Current launch vehicle trajectory design philosophies are generally based on maximizing payload capability. This approach results in an expensive trajectory design process for each mission. Two concepts of robust flight design have been developed to significantly reduce this cost: Standardized Trajectories and Command Multiplier Steering (CMS). These concepts were analyzed for an Advanced Launch System (ALS) vehicle, although their applicability is not restricted to any particular vehicle. Preliminary analysis has demonstrated the feasibility of these concepts at minimal loss in payload capability.


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    Title :

    Robust flight design for an advanced launch system vehicle


    Contributors:

    Conference:

    AIAA Guidance, Navigation and Control Conference ; 1991 ; New Orleans, LA, United States


    Publication date :

    1991-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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