考虑导弹1阶驾驶仪的近似最小加速度峰值导引律

doi:10.3969/j.issn.1000-1093.2018.01.009

摘要/Abstract

摘要： 为避免操纵能力受限的导弹在实现大落角约束时出现控制饱和问题，提出一种考虑系统惯性且加速度峰值近似最小的解析形式组合导引律。通过设计切换点以及后段惯性补偿项，该组合导引律由圆弧-直线导引律和带1阶惯性补偿项的多项式导引律组合而成；通过数学推导，证明了切换点必然存在，且组合导引律的加速度峰值出现在切换点；结合前段圆弧-直线导引律对加速度峰值的优化能力，实现了组合导引律的近似最优性。仿真结果表明：组合导引律的加速度在切换点后不再增大，且落角约束得到了满足；与数值最优解的比较进一步验证了该组合导引律的近似最优性。

关键词: 导弹, 最小加速度峰值, 落角约束, 最优控制, 1阶驾驶仪, 圆弧-直线导引律

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

中图分类号:

TJ765.2⁺2

郭琨，杨树兴. 考虑导弹1阶驾驶仪的近似最小加速度峰值导引律[J]. 兵工学报, 2018, 39(1): 83-93.

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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