The aerothermal environment is examined for two vehicle forebodies near the peak heating points of lunar and martian return-to-earth trajectories at several nominal entry velocities. The first vehicle forebody is that of a 70 deg aerobrake for entry into earth orbit; the second, a capsule of Apollo configuration for direct entry into the earth's atmosphere. The configurations and trajectories are considered likely candidates for such missions. Two-temperature, thermochemical nonequilibrium models are used in the flow field analyses. In addition to Park's empirical model for dissociation under conditions of thermal nonequilibrium, the Gordiets kinetic model for the homonuclear dissociation of N2 and O2 is also considered. Temperature and emission profiles indicate nonequilibrium effects in a 2 to 5 cm post shock region. Substantial portions of the shock layer flow appear to be in equilibrium. The shock layer over an aerobrake for return from the moon exhibits the largest extent of nonequilibrium effects of all considered missions. Differences between the Gordiets and Parks kinetic model were generally very small for the lunar return aerobrake case, the greatest difference of 6.1 percent occurring in the radiative heating levels.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Convective and radiative heating for vehicle return from the Moon and Mars


    Contributors:

    Publication date :

    1995-07-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Numerical Prediction of Convective and Radiative Heating of a Mars Sampler Return Orbiter

    Bedon, N. / European Space Agency / Centre national d'etudes spatiales (France) | British Library Conference Proceedings | 2006


    HYDRATION: Mining Water Ice on the Moon and Mars Using Downhole Radiative Heating

    Lordos, George / Vanderhout, Amy / Adams, Andrew et al. | TIBKAT | 2021


    Assessment of Convective and Radiative Heating for Jupiter Trojan Sample Return Capsule

    Fujita, Kazuhisa / Takayanagi, Hiroki / Matsuyama, Shingo et al. | AIAA | 2014


    MSRO Convective and Radiative Heating

    Surzhikov, Sergey / Omaly, P | AIAA | 2008