基于直接力控制的导弹高精度末端导引方法研究

采用直接力控制的拦截导弹具有自身控制不连续、目标机动能力强、要求直接命中等特点，因此需要一种精度高、适应性强耳较睿脉冲发动机的导引律。以某型末端采用直接侧向力控制的反导导弹为背景，基于变结构控制理论设计了一种导引律，该导引律以可测量信息为基础，十分易于工程实现。最后进行了三维弹道仿真，结果表明：所设计的导引律攻击精度明显优于比例导引律，尤其是在目标机动较大情况下，保证了脱靶量在米级以内；所设计的导引律在制导初期对误差进行修正，因而末端弹道更为平直，同情况下所消耗的姿控发动机数目更少。此外，所设计的导引律基于较大交会角的拦截而非逆轨道拦截，因而发射阵地更灵活、发射准备时间更短。

A Precision Terminal Guidance Law for Missiles Using Direct Force Control Systems

In missiles using direct force control systems, a high precision robust guidance law with low side jet consuming is required. Those in open literatures are either less precise, or too complex to apply. A variable structure guidance law is researched for an anti-ballistic missile using direct force control system. It adapts to discontinuous control and acquires high precision with no more information needed. Based on a nonlinear model, it ensures the final high precision. A suitable slide function avoids unnecessary requirements of information. The result established by the approaching law is simple to compute overall. Tree-dimension trajectory simulation results are given. The results show that variable structure guidance law acquires higher precision than proportional navigation, especially in case of intercepting maneuvering targets. They also show that variable structure guidance law gets more straight terminal trajectory and lower side jet consuming than proportional navigation, because it corrects the error of guidance earlier. All the guidance laws designed take large interception angle compared with reverse trajectory interception, so the base may be disengaged and less preparing time is required.