LOX-Hydrocarbon Rocket Engines and Thrust Chamber Technologies for Future Launch Vehicle Applications

Details LOX-Hydrocarbon Rocket Engines and Thrust Chamber Technologies for Future Launch Vehicle Applications LOX-Hydrocarbon Rocket Engines and Thrust Chamber Technologies for Future Launch Vehicle Applications

Jan 2002

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002iaf..confe.780h&link_type=abstract

IAF abstracts, 34th COSPAR Scientific Assembly, The Second World Space Congress, held 10-19 October, 2002 in Houston, TX, USA.,

Computer Science

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Recent investigations into the use of hydrocarbon fuels for launcher propulsion and in-orbit propulsion show the potential to satisfy the market's performance and cost requirements. The main expected advantages compared to current cryogenic and storable propellants are reduced handling effort and reduced safety precautions. Large liquid boosters or first stages for expendable and reusable vehicles are seen today as major application areas. Engine and stage concepts have been compared assuming various possible propellant combinations with hydrocarbon fuels. The expected characteristics like performance, dry mass, and development status are compared. Both expendable as well as reusable vehicle stages were considered. Investigations aiming at identifying the optimum hydrocarbon propellant in view of thrust chamber performance and engine system have been performed. System studies were performed to conclude on propellant selection, the propulsion system configuration, and the most economic engine cycle for the considered applications. The chamber cooling was assessed for envisaged chamber operational conditions in view of cooling limitations by propellant dissociation and coking. Since 1993 injector and combustion chamber technologies for the applications of different hydrocarbon propellant combinations are investigated by Astrium Space Infrastructure. The operation with hydrocarbon propellants was already demonstrated with an existing Aestus engine in cooperation with Boeing Propulsion and Power. Test have been performed with a subscale combustion chamber with the selected propellants LOX-methane and LOX-kerosene to confirm operation feasibility, cooling, and performance in a cooperation of Astrium with Chemieautomatics Design Bureau in Russia. Several injection concepts have been studied to allow a comparison and down-selection for future application. A continuation of this program is currently under preparation.

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