Spacecraft Aerodynamics and Trajectory Simulation During Aerobraking

ZHANG Wen-pu; HAN Bo; ZHANG Cheng-yi

doi:10.3879/j.issn.1000-0887.2010.09.002

Volume 31 Issue 9

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ZHANG Wen-pu, HAN Bo, ZHANG Cheng-yi. Spacecraft Aerodynamics and Trajectory Simulation During Aerobraking[J]. Applied Mathematics and Mechanics, 2010, 31(9): 1016-1026. doi: 10.3879/j.issn.1000-0887.2010.09.002

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Spacecraft Aerodynamics and Trajectory Simulation During Aerobraking

doi: 10.3879/j.issn.1000-0887.2010.09.002

Institute of Fluid Engineering, School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, P. R. China

Received Date: 1900-01-01
Rev Recd Date: 2010-07-09
Publish Date: 2010-09-15

Abstract

Abstract

The direct simulation Monte Carlo method(DSMC)was used to simulate rarefied aerodynamic characteristics during the aerobraking process of NASA Mars Global Surveyor(MGS)spacecraft.The research focused on the flowfield and aerodynamic characteristics distribution under various freestream densities,and the variation regularity of aerodynamic coefficients was analyzed.Also,an aerodynamics-aero-heating-trajectory integrative simulation model was developed to preliminarily calculate the aerobraking orbit transfer by combining DSMC technique and classical kinematics theory.Results show that the effect of planetary atmospheric density,spacecraft yaw and pitch attitudes on the spacecraft aerodynamics is significant.The numerical results are in good agreement with the existing results in the literature.The aerody-namics-aeroheating-trajectory integrative simulation model is proved to be able to simulate the orbit transfer in the complete aerobraking mission,and current results of spacecraft trajectory show that the aero-braking maneuvers give good performance of attitude control.
- aerobraking,
- rarefied gas dynamics,
- DSMC,
- Mars spacecraft,
- aerodynamic characteristic,
- trajectory simulation

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References(13)

References

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