大气层外自旋拦截器末制导控制研究

Study on Final Guidance Control of Spinning Interceptor Missile

对大气层外自旋拦截器的末制导控制进行了研究。考虑变质量后质心位置变化产生的扰动力矩对拦截器姿态的干扰,以及弹体自旋运动对直接力分量的影响,建立了拦截器运动模型和相对运动方程。基于现有的脉冲发动机,根据理论所需冲量确定脉冲发动机数和相应的最佳布局,以及等效控制力大小与方向。用衰减记忆滤波算法提取高精度视线转率,选用比例导引律,相对距离变化率采用近似计算,设定视线转率门限避免发动机点火过于频繁。设计了包括脉冲发动机点火策略的算法,可在满足脱靶量要求前提下最大限度减少脉冲发动机消耗和对导弹姿态角的影响。仿真结果表明:该法能有效实现大气层外自旋拦截器在末制导段的精确制导控制。

The final guidance law of spinning extra-atmospheric interceptor was studied in this paper.While the disturbance torque to influence the interceptor attitude caused by the centroid excursion and the effect of the spinning on the direct force were under consideration,the motion model and relative motion equation of the interceptor were established.Based on the present pulse thruster,the thruster number and optimal layout as well as the magnitude and direction of the equivalent thruster were determined according to the total pulse.The high accuracy line-of-sight rate was gained by attenuation memory filter.The proportional navigation guidance law was applied in which the approximate calculation was used for relative distance changing rate and the threshold of LOS rate was set to avoid the thruster opening too frequently.The amiable guidance law was designed.The method proposed could reduce the effect of the thruster on the interceptor attitude under the situation that the requirement of miss distance was satisfied.The simulation results showed the this method could realize the high accuracy guidance control for the spinning extra-atmospheric interceptor in the final phase.