一种基于轨迹预测的滑翔制导炮弹时间约束末制导律扩展方法

An Extended Time-constrained Terminal Guidance Law forGliding-guided Projectiles Based on Trajectory Prediction

针对滑翔制导炮弹末制导过程中的攻击角度与攻击时间控制问题,为简化制导律设计、方便工程应用,提出了一种将现有高性能非时间约束制导律扩展为可处理时间约束形式的方案。该方案以非线性导引模型为基础、现有制导律作用下的弹丸飞行轨迹为参考轨迹,通过为弹丸预设合理的飞行时间并结合轨迹预测的方法,将滑翔制导炮弹的末制导过程分为2个阶段。第一阶段制导炮弹在扩展后的制导律作用下飞行,通过增加参考轨迹曲率、延长弹丸飞行时间的方式使攻击时间误差在有限时间内收敛至零;第二阶段制导炮弹在原始制导律作用下飞行,直至命中目标以满足脱靶量与攻击角约束。同时,通过不同工况下的大量仿真,研究了设计参数的取值范围对第一阶段中弹丸攻击时间误差收敛性能的影响。该扩展方案的推导过程无需现有制导律的显式表达,具有一定的通用性。研究结果表明:通过合理的参数设置,扩展方案可以在现有制导律的基础上实现攻击时间控制,且制导指令光滑,需用过载较小,符合作战任务要求。

Addressing the challenge of controlling impact angle and time during the terminal guidance phase of gliding-guided projectiles,a scheme was proposed to simplify the guidance law design process and facilitate engineering applications.This scheme extends existing high-performance,non-time-critical guidance laws to accommodate time constraints.Based on a nonlinear guidance model and using the projectile’s flight trajectory under existing guidance laws as a reference,the proposal divided the terminal guidance phase into two stages.In the first stage,the projectile flies under the extended guidance law,adjusting the reference trajectory’s curvature and extending flight time to converge the impact time error to zero within a finite period.In the second stage,the original guidance law takes over until the target is hitted,ensuring compliance with miss distance and impact angle constraints.Extensive simulations were carried out under various conditions.The impact of design parameter ranges on the convergence performance of impact time error in the first stage was studied.The derivation of this extended scheme does not require an explicit expression of the existing guidance laws,offering a degree of universality.The results indicate that with appropriate parameter settings,the extended scheme can achieve impact time control on the basis of existing guidance laws,with smooth guidance commands and minimal required overload,meeting the operational requirements.