非对称投弹及非对称挂载补偿控制技术研究  

Research on compensation control technology for asymmetric launching and loading of missiles

作　　者：李宏刚[1] 赵海[1] 高亚奎[1] 江飞鸿[1] 

机构地区：[1]中航工业西安飞机设计研究所飞行控制与液压设计研究所,陕西西安710089

出　　处：《飞行力学》2016年第4期46-49,共4页Flight Dynamics

摘　　要：针对战斗类飞机非对称投弹和非对称挂载这类情况,分析了投弹时横向扰动及纵向机动时横向耦合的机理,描述了其对飞行安全的威胁;通过引入所投弹质量、位置以及飞机法向过载,设计了非对称投弹/非对称挂载补偿控制律。仿真验证结果表明:该补偿控制律可消除上述两种情况下的横向扰动,有助于非对称投弹时飞机状态的保持,更重要的是提高了非对称挂载情况下着陆的安全性。For asymmetric launching and loading missiles from fighters,this paper analyses the principles of lateral disturbance in missile launching and lateral coupling in longitudinal movement,and describes the threats to the flight safety. Finally,a control law is designed to compensate the lateral disturbance caused by asymmetric launching and loading missiles,by using the mass and location of missile fired,along with the normal load factor of aircraft. The simulation results indicate that the control law can eliminate the lateral disturb caused in those two situations. It is conducive to keeping the attitude of aircraft when launch missile asymmetrically,and it improves the landing safety of aircraft with asymmetric missiles especially.

关 键 词：非对称 投弹 挂载 补偿 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]