一种基于轨道根数约束的最优制导方法

doi:10.7527/S1000-6893.2018.21680

电子电气工程与控制

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一种基于轨道根数约束的最优制导方法

李超兵, 吕春红, 尚腾

北京航天自动控制研究所, 北京 100854

收稿日期:2017-08-18 修回日期:2018-01-16 出版日期:2018-04-15 发布日期:2018-01-16
通讯作者: 李超兵,E-mail:lcbpku@163.com E-mail:lcbpku@163.com

An optimal guidance method based on orbital element constraints

LI Chaobing, LYU Chunhong, SHANG Teng

Beijing Aerospace Automatic Control Institute, Beijing 100854, China

Received:2017-08-18 Revised:2018-01-16 Online:2018-04-15 Published:2018-01-16

摘要/Abstract

摘要： 针对航天器空间变轨的制导问题，研究了一种基于轨道根数约束的最优制导方法。在地心惯性坐标系下直接建立航天器的最优控制模型，给出了位置速度表达式和协态变量初值之间的关系；进一步，在不约束真近点角的前提下，推导了5个轨道根数的约束方程，并通过对轨道根数和最优控制理论中协态方程的特性分析，获得了另外两个约束方程。协态变量初值可直接通过求解7个完整约束方程组获得，进而得到最优推力方向。仿真验证了所提制导方法的有效性。

关键词: 航天器, 轨道根数, 最优控制, 约束方程, 轨道转移

Abstract: This paper proposes an optimal guidance method based on orbital element constraints, for the guidance problem during orbital transfer of spacecraft. The optimal control model for the spacecraft is established in the earth centered inertial coordinate frame directly. The relationship between expressions for the position and velocity and the initial values of costate variables is then given. Besides, five orbital element constraint equations are derived without constraint on the true anomaly. The other two constraint equations are given based on the analysis of characteristics of orbital elements and costate equations under the optimal control framework, which include the constraint and scale property of the established optimal conditions, respectively. The initial values of costate variables can be obtained by solving the seven complete constraint equations, and the optimal thrust direction can then be given. Simulations demonstrate the effectiveness of the proposed guidance method.

Key words: spacecraft, orbital elements, optimal control, constraint equation, orbit transfer

中图分类号:

V448.13

李超兵, 吕春红, 尚腾. 一种基于轨道根数约束的最优制导方法[J]. 航空学报, 2018, 39(4): 321680-321680.

LI Chaobing, LYU Chunhong, SHANG Teng. An optimal guidance method based on orbital element constraints[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(4): 321680-321680.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

一种基于轨道根数约束的最优制导方法

An optimal guidance method based on orbital element constraints

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