The linear aerospike engine concept for single-stage-to-orbit application that was studied under NASA/LeRC Contract NAS3-20114 is discussed in this paper. It has a split combustor that operates in a dual-fuel (hydrocarbon/hydrogen) mode. Gas generator and staged combustion power cycles are examined. Performance, engine weight, and engine geometry data are presented. The design of a 4-million pound thrust engine is discussed; major components and engine operation are described.
Linear aerospike engine
Linearmotor (Aerospike) fuer die Raumfahrt
AIAA-Papers ; 1-19
1977
19 Seiten, 15 Bilder, 2 Tabellen, 4 Quellen
Aufsatz (Konferenz)
Englisch
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