基于最优脉冲的空间抵近行为模式可达性分析

doi:10.12305/j.issn.1001-506X.2026.02.25

Abstract

Abstract:

In orbital games, the ability to predict the reachability of an approaching non-cooperative target’s behavior patterns allows the predictor to seize the initiative. To address the reachability problem of such patterns, a reachability analysis method for space-proximity behavior patterns based on optimal impulses is proposed. Given the target’s maneuverability, optimal-impulse estimation evaluates whether each pattern lies within the reachable set, thereby enabling reachability analysis of proximity behavior patterns. Combined with more intelligence information, the spacecraft can be enabled to make decision earlier and acquire a strategic advantage in games. Simulation results for four representative patterns—intercept, fly-by, fly-around, and hover—demonstrate that the proposed method can accurately analyze the possibility of the target’s future behavior patterns.

Key words: orbital game theory, non-cooperative targets, behavior pattern reachability analysis, optimal impulse estimation

CLC Number:

V 19

Jiahui FANG, Kebo LI, Yangang LIANG. Reachability analysis of space proximity behavior patterns based on optimal impulse[J]. Systems Engineering and Electronics, 2026, 48(2): 652-659.

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优化目标	行为模式	脉冲数	优化变量	约束条件	终端相对位置速度
脉冲之和$\displaystyle\sum\limits_i {\left\\| {\Delta {{\boldsymbol{v}}_i}} \right\\|} $	拦截	1	等待时长${t_{{\text{wait}}}}$ 转移时长${t_{{\text{transfer}}}}$	${t_{{\text{wait}}}} + {t_{{\text{transfer}}}} \leqslant {t_{\max }}$	均为0
	绕飞/掠飞	1	等待时长${t_{{\text{wait}}}}$ 漂移量${l_m}$	$\begin{gathered} {t_{{\text{wait}}}} \leqslant {t_{\max }} \\ {l_m} \in \left[ {{l_{\min }},{l_{\max }}} \right] \\ \end{gathered} $	$\left[ {{x_0}}\quad {{y_0}}\quad 0\quad 0\quad {\Delta {v_y}}\quad {{{\dot z}_0}} \right]$ 其中$\Delta {v_y}$满足式（3）
	悬停	1或2	等待时长${t_{{\text{wait}}}}$ 悬停距离${y_{c0}}$ 悬停椭圆半长轴$2b$	$\begin{gathered} {t_{{\text{wait}}}} \leqslant {t_{\max }} \\ 2b - \left\| {{y_{c0}}} \right\| \lt 0 \\ \end{gathered} $	$ \left[ 0\quad {{y_0}}\quad 0\quad {\dfrac{{n{y_0}}}{2}}\quad 0\quad {{{\dot z}_0}} \right] $

航天器	半长轴a/km	偏心率e	倾角i/（°）	升交点赤经Ω/（°）	近地点纬度幅角ω/（°）	真近点角f/（°）
红方	42166.127	0.000504	0.1	78.265	271.690	302.395
蓝方	42220	0	0.11	89.626	0	203.396

行为模式	脉冲冲量/（m/s）	时间/h
拦截	1.0170	29.3367
掠飞	—	—
绕飞	11.5940	14.3453
悬停	2.0048	26.9356

误差大小	拦截		掠飞		绕飞		悬停
误差大小	实现所需最小脉冲/(m/s)	相对误差/%	实现所需最小脉冲	相对误差	实现所需最小脉冲/(m/s)	相对误差/%	实现所需最小脉冲/(m/s)	相对误差/%
[0 m, 0 m/s]	1.017 0	—	—	—	11.594 0	—	2.004 8	—
[10¹ m, 10^—3 m/s]	1.016 5	0.049 2	—	—	11.590 5	0.030 2	1.961 5	2.159 8
[10² m, 10^—2 m/s]	1.021 2	0.413 0	—	—	11.424 3	1.463 7	2.119 9	5.741 2
[10³ m, 10^—1 m/s]	1.096 0	7.767 9	—	—	9.943 1	14.239 3	2.274 7	13.462 7

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Reachability analysis of space proximity behavior patterns based on optimal impulse

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