非最小相位高超声速飞行器自适应参数估计控制

Adaptive parameter estimation control of nonminimum phase hypersonic flight vehicle

本文考虑非最小相位高超声速飞行器纵向动力学模型,提出了一种基于输出重定义的自适应参数估计控制方法.通过输出重定义将不稳定的内动态转换为渐近稳定的内动态,对重定义后的内动态进行坐标变换,推导出俯仰角指令作为输入输出子系统的参考指令.针对重定义后的姿态子系统和速度子系统,将未知气动函数转换为已知状态向量和未知气动参数向量相乘的线性参数化形式,设计自适应更新律对未知气动参数向量进行估计,进一步基于估计信息设计速度子系统动态逆控制和输入输出子系统反步法控制.基于Lyapunov稳定性定理对系统稳定性进行分析,仿真测试证明了所提方法的有效性.

In this study,considering the longitudinal dynamic model of a nonminimum phase hypersonic flight vehicle,output-redefinitionbased adaptive parameter estimation control is proposed.Output redefinition is employed to transform unstable internal dynamics to asymptotically stable internal dynamics.Based on the coordinate transformation of the redefined internal dynamics,the pitch angle command is derived and used as the reference command of the input-output subsystem.For the redefined attitude subsystem and the velocity subsystem,the unknown aerodynamic functions are decomposed into the known state vector and the unknown aerodynamic parameter vector,that is the linear parametric form.The adaptive updating laws are constructed to estimate the aerodynamic parameter vectors,and then the dynamic inversion control is designed for the velocity subsystem and the backstepping control is designed for the input-output subsystem.The system stability is analyzed via the Lyapunov stability theorem while simulation studies are conducted to illustrate the effectiveness of the proposed method.