高空轨控式直接侧向力/气动力复合控制方法  

Orbital Lateral Thrust/Aerodynamic Force Blended Control Methodin High Altitude

作　　者：贾倩[1] 魏明英[1] 郭大勇[1] 

机构地区：[1]北京电子工程总体研究所,北京100854

出　　处：《现代防御技术》2015年第6期61-67,共7页Modern Defence Technology

摘　　要：针对高空条件下导弹过载能力有限的情况,提出一种轨控式直接侧向力/气动力复合控制方法。首先,对侧向推力比例调节的轨控式直接侧向力/气动力复合控制导弹建立数学模型。然后,考虑质心漂移和侧喷流场干扰影响,设计滑模鲁棒控制器,实现气动控制部分姿态稳定功能。最后,建立轨控发动机推力模型,设计分档控制的轨控侧向力开机策略,实现直接力控制跟踪过载指令功能。仿真结果表明,与相同高度、速度条件下的单纯气动控制方法相比较,轨控式直接侧向力/气动力复合控制方法可以有效提高导弹快速响应能力和机动能力。To solve the problem that mobilization ability of missiles is not enough in high altitude, a new orbital lateral thrust/aerodynamic force blended control method is proposed. Firstly, the model of orbital lateral force/aerodynamic blended controlled missile with proportional lateral jets is established. Then robust variable structure controller is designed, including the effect of excursion of centroid and lat- eral jet interference, to control attitude with aerodynamic force control. At last, the model of orbital lateral thrust is constructed and proportional ignition logic is design to track overload command with lateral thrust control. The simulation results indicate thatin comparison with onlyaerodynamic force control in the same altitude and speed condition, orbital lateral thrust /aerodynamic force blended control method can improve the response speed and mobilizati

关 键 词：直接侧向力 复合控制 变结构控制 轨控发动机 开机策略 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]