改进的考虑自动驾驶仪动态特性的有限时间滑模导引律
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摘要
为减小导弹自动驾驶仪延迟特性对制导精度的影响,考虑到实际战争中制导末段时间很短,推导了考虑导弹动态特性的有限时间收敛的制导数学模型;其次根据滑模控制理论设计了基于该数学模型的导引律;证明了所设计的导引律在制导系统中有限时间稳定;为削弱滑模导引律的抖振现象,利用双曲正切函数改进了导引律。仿真表明:改进的导引律在目标做非机动和机动的情形下均能在有限时间内快速跟踪目标的运动,并保持较高的制导精度。
In order to reduce the effect of the delay characteristics of missile autopilot on guidance precision and the terminal guidance time of actual war is short. The mathematical model considering the finite time convergence for the dynamics of the missile autipilot is built. The guidance law is designed based on sliding mode control theory. The designed guidance law is proved stable in the system. A hyperbolic tangent function is used to improve the guidance law in order to reduces the chattering of guidance law. The simulation shows that the design of guidance law can fastly track the target movement in a limited time and maintain a high guidance precision when the target is non-maneuvering or maneuvering.
In order to reduce the effect of the delay characteristics of missile autopilot on guidance precision and the terminal guidance time of actual war is short. The mathematical model considering the finite time convergence for the dynamics of the missile autipilot is built. The guidance law is designed based on sliding mode control theory. The designed guidance law is proved stable in the system. A hyperbolic tangent function is used to improve the guidance law in order to reduces the chattering of guidance law. The simulation shows that the design of guidance law can fastly track the target movement in a limited time and maintain a high guidance precision when the target is non-maneuvering or maneuvering.
引文
[1]周荻,曲萍萍.考虑导弹自动驾驶仪二阶动态特性的有限时间收敛导引律[J].航空兵器,2013,6(3):9-12.
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[6]王超伦,薛林,闫仁勇.考虑弹体动态特性的机动效率约束导引律[J].国防大学科技大学学报,2017,39(4):48-55.
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[9]陈数,王夫栋.基于滑模变结构的WSNs跨层拥塞控制算法[J].传感器与微系统,2014,33(11):132-138.
[10]ZHOU D,SUN S.Guidance laws with finite time convergence[J].J Guid Control Dyn,2009,32(6):1838-1846.
[11]刘名玥.小型导弹与制导控制一体化设计[D].南京:南京理工大学,2015.
[12]钱杏芳,林瑞雄,赵亚男.导弹飞行力学[M].北京:北京理工大学出版社,2015:91-96.
[13]周荻.寻的导弹新型导引规律[M].北京:国防工业出版社,2002:14-16.
[14]高峰,唐胜景,师娇,等.一种改进的自适应滑模变结构导引律[J].弹道学报,2013,25(3):18-23.
[15]张旭.制导控制一体化有限时间收敛控制算法[J].空军工程大学学报,2015,16(5):7-10.
[2]孙胜.有限时间收敛寻的导引律[D].哈尔滨:哈尔滨工业大学,2010.
[3]周卫文,崔平远,崔祜涛.基于改进预测制导的深空撞击探测末制导律[J].传感器与微系统,2009,28(2):116-120.
[4]QU P P,ZHOU D.Observer-based guidance law accounting for second-order dynamics of missile autopilots[J].Journal of Harbin Institute of Technology,2013,20(1):17-22.
[5]张尧.机动目标防御的导弹精确制导与控制及一体化设计研究[D].北京:北京理工大学,2015.
[6]王超伦,薛林,闫仁勇.考虑弹体动态特性的机动效率约束导引律[J].国防大学科技大学学报,2017,39(4):48-55.
[7]ZONG Q,WANG J,TIAN B L,et al.Quasi-continuous high-order sliding mode controller and observer design for flexible hypersonic vehicle[J].Aerospace Science and Technology,2013(27):127-137.
[8]李鹏程.带落角约束有限时间收敛滑模制导律[J].现代防御技术,2017,45(6):66-73.
[9]陈数,王夫栋.基于滑模变结构的WSNs跨层拥塞控制算法[J].传感器与微系统,2014,33(11):132-138.
[10]ZHOU D,SUN S.Guidance laws with finite time convergence[J].J Guid Control Dyn,2009,32(6):1838-1846.
[11]刘名玥.小型导弹与制导控制一体化设计[D].南京:南京理工大学,2015.
[12]钱杏芳,林瑞雄,赵亚男.导弹飞行力学[M].北京:北京理工大学出版社,2015:91-96.
[13]周荻.寻的导弹新型导引规律[M].北京:国防工业出版社,2002:14-16.
[14]高峰,唐胜景,师娇,等.一种改进的自适应滑模变结构导引律[J].弹道学报,2013,25(3):18-23.
[15]张旭.制导控制一体化有限时间收敛控制算法[J].空军工程大学学报,2015,16(5):7-10.