The linear rocket engine is shown to be a viable candidate propulsion system for post-Space Shuttle single-stage-to-orbit systems. The linear engine system has been developed and fired demonstrating high performance and long life with firing durations exceeding 500 seconds. The application of the split or dual combustor to the linear engine permits the uses of two different propellant combinations in a single engine system. The split combustor possesses the advantages of the two position extendible bell nozzle in a fixed nozzle configuration. Engine power cycles and applications to typical vehicles are discussed.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Linear rocket engines for advanced space transportation systems


    Contributors:
    Sobin, A. J. (author) / Martinez, A. (author)

    Conference:

    American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference ; 1975 ; Anaheim, CA


    Publication date :

    1975-09-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English