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针对新型战术弹道导弹(TBM)和智能巡航导弹等具有高机动性的拦截目标,应用控制受限的非线性对策模型,提出非线性微分对策制导律,并分析了零脱靶量拦截所容许的初始航向误差。目标和拦截弹间的相对运动是非线性的,采用传统线性化模型建立的拦截制导律会因为线性化而带来误差。提出的制导律是在保持拦截弹和目标的非线性运动学关系的基础上,把拦截弹航向误差作为性能指标,基于反馈线性化的思想,应用最优控制理论建立的。应用该制导律研究了在迎击拦截、追击拦截和阻击拦截3种拦截方式下实现零脱靶量拦截的容许初始航向误差,分析结果表明减小相对运动速度、提高拦截弹的机动加速度可以增加容许的初始航向误差。同时,当拦截弹具有速度优势时,目标的初始前置角接近90°或采用追击拦截可以允许较大的初始航向误差。
Aiming at the highly maneuverable intercept targets such as new tactical ballistic missiles (TBMs) and intelligent cruise missiles, a nonlinear control strategy for nonlinear differential game is proposed by applying a nonlinear control model with limited control. The initial allowable initial values of zero miss distance intercept Heading error. The relative motion between the target and the interceptor is non-linear, and the interception guidance law established by the traditional linearization model will bring errors due to the linearization. The proposed guidance law is based on the nonlinear kinematics of the interceptor and the target. The guidance error of the interceptor is taken as the performance index. Based on the feedback linearization theory, the optimal control theory is established. The guidance law is applied to study the allowable initial heading error of the zero-miss-interception under the three types of intercepting intercept, pursuit intercept and interception interception. The analysis results show that reducing the relative movement speed and increasing the maneuvering acceleration of the interceptor can increase the allowable Initial heading error. In the meantime, when the interceptor projectile has a speed advantage, the target’s initial pre-steer angle is close to 90 ° or chase interception allows a larger initial heading error.