基于多视线融合的高轨近场感知队形设计

doi:10.12305/j.issn.1001-506X.2023.12.29

摘要/Abstract

摘要：

针对高轨卫星近场态势感知(near-field situation awareness, NSA)问题, 提出了基于多视线(line-of-sight, LOS)融合的多星协同NSA方案, 研究了考虑相对状态估计精度、光照约束等因素的NSA队形设计方法。首先, 基于系统状态方程、测量方程, 以及扩展卡尔曼滤波算法, 构建了多LOS融合的NSA模型; 然后, 通过理论分析获得了LOS夹角越趋近90°, 目标位置估计误差越小的NSA队形设计准则; 进一步考虑光照、有界性相对运动等约束条件, 提出了NSA队形优化策略, 并利用罚函数法对由NSA队形优化问题转换得到的非线性规划问题进行求解。数值仿真验证了所提出的多LOS融合NSA模型、队形设计准则和NSA队形优化策略的有效性。

关键词: 多航天器, 仅测角, 近场态势感知, 队形设计, 非合作目标

Abstract:

For the problem of near-field situation awareness (NSA) of high orbit satellite, this paper proposes a multi-satellite cooperative NSA scheme based on multi-line-of-sight (LOS) fusion and studies the method of configuration design with the consideration of relative state estimation's accuracy and sunlight constraint. Firstly, based on the system state equation, measurement equation, and extended Kalman filter algorithm, the NSA model with multi-LOS fusion is proposed. Secondly, through theoretical analysis, the configuration optimization criterion that the more the LOS angle approaching 90°, the smaller the target position estimation error is proposed. Thirdly, considering the constraints of sunlight and bounded relative motion, the configuration optimization strategy for NSA is proposed, which is transformed to a nonlinear programming problem solved by the penalty function method. Finally, numerical simulations are conducted to validate the effectiveness of the proposed multi-LOS fusion NSA model, configuration optimization design criterion, and configuration optimization strategy of NSA.

Key words: multi-spacecraft, angle-only, near-field situation awareness (NSA), configuration design, non-cooperative target

中图分类号:

V448.2

范大伟, 蔡伟伟, 杨乐平, 张润德. 基于多视线融合的高轨近场感知队形设计[J]. 系统工程与电子技术, 2023, 45(12): 3984-3994.

Dawei FAN, Weiwei CAI, Leping YANG, Runde ZHANG. Multi-line-of-sight fusion based configuration design for near-field situation awareness in high orbit[J]. Systems Engineering and Electronics, 2023, 45(12): 3984-3994.

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轨道根数	主星	从星1	从星2	目标
a/m	42 164 169	42 164 169	42 164 169	42 154 169
e	0	0.000 4	0.000 2	0.000 3
I/(°)	50	50.5	49.9	50.3
Ω/(°)	10	10.5	9.95	10
ω/(°)	20	20.05	20.05	20.3
M/(°)	6	6.045 2	5.997 6	5.946 4

轨道根数	主星	从星1	从星2	目标1
a/m	42 164 169	42 164 169	42 164 169	42 114 169
e	0	0.001 27	0	0
I/(°)	5	5.013 6	4.986 5	5
Ω/(°)	10	10	9.983 8	10
ω/(°)	20	40	0	20
M/(°)	6	-14	26	6

轨道根数	主星	从星1	从星2	目标2
a/m	42 164 169	42 164 169	42 164 169	42 164 169
e	0	0.006 79	0.005 91	0.001
I/(°)	5	5.013 6	4.986 4	5.5
Ω/(°)	10	10	10	10
ω/(°)	20	40	0	20
M/(°)	6	-14	26	6

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