摘要
A new model and design method for integrated flight/propulsion control system are presented. To avoid solving higher order Riccati equations, a hierarchical optimization method is developed based on structure perturbation. In the new method, designing of a linear (luadrate regulator (LQR) is divided into two steps: (1 ) computingfeedback gain matrix of individual subsystem, while the association among these subsystems is omittd, and (2) according to the optimization method of LoR, computing thecompensation gain matrix for each subsystem using input perturbation approach. Simulation and application show that not only the results of the new method is as good as that ofan ordinary LQR, but also the efficiency is much higher than that of LQR.
A new model and design method for integrated flight/propulsion control system are presented. To avoid solving higher order Riccati equations, a hierarchical optimization method is developed based on structure perturbation. In the new method, designing of a linear (luadrate regulator (LQR) is divided into two steps: (1 ) computingfeedback gain matrix of individual subsystem, while the association among these subsystems is omittd, and (2) according to the optimization method of LoR, computing thecompensation gain matrix for each subsystem using input perturbation approach. Simulation and application show that not only the results of the new method is as good as that ofan ordinary LQR, but also the efficiency is much higher than that of LQR.
