This paper discusses the methodology utilized to characterize exhaust plume expansion of the 490 N bipropellant engine and provides an analysis of exhaust plune impingement effects on the Mars Observer oxidizer tank structure. Nozzle and plume continuum flowfields are computed with a method of characteristics solution while transitional and rarefied regions of the exhaust gas flow were defined by a direct simulation Monte Carlo method. Results of this study provide sufficient data for an assessment of spacecraft thermal impacts due to plume heating effects and thrust losses from exhaust plume impingement.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Bipropellant engine plume analyses for the Mars Observer scientific spacecraft


    Contributors:

    Publication date :

    1990-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English






    Bipropellant rocket exhaust plume analysis on the Galileo spacecraft

    Guernsey, C. S. / Mcgregor, R. D. | NTRS | 1986


    The Effect of Impingement Angle on Bipropellant Thruster Plume Degradation of Spacecraft Materials

    Courtney Steagall / Crystal Quiroz / Brian Tulaba et al. | NTRS | 2024


    Mars Observer spacecraft

    POTTS, DENNIS | AIAA | 1989