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中文摘要：
研究了直接力与气动力复合控制拦截弹的轨迹控制问题.建立了复合控制拦截弹的动力学模型,分析了不同复合方式的差别,指出了直接力对弹体运动的影响.建立了拦截弹与目标的相对运动模型,针对直接力与气动力复合控制的特殊性,基于滑模控制理论给出了轨迹控制算法,并在此基础上针对传统控制方法的缺陷,设计了脉冲发动机的点火逻辑.仿真结果表明,该方法能有效的实现拦截弹在末制导段的精确制导控制,并具有较强的鲁棒性.
英文摘要：
The ability of a trajectory control system to control an interceptor missile with combined control of lateral thrust and aerodynamics was investigated. A dynamical model for interceptor missile with combined control was established. After analyzing differ- ences between various combinations of control for interceptor missiles, impacts of lateral thrust on the motion of interceptor missiles were presented. A model of relative movement between the target and interceptor missile was established. Addressing the particularities of combined control for interceptor missiles, a trajectory control algorithm was designed based on the sliding mode control theory. On the basis of which, fire logic was presented for pulse thrusters in order to improve limitation of simple control method. Simulation results show that this method can effectively implement precise guidance for interceptor missiles at the final guidance stage as well as providing preferable robust stability.
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