One of the key design objectives of NASA's Orion Exploration Mission 1 (EM- 1) is to execute a guided entry trajectory demonstrating GN&C capability. The focus of this paper is defining the flyable entry corridor for EM-1 taking into account multiple subsystem constraints such as complex aerothermal heating constraints, aerothermal heating objectives, landing accuracy constraints, structural load limits, Human-System-Integration- Requirements, Service Module debris disposal limits and other flight test objectives. During the EM-1 Design AnalysisCycle 1 design challenges came up that made defining the flyable entry corridor for the EM-1 mission critical to mission success. This documentdetails the optimization techniques that were explored to use with the 6-DOF ANTARES simulation to assist in defining the design entry interface state and entry corridor with respect to key flight test constraints and objectives.


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    Titel :

    Definition ofthe Design Trajectory and Entry Flight Corridor for the NASA Orion Exploration Mission 1 Entry Trajectory Using an Integrated Approach and Optimization


    Beteiligte:
    W.L McNamara (Autor:in) / D.R Braun (Autor:in)

    Erscheinungsdatum :

    2014


    Format / Umfang :

    13 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch






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