The maximum performance of a supersonic inlet will be achieved when operating as close as possible to its buzz boundary. In order to maintain high performance without crossing the buzz boundary, an active buzz margin predictor and controller is necessary. The goal of a control system is to acquire inlet buzz margin and maintain it as the designated value and predict inlet buzz before it occurs and then take some measures to buzz mitigation or inlet restart. The inlet buzz boundary and the margin of ducted rockets were first discussed and analysed. Then the dynamic mathematical model of a gas flow control system was established. Lastly, the inlet buzz margin controller of a ducted rocket was designed. Simulation results show that there exist anti-regulation characteristics for gas flow control for ducted rockets, and it leads to the particularity of inlet buzz margin control for ducted rockets in contrast to liquid ramjet. The designed inlet buzz margin has to be bigger to avoid the appearing of inlet buzz because of anti-regulation characteristics; otherwise, the inlet buzz phenomenon probably appears. If the inlet buzz of the ducted rocket appears, the command of decreasing fuel flow could not be given immediately; otherwise, the inlet buzz will aggravate.


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    Title :

    Supersonic inlet buzz margin control of ducted rockets


    Contributors:
    Shi, X (author) / Chang, J-T (author) / Bao, W (author) / Yu, D (author) / Li, B (author)


    Publication date :

    2010-10-01


    Size :

    9 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Supersonic inlet buzz margin control of ducted rockets

    Shi, X. / Chang, J.T. / Bao, W. et al. | Tema Archive | 2010


    Ducted Rockets

    K. C. Schadow | NTIS | 1976


    Ducted Rockets

    K. C. Schadow | NTIS | 1977


    Experimental Study of Supersonic Inlet Buzz

    Simon Trapier / Philippe Duveau / Sébastien Deck | AIAA | 2006