The selection of the unique aeroshell shape for the Mars Microprobes is discussed. A description of its aerodynamics in hypersonic rarefied, hypersonic continuum, supersonic and transonic flow regimes is then presented. This description is based on Direct Simulation Monte Carlo analyses in the rarefled-flow regime, thermochemical nonequilibrium Computational Fluid Dynamics in the hypersonic regime, existing wind tunnel data in the supersonic and transonic regime, additional computational work in the transonic regime, and finally, ballistic range data. The aeroshell is shown to possess the correct combination of aerodynamic stability and drag to convert the probe's initial tumbling attitude and high velocity at atmospheric-interface into the desired surface-impact orientation and velocity.


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    Title :

    Aerodynamics of the Mars Microprobe Entry Vehicles


    Contributors:
    R. A. Micheltree (author) / J. N. Moss (author) / F. M. Cheatwood (author) / F. A. Green (author) / R. D. Braun (author)

    Publication date :

    2004


    Size :

    16 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Aerodynamics of the Mars Microprobe Entry Vehicles

    R. A. Mitcheltree / J. N. Moss / F. M. Cheatwood et al. | AIAA | 1999


    Aerodynamics of the Mars Microprobe entry vehicles

    Mitcheltree, R. / Moss, J. / Cheatwood, F. et al. | AIAA | 1997


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    Mitcheltree, R. A. / Moss, J. N. / Cheatwood, F. M. et al. | NTRS | 1997


    Aerodynamics of the Mars Microprobe Entry Vehicles

    Micheltree, R. / Moss, J. / Cheatwood, F. et al. | British Library Conference Proceedings | 1997