具有直接侧向力的拦截导弹复合制导控制设计  

Blended Guidance and Control Strategy Design for Interceptor Missile with Lateral Jets

作　　者：毕永涛[1] 姚郁[1] 马克茂[1] 

机构地区：[1]哈尔滨工业大学控制与仿真中心,哈尔滨150080

出　　处：《宇航学报》2010年第11期2496-2502,共7页Journal of Astronautics

基　　金：国家自然科学基金(60674043)

摘　　要：针对大气层内直接侧向力与气动力复合控制拦截导弹,提出了一种基于输出稳定的复合制导控制策略。该策略同时考虑了末制导精度和弹体动态响应,首先根据末制导系统数学模型选择零效脱靶量和弹体角加速度作为系统评价输出,然后计算维持末制导系统评价输出在零点所需要的控制量,最后在考虑不确定性和外加干扰的情况下,扩展附加切换控制,使得系统评价输出能够在有限时间内到达零点并确保闭环系统稳定。仿真结果表明,利用所提复合制导控制策略,在制导末段拦截高机动目标时达到了很高精度。Integrated guidance and control strategy based on output stability is proposed for missile with blended lateral thrust and aerodynamic surface control.The integrated strategy can account simultaneously for the guidance and autopilot requirements using the additional degree of freedom.Firstly,zero effort miss and pitch angular acceleration are chosen as system output.Secondly,the original controller is designed to maintain the system output on the zero and to accommodate modeling uncertain and jet interaction;the original controller is augmented by a second component,referred to as the additional controller.Finally,the proposed theorem show that original controller and additional controller can drive the system output to zero in finite time,while ensuring closed-loop stability.

关 键 词：直接侧向力 复合制导控制策略 输出稳定性 零效脱靶量 拦截导弹 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]