The sensitivity of Martian aerocapture performance to L/D and flight path angle is studied. By adding the minimum energy constraint to the classical corridor width definition, an L/D of at least 0.8 was found to be necessary to ensure a 3.0-deg actual corridor width. The plane change desired during the aeropass was also found to affect L/D requirements.


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    Title :

    Aerodynamic requirements for a Mars rover/sample return aerocapture vehicle


    Contributors:

    Publication date :

    1989-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English