This paper contains calculations about propellant slosh for an upper stage rocket. The liquid fuel is modeled by using an equivalent mechanical model, from this point of view the stability of this rocket is examined by means of mass-spring model. In theory, a nonlinear mathematical model is derived and nonlinear feedback control laws are used. Specifications of the Attitude Vernier Upper Module (AVUM) upper stage rocket Vega are chosen for simulations. The results of this study are obtained for first four slosh modes.


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    Titel :

    Model and control problem for space vehicles with propellant slosh


    Beteiligte:
    Sahin, Merve (Autor:in) / Cihan, Melahat (Autor:in) / Kaya, Metin Orhan (Autor:in)


    Erscheinungsdatum :

    01.06.2015


    Format / Umfang :

    822030 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



    A propellant slosh measuring system for space vehicles

    Bynum, B. G. / Hamlet, J. F. | NTRS | 1965


    Adaptive control of propellant slosh for launch vehicles

    Adler, James M. / Lee, Michael S. / Saugen, John D. | SPIE | 1991


    Propellant slosh loads

    USA, National Aeronautics and Space Administration | TIBKAT | 1968