带落角约束的空地导弹模糊滑模末制导律研究  

Research on Fuzzy Sliding Mode Terminal Guidance Law with Impact Angle Constraint for Air-to-ground Missile

作　　者：辛腾达 范惠林[1] 刘成亮[1] 肖冲华 

机构地区：[1]空军航空大学,长春130022 [2]沈空装备部,沈阳110000

出　　处：《战术导弹技术》2015年第5期61-69,共9页Tactical Missile Technology

摘　　要：为提高空地导弹的制导性能,满足空地导弹对落角约束的要求,获得最佳的打击效果,以经解耦的空地导弹-目标相对运动学模型为基础,应用滑模变结构控制理论推导出了带落角约束的空地导弹滑模末制导律,并用饱和函数取代滑模末制导律中的符号函数,削弱滑模末制导律的抖振。其次,应用模糊控制理论对滑模趋近律系数进行模糊自适应调节,设计出带落角约束的空地导弹模糊滑模末制导律。最后,应用Matlab对该模糊滑模末制导律的制导性能进行数字仿真验证。仿真结果表明,所设计的模糊滑模末制导律能够导引导弹以期望的落角命中目标,具有一定的应用价值。In order to improve the guidance performance of the air-to-ground missile,satisfy the demand of the impact angle constraint for air-to-ground missile,and achieve the best efficiency of strike,a sliding mode terminal guidance law with impact angle constraint for air-to-ground missile is designed based on the decoupled air-to-ground missile,target relative motion model and the sliding mode variable structure control theory. The symbol function of the sliding mode terminal guidance law is replaced by the saturation function to weaken the chattering of the sliding mode terminal guidance law. Secondly,the fuzzy sliding mode terminal guidance law with impact angle constraint for air-to-ground missile is designed by appalling the fuzzy control theory to adaptive adjust the reaching law coefficient. Finally,the Matlab is applied to run the digital simulation to verify the performance of the fuzzy sliding mode terminal guidance law. The simulation results show that the fuzzy sliding mode terminal guidance law can guidance the missile to hit the target with the expected angle,and has a certain application value.

关 键 词：落角 空地导弹 滑模变结构控制 模糊控制 末制导律 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]