A Robust Model Reference Adaptive Control Framework for Integrated Flight Propulsion System

Abstract

Abstract In this paper, a robust model reference adaptive control framework for the integrated flight propulsion system has been proposed. It could serve as a general controller structure for the integrated flight propulsion system. The linear state feedback controller using LQR method is firstly designed under deterministic uncertainty-free conditions, serving as the reference model. Robust adaptive controller is thereafter introduced to make the system state trajectories converge to the reference model under parametric uncertainties. It is worth noting that, such an arrangement makes the whole control framework easy to be implemented as a modification to existing well designed linear controllers. Besides, high order complexities of the system can be resolved by decomposing it using singular perturbation method based on time scale. A formal stability proof will be provided. The whole control framework has been implemented on a trim point of an F-16 model. Only actuator anomalies have been concerned as uncertainties to verify the effectiveness of the control framework. However, this structure can be easily extended to accommodate other parametric uncertainties. The simulation results of the controller implemented on the nonlinear system near an equilibrium point will be provided. Superior performance regarding stability and robustness can be observed from the simulation results with robust adaptive augmentation controller used.