宇航学报

宇航学报 ›› 2017, Vol. 38 ›› Issue (4): 331-337.doi: 10.3873/j.issn.1000-1328.2017.04.001

• 飞行器设计与力学 • 上一篇    下一篇

载人登月绕月自由返回轨道混合-分层优化设计

曹鹏飞，贺波勇，彭祺擘，李海阳   

  1. 1. 国防科学技术大学航天科学与工程学院，长沙410073；2. 载人航天总体研究论证中心，北京100094
  • 收稿日期:2016-11-17 修回日期:2017-02-12 出版日期:2017-04-15 发布日期:2017-04-25
  • 基金资助:

    国家自然科学基金（11372345）；国家重点基础研究发展计划(973计划)（2013CB733100）

Hybrid and Two Level Optimization Design of Circumlunar Free Return Trajectory for Manned Lunar Landing Mission

CAO Peng fei, HE Bo yong, PENG Qi bo, LI Hai yang   

  1. 1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China;
     2. Manned Space System Research Center, Beijing 100094, China
  • Received:2016-11-17 Revised:2017-02-12 Online:2017-04-15 Published:2017-04-25

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摘要：

针对载人登月绕月自由返回飞行任务，提出一种混合-分层轨道优化设计方法。将高精度模型下强约束自由返回轨道设计问题转化为有约束非线性规划求解问题，在此基础上提出一种混合-分层优化求解策略。在双二体模型下利用差分进化算法（DE）与序列二次规划（SQP）相结合的混合优化算法快速求解了满足弱约束条件下的轨道初值问题。采用序列二次规划（SQP）构造两层迭代格式，在高精度模型和强目标约束下对初步设计轨道进行逐层修正。最后，通过仿真测试，文章所述方法的可行性与有效性得到了验证。仿真飞行结果还进一步表明该设计方法具有求解精度高、收敛速度快等优点，为探月工程任务提供了一种有效的轨道设计工具。

关键词: 载人登月, 绕月自由返回飞行, 轨道设计, 混合-分层优化

Abstract:

An optimization method of trajectory design is established in this paper for manned lunar landing circumlunar free-return flight mission. The problem of designing free-return trajectory with multiple constrains under the high precise dynamic model is converted to the nonlinear bounded optimization problems. A solving strategy consisting of hybrid and two-level optimization algorithm is then proposed. Under the double two-body model, the initial trajectory with the weak constrain conditions is obtained by hybrid optimization algorithm which consists of differential evolution (DE) method and sequence quadratic program (SQP) method based on the patched-conic approach. Then a two-level initial trajectory corrective measure based on the sequence quadratic program is applied to obtain the final solution satisfying the strong engineering constrains under the high precise dynamic model. Finally, the reliability and effectiveness of the approach proposed in this paper are demonstrated by the simulation tests, and the results indicate that the proposed method has excellent convergence performance and high precision, thus can be a useful tool for manned lunar orbit design.

Key words: Manned lunar landing, Circumlunar free return flight, Trajectory design, Hybrid and two level optimization

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