【作者】 胥彪；

【导师】 周荻；

【作者基本信息】 哈尔滨工业大学 ， 控制科学与工程， 2010， 硕士

【摘要】 拦截导弹通过精确制导实现与机动目标直接碰撞,利用动能将目标彻底摧毁。在距离地面约20km高度,拦截导弹的气动外形可以保证精确制导所需要的机动能力,但是响应速度却因为舵控效率的减弱而大大降低,采用直接侧向力与气动力的复合控制方式则可以显著提高拦截导弹控制系统的响应速度。本文基于增益调度方法对复合控制律进行了设计。首先对带有侧向喷流装置的拦截弹的数学模型进行了推导,然后在工作点对模型进行了线性化,从而建立了导弹的线性变参数模型。并以俯仰方向为例,设计了导弹直接侧向力与气动力复合控制系统。针对由脉冲发动机提供直接侧向力的拦截导弹,本文采用了这样的设计思路,即先独立设计舵控制律,然后把设计好舵控制律的系统整合成新受控对象,与离散控制量——脉冲发动机点火数量构成新控制系统。并将动态增益调度方法应用于过载指令跟踪控制系统设计。通过与静态增益调度方法和固定系数方法进行比较,得出动态增益调度方法能够更好的跟踪过载指令,而且改善了舵系统的响应。因为脉冲发动机的数量有限,为了节省脉冲发动机,本文给出了拦截导弹稳定跟踪上过载指令后,直接侧向力不输出的条件以及数学证明。并且通过仿真,验证该条件的正确性。最后,综合拦截导弹运动模型和目标机动模型,对飞机和再入大气层的弹道导弹目标完成了从中制导段到遭遇的拦截过程仿真。给出了拦截导弹和目标的相对运动曲线和脱靶量的Monte-Carlo仿真结果。仿真结果表明,拦截导弹能够很好的完成拦截飞机和弹道导弹任务。更多还原

【Abstract】 A hit-to-kill interceptor achieves direct collision with a maneuverable target by precision guidance, and destroys the target with kinetic energy. At about 20km altitude, the aerodynamic shape of the interceptor is able to create a desired divert acceleration for precision guidance, but the response to a guidance command is getting much slower because of the control fin’s weak effectiveness. The blended control, which means the combination of lateral thrust control and aerodynamic control, can evidently increase the response speed of the interceptor’s control system. In this thesis, the design of aerodynamic and lateral thrust blended control law using the gain scheduling method is investigated.First of all, the nonlinear model of interceptor with lateral thrust is deduced. Then the plant is linearized around different operating points, and which leads to the linear parameter-varying model. With the pitch loop as an example, we design the missile’s lateral thrust and aerodynamics blended control system.Assuming that the lateral thrust is provided by impulse thrusters, we design the control system with the following strategy. The tail fin’s controller is designed independently, and then all the continuous parts, including the fin’s controller, are reunited into a new controlled plant of the ignition number of the impulse thrusters which is in discrete-time form. A dynamic gain scheduling method is employed in the system design. Compared with the static gain scheduling and fixed gain method, the dynamic gain scheduling gives better transient performance and improves the transient performance of tail fins.The problem about how to save the impulse thrusters is discussed. Theoretically, we give the possibility of decreasing the use of impulse thrusters. Then we use simulation to verify the idea.Finally, we simulate the interception processes against an airplane or a reentry ballistic missile target from the mid-course guidance to the engagement. The simulation results prove that the interceptor can hit the target effectively.更多还原