This paper describes two unconventional types of internal combustion reciprocating engines designed to drive rectified alternators to provide electrical power for space missions. The engines use Aerozine 50 as the fuel and nitrogen tetroxide as the oxidizer. These two propellants are commonly used in liquid rockets and are characterized by the combination of high energy release and immediate ignition upon contact. The first engine is designed to provide 6 hp using a plunger type propellant injection system and in-head exhaust valve. The second provides 4.5 hp using a unique pressure fed, cam-operated, poppet injector and cylinder exhaust ports. One of the critical problems in the design of these engines concerns the very short time interval during which the propellants must be injected and burned.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    The Space Hypergolic Bipropellant Internal Combustion Engine


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:

    Kongress:

    Pre-1964 SAE Technical Papers ; 1906



    Erscheinungsdatum :

    1963-01-01




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    Combustion of a TMEDA/WFNA Hypergolic in a Bipropellant Rocket Engine

    Hollingshead, Joshua / Litzinger, Morgan / Kiaoulias, Dimitris et al. | AIAA | 2019


    COMBUSTION OF A TMEDA/WFNA HYPERGOLIC IN A BIPROPELLANT ROCKET ENGINE

    Hollingshead, Joshua / Litzinger, Morgan / Kiaoulias, Dimitris et al. | TIBKAT | 2019


    Starting Transients Of Hypergolic Bipropellant Rockets

    Bollinger, Loren E. / Lemmon, Jr. Alexis W. / Goldsmith, Martin | AIAA | 1960


    Hypergolic bipropellant spray combustion and flow modelling in rocket engines

    LAROSILIERE, LOUIS / LITCHFORD, RON / JENG, SAN-MOU | AIAA | 1990