The objective of this paper is to investigate the uncertainty in the bondline temperature response of a flexible thermal protection system subject to uncertain parameters in the hypersonic flowfield and thermal response modeling of a hypersonic inflatable aerodynamic decelerator configuration for ballistic Mars entry. An inflatable decelerator with a 10 m major diameter is selected for this study based on the forebody dimensions scaled from the 6 m test article that was tested in the NASA Ames Research Center’s National Full-Scale Aerodynamics Complex facility. A global nonlinear sensitivity analysis study for the bondline temperature uncertainty shows that the dimension of uncertain parameters can reduce from 22 to 8. An uncertainty analysis of the bondline temperature in the reduced dimensions indicates that the bondline temperature varies by as much as 125% above the nominal prediction and exceeds the temperature limit of 400°C. The largest uncertainty occurred at 70 s in the trajectory before separation of the inflatable decelerator for transition to a secondary descent technology. The main contributors to the bondline temperature uncertainty are the insulator and outer fabric conductivities, as well as the freestream density. The thickness and initial density of the insulator layer, closest to the gas barrier layer, are also shown to be significant contributors to the bondline temperature uncertainty, especially earlier in the trajectory.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Thermal Protection System Response Uncertainty of a Hypersonic Inflatable Aerodynamic Decelerator




    Publication date :

    2017




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.60 Raumfahrttechnik
    Local classification TIB:    770/7040



    Thermal Protection System Response Uncertainty of a Hypersonic Inflatable Aerodynamic Decelerator

    Brune, Andrew J. / Hosder, Serhat / Edquist, Karl T. et al. | AIAA | 2016



    Uncertainty Analysis of Thermal Protection System Response of a Hypersonic Inflatable Aerodynamic Decelerator

    Brune, Andrew J. / Hosder, Serhat / Edquist, Karl T. et al. | AIAA | 2016


    Morphing Hypersonic Inflatable Aerodynamic Decelerator

    Green, Justin S. / Dunn, Barry / Lindberg, Robert | AIAA | 2013


    Morphing Hypersonic Inflatable Aerodynamic Decelerator

    Green, J.S. / Dunn, B. / Lindberg, R. et al. | British Library Conference Proceedings | 2013