This paper covers the simulation and evaluation of a controller design for the Crew Module (CM) Launch Abort System (LAS), to measure its ability to meet the abort performance requirements. The controller used in this study is a hybrid design, including features developed by the Government and the Contractor. Testing is done using two separate 6-degree-of-freedom (DOF) computer simulation implementations of the LAS/CM throughout the ascent trajectory: 1) executing a series of abort simulations along a nominal trajectory for the nominal LAS/CM system; and 2) using a series of Monte Carlo runs with perturbed initial flight conditions and perturbed system parameters. The performance of the controller is evaluated against a set of criteria, which is based upon the current functional requirements of the LAS. Preliminary analysis indicates that the performance of the present controller meets (with the exception of a few cases) the evaluation criteria mentioned above.


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    Title :

    Crew Exploration Vehicle Launch Abort Controller Performance Analysis


    Contributors:

    Conference:

    AIAA Guidance, Navigation, and Control Conference & Exhibit ; 2007 ; Hilton Head, SC, United States


    Publication date :

    2007-08-20


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English