Manned spacecraft abort during ascent is a particularly unpleasant event. Not only does this represent a mission failure, but it can also be a very severe loading event on the crew. There are several dynamic events happening within a few hundred milliseconds while the vehicle is under aerodynamic-induced strain and possibly divergent control. Some of these events are spacecraft separation, abort motor ignitions, and aerodynamic variation. This paper will describe a methodology for implementing this analysis within a multi-body solution. Some generic examples will be shown along with some guidance on what parameters are important.


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    Titel :

    In-Flight Abort Separation Dynamics


    Beteiligte:
    Isam S Yunis (Autor:in)

    Kongress:

    Spacecraft and Launch Vehicle Dynamics Environments Workshop ; 2012 ; Los Angeles, CA, US


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




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