一种适用于大气层外动能拦截器的末制导律

A Terminal Guidance Law for Exoatmospheric Kill Vehicle

针对大气层外动能拦截器拦截问题,设计了一种简单有效的末制导律。推导出计算零控脱靶量一种新的解析表达式,由于在推导过程中考虑了两飞行器间重力差影响,得出的表达式相对于将两飞行器重力差简化为零重力模型得到的解析式具有更高的精度;根据平行接近法原理利用此表达式推导出一种简单的末制导律;详细介绍了脉宽调制(PWM)式实现变推力控制的方案,仿真中在考虑发动机工程约束的情况下,利用PWM技术对提出的制导律进行验证。对机动目标进行拦截仿真显示,提出的制导律在取得良好拦截精度的同时表现出较强的鲁棒性。

A simple and effective terminal guidance law for exoatmospheric interceptor, which uses a kinetic kill vehicle for a direct hit kill, is proposed. Firstly, a new analytic expression of zero effort miss is derived, because the difference of gravity for interceptor and ballistic missile is taken into account, so the expression has good fidelity as compared with that in the case where gravitational accelerations acting upon both vehicles are equal. A terminal guidance law is designed using the zero effort miss steering. The thrusters with variable thrust by pulse-width modulated （PWM） technique are examined. The guidance law is proved using PWM with engineering constraints. Simulation results show that the presented guidance law guarantees perfect intercept for maneuvering target and has goodlau robustness.