The LOx-methane upper stage motor development for the Lyra Launch Vehicle
Agency, Arturo de Lillis ASI - Italian Space ; Emanuela, Co-Authors Mr. Mauro Balduccini- ELV Corso Garibaldi Mrs. ; Agency, D’Aversa ASI - Italian Space ; et al. ; - ASI Sponsor
Jan - 2007

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type: Conference Proceedings

Abstract
The Lyra Launch Vehicle represents a follow-on of the Vega Launcher development that ELV(I), as Prime Contractor, is carrying out under ESA contract an whose qualification flight is scheduled in 2008. The Italian Space Agency (ASI) has set-up the Lyra Program with the objectives of studying the possible improving of the Payload capability and launch service flexibility of the European Launcher family, of consolidating the Italian Industry competence as System authority in the Launcher sector and, finally, of creating an Italian capability in AVIO (I) for the development of liquid propulsion systems based on Oxygen and Methane. The Lyra Launcher main requirement is to improve of about 30The Launcher configuration is based on the re-use of the Vega 1st and 2nd solid stages and on a new upper stage based on LOx-Methane propulsion that will substitute both the Vega (solid) 3rd stage and the storable bipropellant upper stage. The new LOX-Methane engine is an expander cycle, multi-start engine with a nominal thrust of about 100 KN and 364s of specific impulse, and with a throttling capability from 60 to 120During the phase B of the program, that is the main subject of this paper, a full scale engine demonstrator will be designed, manufactured and firing tested at ground conditions. This will enable the functional verification of the expander cycle performance and of the engine overall performances, including full firing time capability. Testing at sub-assembly (engine injectors, thrust chamber assembly, bearing in Methane etc) and equipment levels has been planned in order to control the program risk.

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