Prescribed performance and anti-noise control of near space vehicle with thermal constraint

Near space hypersonic vehicle will under harsh load such as complex aerodynamics, high temperature and noise in the reentry process due to its supersonic velocity. In order to alleviate the design pressure of thermal protection system on high-speed aircraft and ensure the structural and material safety during reentry process, from the perspective of trajectory and control system design, a high-performance adaptive nonlinear prescribed performance control scheme under the angle of attack constraint is given to do the thermal and mechanical loads management actively. First, the angle of attack constraint of the full ballistic flight is solved according to the engineering model of large-area heat flux, and the dynamic response process of angle of attack is designed based on the prescribed performance control theory combined with the exponential function. To avoid the explosion of the complexity problem in the backstep-ping procedure, a new feedforward nonlinear sigmoid tracking differentiator is introduced to improve the chattering and peak phenomenon of traditional tracking differentiator in ADRC theory. Then a new nonlinear extended state observer based on cascade is introduced to suppress the peak phenomenon of the traditional high gain observer, nonlinear gain adjustment mechanism is introduced to improve the anti-noise ability of the extended state observer. The Lyapunov stability of above control system is proved to ensure the safety of the thermal protection system during reentry process theoretically. Finally, the simulation comparison between the prescribed performance control system and the robust ADRC system are given. The results show that the prescribed performance control system can ensure AOA within the prescribed boundary to meet the demand on the thermal and mechanical load constraints, and also has more reliable robust security guarantee with better command tracking performance in the engineering noise environment. © 2023 Chinese Society of Astronautics. All rights reserved.