumatic and hydraulic systems self contained, electrical panels consolidated, thrust frame to simplify mechanical interface)
- Environmentally clean operations with staged combustion oxidizer rich preburner, and oxidizer start and shutdown modes that eliminate coking and unburned kerosene pollution potential
- 50 - 100% continuous throttling provides potential for real time trajectory matching and engine checkout on the pad before launch commit
- 80% RD-170 parts
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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© Mark Wade, 2001 .