Aerodynamic heating and thermal protection design analyses were performed for three blunt re-entry bodies at an L/D = 0.3 returning from low earth orbit. These configurations consisted of a scaled up Apollo command module, a Viking re-entry vehicle, and an Aeroassist Flight Experiment (AFE) aerobrake, each with a maximum diameter of 4.42 m. The aerothermodynamic analysis determined the equilibrium stagnation point heating rate and heat load for nominal and 3-sigma re-entry trajectories and the distribution of heating along the pitch and yaw planes for each of the vehicles at the time of highest heat flux. Using the predicted heating rates and heating distributions, a Thermal Protection System (TPS) design with flight certified materials was tailored for each of the configurations. Results indicated that the heating to the corner of the Viking aeroshell would exceed current limits of reusable tile material. Also, the maximum heating for the AFE would be 15 percent greater than the maximum heating for the Apollo flying the same trajectory. TPS designs showed no significant advantage in TPS weight between the different vehicles; however, heat-shield areal density comparisons showed the Apollo configuration to be the most efficient in terms of TPS weight.


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    Titel :

    Aerothermodynamic performance and thermal protection design for blunt re-entry bodies at L/D = 0.3


    Beteiligte:
    Caram, Jose M. (Autor:in) / Kowal, T. J. (Autor:in)

    Kongress:

    AIAA, Aerospace Sciences Meeting and Exhibit ; 1993 ; Reno, NV, United States


    Erscheinungsdatum :

    1993-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch







    METAMODELS FOR AEROTHERMODYNAMIC DESIGN OPTIMIZATION OF HYPERSONIC SPIKED BLUNT BODIES

    Ahmed, M. / Qin, N. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2010