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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    Title :

    In-Flight Abort Separation Dynamics


    Contributors:

    Conference:

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


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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