Small rocket engine tests were conducted for the purpose of obtaining pulse performance data to aid in preliminary design and evaluation of attitude control systems. Both monopropellant and hypergolic bipropellant engines of thrust levels from 1 to 100 lbs were tested. The performance data for the hypergolic propellant rockets are compared with theoretical performance calculated from idealized chamber filling and evacuation characteristics. Electromechanical delays in valve response and heat transfer characteristics were found to cause substantial deviation between theoretical and test performance. The theoretical analysis is modified to obtain a semi-empirical model for hypergolic propellant rockets which is demonstrated to be reasonably accurate for two different engine configurations over a considerable range of duty cycles.


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    Titel :

    Pulse performance analysis for small hypergolic-propellant rocket engines


    Beteiligte:
    Smith, G. W. (Autor:in) / Sforzini, R. H. (Autor:in)

    Erscheinungsdatum :

    1972-04-13


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Pulse Performance Analysis for Small Hypergolic-Propellant Rocket Engines

    GERALD W. SMITH AND RICHARD H. SFORZINI | AIAA | 1972




    Computational analysis of liquid hypergolic propellant rocket engines

    KRISHNAN, A. / PRZEKWAS, A. / GROSS, K. | AIAA | 1992


    Propellant Handling Provisions at a Test Facility for Hypergolic Bipropellant Rocket Engines

    Schulte, G. / Advisory Group for Aerospace Research and Development; Propulsion and Energetics Panel | British Library Conference Proceedings | 1995