航空学报 > 2014, Vol. 35 Issue (9): 2461-2471   doi: 10.7527/S1000-6893.2014.0011

火星探测器气动外形/弹道一体化多目标优化

丰志伟, 张青斌, 高兴龙, 唐乾刚, 杨涛   

  1. 国防科学技术大学 航天科学与工程学院, 湖南 长沙 410073
  • 收稿日期:2013-12-05 修回日期:2014-03-05 出版日期:2014-09-25 发布日期:2014-03-07
  • 通讯作者: 张青斌,Tel.:0731-84576436 E-mail:qingbinzhang@sina.com E-mail:qingbinzhang@sina.com
  • 作者简介:丰志伟 男,博士研究生。主要研究方向:飞行器多目标优化设计。Tel:0731-84576436 E-mail:fzwnudt@163.com;张青斌 男,博士,副教授,硕士生导师。主要研究方向:飞行器多目标优化设计。Tel:0731-84576436 E-mail:qingbinzhang@sina.com
  • 基金资助:

    国家自然科学基金(51375486)

Aerodynamic Shape and Trajectory Integrated Multiobjective Optimization for Mars Explorer

FENG Zhiwei, ZHANG Qingbin, GAO Xinglong, TANG Qian'gang, YANG Tao   

  1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
  • Received:2013-12-05 Revised:2014-03-05 Online:2014-09-25 Published:2014-03-07
  • Supported by:

    National Natural Science Foundation of China (51375486)

摘要:

针对火星探测器概念设计阶段的需求,提出了融合气动外形、弹道和开伞条件的一体化多目标优化设计方法。首先建立了火星探测器进入段三自由度弹道运动方程,基于修正牛顿理论推导了适用于具有较大半锥角球锥外形的气动参数估算模型,采用Sutton-Graves公式计算了驻点热流密度。以开伞高度、总吸热量和容积率为目标函数建立了火星探测器气动外形/弹道一体化多目标优化模型,采用基于分解的多目标进化算法(MOEA/D)进行求解计算并与参考设计进行了对比。数值结果表明:多目标优化方法提供多个三目标均优于参考设计的Pareto最优解,为火星探测器的概念设计提供了一定的参考依据。

关键词: 火星探测器, 多目标优化, 基于分解的多目标进化算法, 气动外形, 概念设计

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

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