A modified source flow model was used to calculate the plume flowfield from a Mars Odyssey thruster during aerobraking. The source flow model results compared well with previous detailed CFD results for a Mars Global Surveyor thruster. Using an iso-density surface for the Odyssey plume, DSMC simulations were performed to determine the effect the plumes have on the Odyssey aerodynamics. A database was then built to incorporate the plume effects into 6-DOF simulations over a range of attitudes and densities expected during aerobraking. 6-DOF simulations that included the plume effects showed better correlation with flight data than simulations without the plume effects.
Plume Modeling and Application to Mars 2001 Odyssey Aerobraking
8th AIAA/ASME Joint Thermophysics and Heat Transfer Conference ; 2002 ; Saint Louis, MO, United States
01.01.2002
Preprint
Keine Angabe
Englisch
Plume Modeling and Application to Mars 2001 Odyssey Aerobraking
British Library Conference Proceedings | 2005
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