利用径向力平衡飞行控制的航天器高精度轨道捕获方法
2024,46(2):27-35
孟云鹤
中山大学 人工智能学院, 广东 珠海 519082，mengyh7@mail.sysu.edu.cn
侯佳睿
中山大学 物理与天文学院, 广东 珠海 519082，503599729@qq.com
罗宇飞
中山大学 人工智能学院, 广东 珠海 519082
中山大学 人工智能学院, 广东 珠海 519082，mengyh7@mail.sysu.edu.cn
侯佳睿
中山大学 物理与天文学院, 广东 珠海 519082，503599729@qq.com
罗宇飞
中山大学 人工智能学院, 广东 珠海 519082
摘要：
为实现对探测器轨道形状与高度的精准调整,提出一种径向力平衡飞行的航天器连续推力控制新方法。建立连续推力平衡飞行的动力学极坐标模型,并推导出特殊条件下的解析轨道解,进一步分析边值条件,给出连续推力的控制律。利用这一平衡飞行控制理论,构建轨道捕获的最优控制策略。考虑推力器的推力水平,通过一次或多次的控制过程,实现对轨道形状、轨道高度及轨道相位的综合调整。数值仿真表明:利用平衡飞行的轨道控制方法,配置微小推力器的空间引力波探测器可以实现高精度的轨道捕获；该方法具有控制过程可解析、计算量小、简便、实用等特点。
为实现对探测器轨道形状与高度的精准调整,提出一种径向力平衡飞行的航天器连续推力控制新方法。建立连续推力平衡飞行的动力学极坐标模型,并推导出特殊条件下的解析轨道解,进一步分析边值条件,给出连续推力的控制律。利用这一平衡飞行控制理论,构建轨道捕获的最优控制策略。考虑推力器的推力水平,通过一次或多次的控制过程,实现对轨道形状、轨道高度及轨道相位的综合调整。数值仿真表明:利用平衡飞行的轨道控制方法,配置微小推力器的空间引力波探测器可以实现高精度的轨道捕获；该方法具有控制过程可解析、计算量小、简便、实用等特点。
基金项目：
国家自然科学基金资助项目(61673390)；广东省基础与应用基础研究重大资助项目(2019B030302001)
国家自然科学基金资助项目(61673390)；广东省基础与应用基础研究重大资助项目(2019B030302001)
High-precision orbit capture method of spacecraft based on radialequilibrium flight control
MENG Yunhe
School of Artificial Intelligence, Sun Yat-sen University, Zhuhai 519082, China,mengyh7@mail.sysu.edu.cn
HOU Jiarui
School of Physics and Astronomy, Sun Yat-sen University, Zhuhai 519082, China,503599729@qq.com
LUO Yufei
School of Artificial Intelligence, Sun Yat-sen University, Zhuhai 519082, China
School of Artificial Intelligence, Sun Yat-sen University, Zhuhai 519082, China,mengyh7@mail.sysu.edu.cn
HOU Jiarui
School of Physics and Astronomy, Sun Yat-sen University, Zhuhai 519082, China,503599729@qq.com
LUO Yufei
School of Artificial Intelligence, Sun Yat-sen University, Zhuhai 519082, China
Abstract：
In order to acquire the accurate adjustment of the orbit shape and height of the detector, a new method of spacecraft continuous thrust control based on radial force equilibrium flight was proposed. The dynamic polar coordinate model of continuous thrust equilibrium flight was established, and the analytical orbit solution under special conditions was derived, the boundary conditions were further analyzed, and the control law of continuous thrust was given. Using this equilibrium flight control theory, the optimal control strategy for orbit capture can be constructed. Considering the thrust level of thrusters, the integrated adjustment of orbit shape, orbit height and orbit phase can be adjusted through one or more control processes. Numerical simulations show that the space gravitational wave detector with micro thruster can achieve high-precision orbit capture by using the orbit control method of equilibrium flight. This method has the advantages of analytical control process, small calculation, simple and practical.
In order to acquire the accurate adjustment of the orbit shape and height of the detector, a new method of spacecraft continuous thrust control based on radial force equilibrium flight was proposed. The dynamic polar coordinate model of continuous thrust equilibrium flight was established, and the analytical orbit solution under special conditions was derived, the boundary conditions were further analyzed, and the control law of continuous thrust was given. Using this equilibrium flight control theory, the optimal control strategy for orbit capture can be constructed. Considering the thrust level of thrusters, the integrated adjustment of orbit shape, orbit height and orbit phase can be adjusted through one or more control processes. Numerical simulations show that the space gravitational wave detector with micro thruster can achieve high-precision orbit capture by using the orbit control method of equilibrium flight. This method has the advantages of analytical control process, small calculation, simple and practical.
收稿日期：
2022-08-03
2022-08-03
