The Mars Microprobe mission will provide the first opportunity for subsurface measurements, including water detection, near the south pole of Mars. In this paper, performance of the Microprobe aeroshell design is evaluated through development of a six-degree-of-freedom (6-DOF) aerodynamic database and flight dynamics simulation. Numerous mission uncertainties are quantified and a Monte-Carlo analysis is performed to statistically assess mission performance. Results from this 6-DOF Monte-Carlo simulation demonstrate that, in a majority of the cases (approximately 2-/spl sigma/), the penetrator impact conditions are within current design tolerances. Several trajectories are identified in which the current set of impact requirements are not satisfied. From these cases, critical design parameters are highlighted and additional system requirements are suggested. In particular, a relatively large angle-of-attack range near peak heating is identified.


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    Title :

    Mars Microprobe entry analysis


    Contributors:

    Published in:

    Publication date :

    1997-01-01


    Size :

    1454106 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



    Mars Microprobe Entry Analysis

    Braun, R. D. / Mitcheltree, R. A. / Cheatwood, F. M. et al. | British Library Conference Proceedings | 1997



    Mars Microprobe Entry-to-Impact Analysis

    Robert D. Braun / Robert A. Mitcheltree / F. McNeil Cheatwood | AIAA | 1999