卫星编队脉冲机动维持控制与策略

doi:10.12305/j.issn.1001-506X.2023.08.28

摘要/Abstract

摘要：

针对近地圆轨道卫星编队维持问题, 开展了脉冲控制方案与维持控制策略研究，并搭建了仿真环境进行验证。根据相对轨道根数(relative orbital elements, ROEs)的状态转移方程，推导了各ROEs元素在J₂摄动下的漂移速率，并针对编队构型受到空间摄动的破坏问题，提出了两种不同的编队脉冲控制方案和维持策略。基于空间圆编队长期维持需求，建立了包括高精度轨道递推算法的任务仿真环境，从脉冲消耗与控制误差对提出的方案策略进行了分析讨论，验证了脉冲方案与维持策略的可行性。仿真结果表明，所提出的脉冲控制方案与维持策略具有较高的有效性及可靠性，可用于未来空间编队飞行任务。

关键词: 卫星编队, J₂摄动, 脉冲控制, 维持策略, 任务仿真

Abstract:

In view of the satellites formation maintenance issue on low near-earth orbit, the impulsive control solution and maintenance control strategy are studied, while the simulation environment is built for further verification. According to the state transition equation of relative orbital elements(ROEs), the drift rates of each element of ROEs caused by J₂ perturbation are derived. Solutions of impulse control and two different maintenance strategies are proposed to solve the problem of formation configuration destruction caused by perturbation. Based on the long-term maintenance requirement of satellites space formation, a task simulation environment is established for satellites formation mission including high-precision orbit propagation algorithm. The feasibility of the proposed impulsive solutions and maintenance strategies are verified, which are analyzed and discussed in term of impulsive consumption and control error. The simulation result shows that the proposed impulsive control solution and maintenance strategy have high effectiveness and reliability, which could be applied to future space formation flight missions.

Key words: satellites formation, J₂ perturbation, impulsive control, maintenance strategy, mission simulation

中图分类号:

刘幸川, 陈丹鹤, 徐根, 廖文和. 卫星编队脉冲机动维持控制与策略[J]. 系统工程与电子技术, 2023, 45(8): 2533-2545.

Xingchuan LIU, Danhe CHEN, Gen XU, Wenhe LIAO. Control and strategy for satellites formation maintenance with impulsive maneuver[J]. Systems Engineering and Electronics, 2023, 45(8): 2533-2545.

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参数	$ a_c \delta \dot{e}_x$	$ a_c \delta \dot{e}_y$	$ a_c \delta \dot{i}_y$
漂移速率/(m/s)	-8.0×10^-4	6.0×10^-4	0.001 4
Δ=100 m/轨	21.52	28.70	11.95
Δ=150 m/轨	32.29	43.05	17.93

编号	a_cδα/m	漂移速率/(×10^-4 m/s)
卫星1	[0, 0, 469.84, 171.01, -296.19, 813.79]^T	[0, 0, 1.060, -2.912, 0, -5.415]^T
卫星2	[0, 0, -383.02, 321.39, -556.67, -663.41]^T	[0, 0, 1.992, 2.374, 0, -10.177]^T
卫星3	[0, 0, -86.82, 492.40, 852.86, -150.38]^T	[0, 0, -3.052, 0.538, 0, 15.593]^T

仿真算例	算例描述
仿真算例	T_n∶T_c	控制方法	控制策略
算例0	1∶1	方法1	无预估漂移量
算例1	1∶1	方法1	策略1
算例2	1∶1	方法2	策略1
算例3	2∶1	方法1	策略1
算例4	2∶1	方法2	策略1
算例5	2∶1	方法1	策略2
算例6	2∶1	方法2	策略2

编号	参数	理论速率/(×10^-4 m/s)	仿真速率/(×10^-4 m/s)	误差/%
卫星1	$ a_c \delta \dot{e}_x$	1.060	1.037	2.217
	$ a_c \delta \dot{e}_y$	-2.912	-2.957	1.521
	$ a_c \delta \dot{i}_x$	0	-0.020	-
	$a_c \delta \dot{i}_y $	-5.415	-4.973	8.888
卫星2	$ a_c \delta \dot{e}_x$	1.992	2.023	1.532
	$ a_c \delta \dot{e}_y$	2.374	2.339	1.496
	$ a_c \delta \dot{i}_x$	0	0.017	-
	$a_c \delta \dot{i}_y $	-10.177	-9.356	8.775
卫星3	$ a_c \delta \dot{e}_x$	-3.052	-3.016	1.193
	$ a_c \delta \dot{e}_y$	0.538	0.518	3.720
	$ a_c \delta \dot{i}_x$	0	0.003	-
	$a_c \delta \dot{i}_y $	15.593	14.432	8.044

总脉冲值	卫星1	卫星2	卫星3
算例0	0.659 75	0.973 47	1.335 44
算例1	0.686 58	1.015 52	1.395 67
算例2	0.524 82	0.853 43	1.231 37
算例3	0.684 86	1.013 00	1.395 88
算例4	0.516 01	0.838 94	1.210 06
算例5	0.698 28	1.034 22	1.425 82
算例6	0.535 81	0.871 21	1.257 99