Four 71-cm-diameter rocket motor chambers were designed and fabricated with advanced composite materials. The first three chambers were filament wound from boron/epoxy tape, and the fourth from graphite/epoxy tape. The first boron/epoxy chamber was 74 cm in length and was successfully hydroburst tested. The other three chambers were 57.6 cm in length for a smaller propellant load. The first shortened boron/epoxy chamber failed in proof test as a result of fabrication deficiencies. The last boron/epoxy and the graphite/epoxy chambers were successfully proof tested.
Development of advanced composite rocket motor chambers using boron and graphite fibers.
Conference on Reinforced Plastics in Aerospace Applications ; 1973 ; London
1973-04-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
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