In this paper, the dynamic performance of aero-engine acceleration process is improved by switching among several controllers, and it is protected when the speed is too high. Firstly, according to the aeroengine control system model, an H________________________ In order to avoid unnecessary loss of actuator caused by frequent switching, the safety protection controller and event triggered switching mechanism are designed to protect the speed of high-voltage rotor when the speed is too high to exceed the maximum speed boundary to ensure flight safety.
Finally, the effectiveness of this method is verified by several simulation examples.
In aeroengine control, there is a need for a simple and computational method that can use the traditional linear system design method, and gain scheduling technology just meets this requirement.
Gain scheduling linearizes the non-linear object at some working points. The classical linear control theory is used to design the local controller.
Then the parameters of the controller are selected according to the scheduling variables reflecting the dynamic performance of the system. Thus the parameter selection of the controller under all working conditions is realized. Designing a global controller according to the above-mentioned incremental scheduling method can achieve the corresponding control functions, but the traditional single controller control method can only meet the requirements of one performance, not other performance requirements of the system at the same time.
If multiple controllers are designed to meet the system’s performance requirements, and then switching in time according to the switching rules can simultaneously meet the system’s performance requirements, which is the advantage of switching control.
In switching control, switching strategy plays an important role [2].
The advantages of each subsystem can be brought into full play by switching according to a reasonable switching strategy. At the same time, with the expansion of flight range, the increase of flight speed and the improvement of maneuverability, the contradiction between the speed and safety of engine dynamic response becomes more prominent [3]. Therefore, safety protection is a necessary control function for every aeroengine. This paper mainly studies the acceleration control of engine speed, aiming at accelerating the engine high-pressure rotor speed to a stable value along a relatively ideal reference acceleration curve. The tracking process should be fast and have a small overshoot.
At the same time, in order to prevent the high-pressure rotor speed from threatening flight safety in the acceleration process, safety protection links are added to the high-pressure engine. Rotor speed should be limited to prevent it from exceeding the maximum speed boundary, so as to protect flight safety. Two H__ global tracking controllers are designed by means of the integrated design method of gain scheduling and regional pole placement, thermostatic element so that the engine rotate speed can track an ideal acceleration reference curve, thus accelerating the engine with the expected effect. At the same time, by designing reasonable switching rules between the two controllers, the system can simultaneously meet the requirements of fast tracking and small overshoot. In the design of safety protection controller, tracking control can be used to limit the speed of engine rotor [4].
However, the proportional controller is used in [4], which has no anti-interference ability.
[5] The H_2/H_______________________ Compared with the single controller in [5], the switching controller used in this paper can meet the requirements of the system for fast tracking and small overshoot, which is the advantage of the switching controller.
Because H____________________ In this paper, the switching method is used to study the speed regulation and safety protection of aeroengine. Firstly, several H______________________ tracking controllers are designed according to the aeroengine control system model, and The unnecessary loss of the actuator; then, the safety protection controller is designed to protect the speed of the high-voltage rotor when the speed is too high to exceed the maximum speed boundary, so as to ensure flight safety; finally, the effectiveness of this method is verified by several simulation examples.