The capability of the HL-20 lifting body spacecraft to perform an abort maneuver from the launch pad to a horizontal landing was studied at NASA Langley Research Center. This study involved both piloted and batch simulation models of the vehicle. A point-mass model of the vehicle was used for trajectory optimization studies. The piloted simulation was performed in the Visual Motion Simulator in fixed-base mode. A candidate maneuver was developed and refined for the worst-case launch-pad-to-landing-site geometry using an iterative procedure of off-line maneuver analysis followed by piloted evaluations and heuristic improvements to the candidate maneuver. The resulting maneuver demonstrates the launch site abort capability of the HL-20 and dictates requirements for nominal abort motor performance. The sensitivity of the maneuver to variations in several design parameters was documented.


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    Title :

    Investigation of the launch pad abort capabilities of the HL-20 lifting body


    Contributors:

    Conference:

    AIAA, Atmospheric Flight Mechanics Conference ; 1993 ; Monterey, CA, United States


    Publication date :

    1993-08-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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