Q21449565

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.

MainWikipediaGalleryBibliographyTableSearch

Wikidata
Bell 8096, XLR81-BA-11, YLR81-BA-11
Bell Model 8000, Bell Aircraft Corporation, 
United States, Ashkenaz, Calvinist Republic of Ghent, Chinland, Democratic Republic of the Congo, Havilah, Kingdom of Martabam-hongsawatoi, Kingdom of Wolaita, Persia, Reman, Sikh Confederacy, Tarshish, Bell Model 8000, Dong Fang Hong 2, Ekran, Republic of Haiti, 

​

Location: KML, Cluster Map, Maps,

Frameless

Type	Subtype	Date	Description	Notes	Source