Modeling and Prescribed Performance Attitude Control of Transport Aircraft

The attitude control problem of the transport air-craft under state constraints is investigated in this paper. Firstly, a 6-degree-of-freedom(DOF) model of the transport aircraft is established, and an aerodynamic parameter interpolation table is created using wind tunnel test data. The aircraft's aerodynamic parameters are identified using an improved Simulated Annealing-Particle Swarm Optimization(SA-PSO) algorithm, which providing a basis for control law design. Then, the prescribed performance control theory is introduced. A prescribed performance function is established to constrain the dynamic and steady-state performance of the aircraft system. The aircraft's attitude angle output error is transformed into an unconstrained space and an attitude controller is designed using the backstepping control method based on the transformed error. Finally, simulation experiments are conducted to validate the performance of the proposed prescribed performance back-stepping attitude controller(PPBC). The simulation results show that the aircraft model with PPBC controller can effectively track the desired signal and maintain the error within the prescribed performance boundary.