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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Development of advanced composite rocket motor chambers using boron and graphite fibers.


    Contributors:

    Conference:

    Conference on Reinforced Plastics in Aerospace Applications ; 1973 ; London


    Publication date :

    1973-04-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Development of boron epoxy rocket motor chambers.

    Jensen, W. M. / Knoell, A. C. / Zweben, C. | NTRS | 1972


    Fabrication of boron/epoxy rocket motor chambers.

    Jensen, W. M. / Stang, D. A. | NTRS | 1972



    Advanced tube-bundle rocket thrust chambers

    KAZAROFF, JOHN M. / PAVLI, ALBERT J. | AIAA | 1992


    Advanced tube-bundle rocket thrust chambers

    Kazaroff, John M. / Pavli, Albert J. | NTRS | 1992