Computer Science
Scientific paper
Sep 2001
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2001esasp.480..183p&link_type=abstract
In: Proceedings of the 9th European Space Mechanisms and Tribology Symposium, 19-21 September 2001, Liège, Belgium. Compiled by
Computer Science
Launch Vehicle Mechanisms
Scientific paper
From technical point of view, Liquid propellant Rocket Engine (LRE) control architectures have to be designed in such a way that: (i) complexity/weight for control and actuation power of valves is minimal, (ii) the engine working point is as far as possible adapted to actual requirements throughout the mission, and (iii) RAMS requirements are complied with. In this context, investigations related to proportional electrically actuated LRE valves are of particular interest in order to investigate the implications of "All Electric Engine control" or in-flight control of the LRE operating point, identify mechanism and electronic controller architectures which present a maximum potential for standardisation and growth, and provide a hardware demonstration of a representative electric valve which can be used for a LRE firing test. As part of the ESA-GSTP2 program, Techspace Aero conducted a market survey identifying the needs for proportional actuation. Based on these considerations, a Technical Specification has been established and a valve demonstrator has been designed and successfully tested (Alcatel ETCA for electronic aspects).
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