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
2002
11 pages
Report
No indication
English
Extraterrestrial Exploration , Astronomy & Astrophysics , Computational fluid dynamics , Aerobraking , 2001 mars odyssey , Computerized simulation , Rocket exhaust , Flow distribution , Mathematical models , Monte carlo method , Rocket engines , Applications programs(Computers) , Navier-stokes equation , Data bases
Plume Modeling and Application to Mars 2001 Odyssey Aerobraking
British Library Conference Proceedings | 2005
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