主动防御非奇异终端滑模协同制导律

由于在大气层外突防的弹道导弹机动能力很小易被导弹防御系统拦截，因此研究提高突防概率的有效手段具有重要的实用价值。提出基于主动防御方式的分阶段非奇异终端滑模协同制导律，防御导弹的制导过程分为阶段1和阶段2两个阶段。阶段1设计基于视线三角制导策略的制导律，防御导弹将自身控制在目标和拦截导弹的视线上，能有效降低防御导弹需用过载，对相对运动模型进行近似，带来的误差比较小；阶段2设计零化视线转率策略的制导律，使用更加精确的相对运动模型，避免了阶段1近似建模在制导后期带来的较大误差。仿真计算结果验证了该制导律的有效性。

Active Defense Nonsingular Terminal Sliding Mode Cooperative Guidance Law

The ballistic missiles are easily intercepted by the missile defense systems due to the absence of maneuverability in exo-atomosphere. It is important to design an effective guidance law to improve the success penetration rate of ballistic missile. An active defense nonsingular terminal sliding mode cooperative guidance law is presented. In ballistic missile active defense scenarios, one or more defending missiles, named defenders, accompany the ballistic missile to intercept the incoming interceptor missiles launched from the missile defense systems. The guidance process for the defenders is divided into two phases: Phase 1 and Phase 2. For Phase 1, a line of sight (LOS) based guidance law is designed, by which the defending missile positions itself on LOS between the ballistic missile and the interceptor missile. In this phase, the proposed guidance law can notably reduce the needed maneuverability of defending missile. To simplity the designing, the guidance law uses an approximate relative motion model, of which accuracy is acceptable in Phase 1. For Phase 2, a guidance law based on LOS angular velocity nullifying strategy is proposed. In this phase, the proposed guidance law uses more accurate relative motion models and avoids the increased errors induced by the approximate relative motion model in Phase 2. Simulation results show the high performance of the guidance laws.