基于最优误差动力学的变速导弹飞行路程控制制导律

doi:10.7527/S1000-6893.2022.26909

Abstract

Abstract:

To solve the problem of performance degradation of current impact time control guidance based on constant speed assumption in practical application， a feasible flying range control guidance scheme with time-varying speed is proposed in this paper. The relative motion equation of the missile against the stationary target in the arc-length domain is derived based on the classical differential geometric curve principle， which reduces the influence of time-varying speed on the relative motion of missile and target. Furthermore， the exact solution for the range-to-go guided by pure proportional navigation is derived using the Gaussian hypergeometric function. On this basis， a flying range control guidance law is designed with the optimal error dynamics method， and the effectiveness of the proposed guidance is verified by simulation.

Key words: classical differential geometric curve theory, varying-speed missile, Gaussian hypergeometric function, optimal error dynamics, flying range control

CLC Number:

V448.2

Yuanhe LIU, Kebo LI, Shaoming HE, Yangang LIANG. Flying range control guidance for varying⁃speed missiles based on optimal error dynamics[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(7): 326909-326909.

Figures/Tables 9

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References 24

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场景	制导律	时间误差/s	脱靶量/m	速度增量/（m∙s^-1）
1	OED-FRCG	-1.5×10^-3	8.1×10^-16	1 026.7
	OED-ITCG	-1.6×10^-3	2.2×10^-15	1 026.7
	BPN-ITCG	-2.0×10^-3	7.6×10^-6	1 064.0
2	OED-FRCG	-1.7×10^-3	3.3×10^-15	931.8
	OED-ITCG	-2.3	8.4×10^-4	1 182.9
	BPN-ITCG	9.8×10^-2	8.2×10^-6	1 016.8

Flying range control guidance for varying⁃speed missiles based on optimal error dynamics

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