Near-minimax Acceleration Guidance Law with First-order Autopilot

doi:10.3969/j.issn.1000-1093.2018.01.009

Abstract

Abstract: A hybrid near-minimax acceleration guidance law for first-order lag systems is proposed to avoid the control saturation of missiles with control limits and large impact angle constraint. By designing the switch point and the lag compensation term in the latter phase, the proposed guidance law is composed of a circular arc-straight line guidance phase and a polynomial guidance phase with first-order autopilot compensation. It is proved by mathematical deduction that the switch point must exist and the peak acceleration of the whole trajectory appears at the switch point. Combining the optimization ability of the circular arc-straight line guidance law, the near-optimality of the hybrid guidance law is obtained. Simulated results show that the acceleration does not increase after the switch point, and the impact angle constraint is satisfied. Comparisons with the numerical optimal solutions further verify the near-optimality of the hybrid guidance law. Key

Key words: missile, minimaxacceleration, impactangleconstraint, optimalcontrol, first-orderautopilot, circulararcandstraightlineguidancelaw

CLC Number:

TJ765.2⁺2

GUO Kun， YANG Shu-xing. Near-minimax Acceleration Guidance Law with First-order Autopilot[J]. Acta Armamentarii, 2018, 39(1): 83-93.

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第39卷
第1期2018 年1月兵工学报ACTA
ARMAMENTARIIVol.39No.1Jan.2018

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