An integrated analysis is presented for ascent, stage separation and glide back performance of a small, partially reusable launch vehicle sized for a payload of about 330 lbs to a 150 nm polar orbit. The altitude margin was used a performance metric for the glideback performance. Aerodynamic databases for each of these three phases of flight were developed using a combination of engineering level code, free stream and proximity wind tunnel test data and Euler CFD results. The ascent and glideback trajectories were generated using POST and the stage separation simulation was done using the in-house software Sep-Sim as a front end to the commercially available multi-body dynamic simulation code ADAMS. The payload to the designated polar orbit was optimized subject to the constraints imposed by stage separation and adequate performance reserve for the glideback booster in addition to the usual ascent trajectory constraints.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Ascent, Stage Separation and Glideback Performance of a Partially Reusable Small Launch Vehicle


    Beteiligte:

    Kongress:

    42nd AIAA Aerospace Sciences Meeting and Exhibit ; 2004 ; Reno, NV, United States


    Erscheinungsdatum :

    01.01.2004


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch





    ASCENT, STAGE SEPARATION AND GLIDEBACK PERFORMANCE OF A PARTIALLY REUSABLE SMALL LAUNCH VEHICLE

    Pamadi, B. N. / Tartabini, P. V. / Starr, B. R. et al. | British Library Conference Proceedings | 2004




    Research on robust ascent guidance of reusable launch vehicle

    Zhang, Jinhan / Wei, Jianli / Yu, Yunfeng et al. | IEEE | 2017