In this investigation, entry corridor analyses are performed to identify the aerodynamic requirements of a manned Mars aerobraking transfer vehicle. The major emphasis is on identifying the required aerobrake hypersonic L/D to insure a successful aerocapture. Aerobraking entry requirements are also imposed on a set of interplanetary mission opportunities to demonstrate their effect on mission flexibility. Based on the requirements of a 1 deg corridor width, deceleration into a parking orbit witn an apoapsis altitude of 32,972 km, and a 5-g deceleration limit, a manned Mars aerobrake characterized by an L/D of at least 1.5 is required for entry velocities as high as 10.0 km/sec. Limiting the Mars entry velocity to values below 8.5 km/sec is shown to induce a minor restriction on mission flexibility while alleviating aerothermodynamic and vehicle packaging concerns; hence, Mars entry velocities in the range of 6.0-8.5 km/sec are suggested, and a manned Mars aerobrake characterized by an L/D between 0.3 and 0.5 is recommended.


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    Titel :

    Aerodynamic requirements of a manned Mars aerobraking transfer vehicle


    Beteiligte:

    Kongress:

    AIAA Atmospheric Flight Mechanics Conference ; 1990 ; Portland, OR, United States


    Erscheinungsdatum :

    01.01.1990


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Aerodynamic requirements of a manned Mars aerobraking transfer vehicle

    Braun, Robert D. / Powell, Richard W. | NTRS | 1991


    Aerodynamic requirements of a manned Mars aerobraking transfer vehicle

    BRAUN, ROBERT D. / POWELL, RICHARD W. | AIAA | 1991


    Aerobraking systems for manned Mars missions

    Eldred, Charles H. | NTRS | 1992


    Earth aerobraking strategies for manned return from Mars

    BRAUN, ROBERT / POWELL, RICHARD | AIAA | 1991