The application of the turbine engine to high flight speed missiles is considered and the advantages that such missiles have are discussed. In order to show examples of high flight speed turbine engines a straight turbojet engine and a turbojet-ramjet engine are described briefly. The performance at a Mach 4.0 cruise condition is shown for a sample set of assumptions. The acceleration phase of the mission is then considered and the differences in characteristics between a high specific thrust engine and a low specific thrust engine are described. The inlet and exit matching problems over the flight speed range are also illustrated. The suitability of the turbine engine for powering missiles with different ranges and different engine requirements is discussed. It is indicated that several important missions can be carried out by turbine engine powered missiles of low gross weight.


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    Titel :

    TURBINE ENGINES FOR HIGH SPEED MISSILES


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:
    Zipkin, M. A. (Autor:in) / NEITZEL, R. E. (Autor:in)

    Kongress:

    Pre-1964 SAE Technical Papers ; 1906



    Erscheinungsdatum :

    1958-01-01




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    Turbine engines for high speed missiles

    Neitzel, R.E. / Zipkin, M.A. | Engineering Index Backfile | 1958


    Kinetic Heating of High Speed Missiles

    B. E. Richards | NTIS | 1979


    High Speed Pumps for Gas Turbine Engines

    Murray, J. F. | SAE Technical Papers | 1969


    Large rocket engines for space vehicles and missiles

    Hoffman, S.K. | Engineering Index Backfile | 1961