火星探测器气动外形/弹道一体化多目标优化

doi:10.7527/S1000-6893.2014.0011

Abstract

Abstract:

An integrated multiobjective optimization design framework is developed for the conceptual design of the Mars explorer, in which the aerodynamic shape, trajectory and the condition of parachute deployment are considered simultaneously. The three degree of freedom motion equation is established; the modified Newtonian flow theory is employed to calculate the aerodynamic parameters, which is suitable to the sphere-cone shape with large half cone angle; the Sutton-Graves equation are adopted to compute the stagnation heat flux. In the integrated multiobjective optimization problem, the three optimization objectives are parachute deployment altitude, total heat and volumetric efficiency, which are solved by using the multiobjective evolutionary algorithm based on decomposition (MOEA/D). The numerical simulation results show that the proposed method can obtain multiple Pareto optimal solutions whose three objectives are all better than those of baseline design, and it can be used in the conceptual design of Mars explorer.

Key words: Mars explorer, multiobjective optimization, multiobjective evolutionary algorithm based on decomposition, aerodynamic shape, conceptual design

CLC Number:

V421.1

FENG Zhiwei, ZHANG Qingbin, GAO Xinglong, TANG Qian'gang, YANG Tao. Aerodynamic Shape and Trajectory Integrated Multiobjective Optimization for Mars Explorer[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(9): 2461-2471.

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Aerodynamic Shape and Trajectory Integrated Multiobjective Optimization for Mars Explorer

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