针对高速飞行情况下倾斜转弯(Bank To Turn,BTT)飞行器编队控制问题,基于一种制导控制一体化(Integrated Guidance and Control,IGC)理论提出一种分布式编队系统建模与控制器设计方法。通过坐标变换,将双积分系统模型与BTT飞行器动力学...针对高速飞行情况下倾斜转弯(Bank To Turn,BTT)飞行器编队控制问题,基于一种制导控制一体化(Integrated Guidance and Control,IGC)理论提出一种分布式编队系统建模与控制器设计方法。通过坐标变换,将双积分系统模型与BTT飞行器动力学模型相结合,得到了IGC模型;在反演控制框架下,采用一致性理论与神经网络自适应滑模变结构理论设计了编队控制器;进行严格的理论分析并证明了闭环系统的稳定性和收敛特性;在高速情况下进行了六自由度数学仿真,仿真结果表明了IGC设计方法的有效性,以及较传统设计方法的优越性。展开更多
A new non-decoupling three-dimensional guidance law is proposed for bank-to-turn （BTT） missiles with the motion coupling problem. In this method, the different geometry is taken for theoretically modeling on B-IT mi...A new non-decoupling three-dimensional guidance law is proposed for bank-to-turn （BTT） missiles with the motion coupling problem. In this method, the different geometry is taken for theoretically modeling on B-IT missiles＇ motion within the threedimensional style without information loss, and meanwhile, Liegroup is utilized to describe the line-of-sight （LOS） azimuth when the terminal angular constraints are considered. Under these cir- cumstances, a guidance kinematics model is established based on differential geometry. Then, corresponding to no terminal angular constraint and terminal angular constraints, guidance laws are re- spectively designed by using proportional control and generalized proportional-derivative （PD） control in SO（3） group. Eventually, simulation results validate that this developed method can effectively avoid the complexity of pure Lie-group method and the information loss of the traditional decoupling method as well.展开更多
文摘针对高速飞行情况下倾斜转弯(Bank To Turn,BTT)飞行器编队控制问题,基于一种制导控制一体化(Integrated Guidance and Control,IGC)理论提出一种分布式编队系统建模与控制器设计方法。通过坐标变换,将双积分系统模型与BTT飞行器动力学模型相结合,得到了IGC模型;在反演控制框架下,采用一致性理论与神经网络自适应滑模变结构理论设计了编队控制器;进行严格的理论分析并证明了闭环系统的稳定性和收敛特性;在高速情况下进行了六自由度数学仿真,仿真结果表明了IGC设计方法的有效性,以及较传统设计方法的优越性。
基金supported by the National University of Defense Technology Innovation Support Project for Outstanding Graduate Student(B100303)
文摘A new non-decoupling three-dimensional guidance law is proposed for bank-to-turn （BTT） missiles with the motion coupling problem. In this method, the different geometry is taken for theoretically modeling on B-IT missiles＇ motion within the threedimensional style without information loss, and meanwhile, Liegroup is utilized to describe the line-of-sight （LOS） azimuth when the terminal angular constraints are considered. Under these cir- cumstances, a guidance kinematics model is established based on differential geometry. Then, corresponding to no terminal angular constraint and terminal angular constraints, guidance laws are re- spectively designed by using proportional control and generalized proportional-derivative （PD） control in SO（3） group. Eventually, simulation results validate that this developed method can effectively avoid the complexity of pure Lie-group method and the information loss of the traditional decoupling method as well.
