基于速度追踪法的旋转导弹空中截获制导方法研究

Study on Lock-on-after-Launch Guidance for Rolling Airframe Missiles Based on Pursuit Guidance Law

为保证旋转导弹导引头尽早截获目标并能适应导引头截获距离的变化,对一种基于速度追踪法的空中截获制导方法进行了研究。将速度追踪导引律引入中制导,给出了制导律。对速度追踪法的前置角收敛特性和弹道收敛性进行分析,证明了速度追踪法用于空中截获制导时的有效性。讨论了速度追踪系数的取值方法,以及其与前置角稳态误差的关系,给出了制导参数的优化方法,解决了初制导段前置角振荡及导引头截获距离附近前置角稳定性协调问题。仿真结果表明:将速度追踪法引入空中截获制导,既保证了弹目距离收敛,又能尽早满足导引头角度截获条件,适应不同拦截方向导引头截获距离变化造成的截获困难,利于导弹快速进入末制导。提出的制导算法适于大离轴角发射和目标机动情况,简单易行,性能良好。

To ensure quick lock-on-after-launch and suitability for various acquisition distance of seeker for rolling airframe missile,a lock-on-after launch guidance method based on pursuit guidance law was studied in this paper.The pursuit guidance law was introduced into mid-course guidance.The analysis on convergence of leading angle and trajectory proved the effectiveness of pursuit guidance law adopted in the acquisition.The determination method of pursuit parameter and the relationship with the stable error of the leading angle were discussed.The optimal method of the guidance parameter was given,which solved the oscillatory of the leading angle in the initial guidance course and the stable coordination of the leading angle around capture distance.The simulation results show that it can ensure the convergence of missile-target distance and meet the condition for the seeker's angle interception quickly,which is able to adapt the various interception distance caused by different interception direction and is benefit for the terminal guidance.The proposed method is suitable for launching with large off-axis angle and maneuvering target,which is simple and feasible and has good performance.