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The Bell Aerosystems Company XLR81 was an American liquid-propellant rocket engine, which was used on the Agena upper stage. It burned UDMH and RFNA fed by a turbopump in a fuel rich gas generator cycle. The turbopump had a single turbine with a gearbox to transmit power to the oxidizer and fuel pumps. The thrust chamber was all-aluminum, and regeneratively cooled by oxidizer flowing through gun-drilled passages in the combustion chamber and throat walls. The nozzle was a titanium radiatively cooled extension. The engine was mounted on a hydraulic actuated gimbal which enabled thrust vectoring to control pitch and yaw. Engine thrust and mixture ratio were controlled by cavitating flow venturis on the gas generator flow circuit. Engine start was achieved by solid propellant start cartridge.
The HWK 109-507 was a liquid-propellant rocket engine developed by Germany during World War II. It was used to propel the Hs 293 anti-ship guided missile.
References
- ↑ US Patent 3,205,656,Elverum Jr., Gerard W.,"Variable thrust bipropellant rocket engine",issued 1963-02-25
- ↑ US Patent 3,699,772,Elverum Jr., Gerard W.,"Liquid propellant rocket engine coaxial injector",issued 1968-01-08
- ↑ REMEMBERING THE GIANTS - Apollo Rocket Propulsion Development. NASA. pp. 73–86.
- ↑ Dressler, Gordon A.; Bauer, J. Martin (July 2000). TRW Pintle Engine Heritage and Performance Characteristics (PDF). 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Redondo Beach, CA: TRW Inc. doi:10.2514/6.2000-3871. AIAA 2000-3871. Archived (PDF) from the original on 31 March 2022.
- ↑ "TR-201". Encyclopedia Astronautica. Archived from the original on 6 July 2008. Retrieved 4 June 2012.
- ↑ US Patent 3,699,772,Elverum Jr., Gerard W.,"Liquid propellant rocket engine coaxial injector",issued 1968-01-08
- ↑ US Patent 3,205,656,Elverum Jr., Gerard W.,"Variable thrust bipropellant rocket engine",issued 1963-02-25
- ↑ "Delta P". Encyclopedia Astronautica. Archived from the original on 17 June 2012. Retrieved 4 June 2012.
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