防空导弹尾追拦截目标的遭遇点预测方法

为充分发挥导弹武器系统的全向拦截能力,防空导弹需要面对拦截发射时即处于尾追逃逸态势目标的问题。结合防空导弹任务特点,设计了一种兼顾迎击、尾追拦截态势的遭遇点预测方法。根据导弹与目标在发弹时刻和拦截过程中的相对运动关系,建立常规迎击态势下的遭遇点预测模型。针对尾追拦截的特殊情况,分析预测模型对弹目相对运动关系描述的适用性,并进一步研究目标初始参数对预测模型收敛性的影响。在此基础上优化运动几何关系描述模型,结合收敛条件设计迭代算法,形成尾追拦截态势下遭遇点的预测方法。该方法修正了目标穿越发射点上空引起的模型适用性问题。仿真结果表明:迭代算法对迎击、尾追目标态势均快速收敛,预测精度满足工程应用要求,为导弹全向拦截时的遭遇点预测提供了有效的解决途径。

Method of Impact Point Forecast of Air Defense Missile for Tail-Chase Target Interception

In order to take omni-directional interception capability of missile weapon system into full play, air-defense missiles are required to intercept tail-chase targets at the moment of launching. This paper provides a method of impact point forecast which takes account of both head-on and tail-chase attacking targets, considering the mission characteristics of air-defense missile. Firstly, the paper establishes a model of normal head-on attacking target according to the relative motion relation between the missile and the target during the phase of lunching and interception. Then, according to the special case of tail-chase interception, the paper analyses the applicability of impact point forecast model to the relative motion relation between the missile and the target, and studies the effect of target initial parameter on model convergence. On this basis, geometric relation model of motion is optimized and impact point forecast of intercepting a tail-chase target is put forward by means of designing an iterative algorithm considering the convergence condition. This method modifies the model adaptability in the case of the target passing over the launching point. The simulation results show that the iteration converges fast both in head-on and tail-chase attacking targets. The accuracy of the forecast model satisfies the requirement of engineering application and the method provides an effective approach of impact point forecast for omni-directional interception of missile.