A Method for Anti-Afterburner Disturbance of Aeroengine
A technology of aero-engine and disturbance method, which is applied in the direction of engine control, machine/engine, mechanical equipment, etc. It can solve the problems of main core machine disturbance, no patent disclosure anti-afterburning disturbance method, engine nonlinear enhancement, etc., and achieve scalability Strong, influence-free, and simple-to-design effects
Active Publication Date: 2021-11-05
DALIAN UNIV OF TECH
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Problems solved by technology
When the model predictive control is used as the main controller, because of the model-based characteristics of the model predictive controller, when the afterburner is turned on and off, the nonlinearity of the engine will increase, and the model predictive control may not be able to ensure that the main engine will not be disturbed
The invention proposes an ADRC compensation control algorithm in the boosting process, that is, the pressure ratio circuit of the engine in the boosting stage is controlled by MPC+ADRC, and the interference advance compensation function of ADRC is used to maintain the excellent performance of the original model predictive controller and the main controller. Steady-state and transition-state performance and constraint management capabilities while addressing main core disturbances caused by afterburner
So far, no patent discloses the anti-afterburning disturbance method based on the model predictive controller based on the aero-engine
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[0025] In order to make the purpose, technology and advantages of the present invention more clear, the present invention will be further described in detail below in conjunction with the accompanying drawings and examples.
[0026] The present invention is a kind of anti-addition disturbance method of aero-engine, and concrete design steps are as follows:
[0027] The first step is to build the model predictive control main control system;
[0028] According to the basic principle of model predictive control, the main control system based on model predictive controller is designed. The present invention focuses on the compensation controller, so the design process of the MPC is briefly introduced. The model predictive controller includes three parts: predictive model, rolling optimization, and feedback correction. The invention adopts the identification model as the controlled model, and obtains the response data off-line through the small disturbance method in a certain st...
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The invention provides an aeroengine anti-addition disturbance method, which belongs to the technical field of system control and simulation in aerospace propulsion theory and engineering. The invention proposes an ADRC compensation control algorithm in the process of boosting, that is, the pressure ratio circuit of the engine in the boosting stage is controlled by MPC+ADRC, and the interference advance compensation function of ADRC is used to maintain the excellent performance of the original model predictive controller and the main controller. Steady-state and transition-state performance and constraint management capabilities, while solving the main core machine disturbance problem caused by the afterburning process. Numerical simulation shows that after using the ADRC compensation controller, compared with no compensator, the disturbance of the core machine during the fast turn-on and turn-off process of the afterburner is significantly reduced, which shows that the design method of the anti-afterburner compensator of the present invention The validity and superiority of the theory can be extended to other theories.
Description
technical field [0001] The invention provides an aeroengine anti-addition disturbance method, which belongs to the field of system control and simulation in aerospace propulsion theory and engineering. Background technique [0002] The turning on and off of afterburning booster of aero-engine will cause a disturbance to the speed control system of the main engine. The design requirement of the booster transition process control system is to ensure the coordinated changes among the parameters of each component, so that the engine is safe, Stable and reliable work, and provide reliable thrust. According to the principle of aero-engines, engine stop in the air generally occurs during afterburner startup and shutdown. If the main engine changes greatly during afterburner, it may cause engine surge or even stop. When the model predictive control is used as the main controller, because of the model-based characteristics of the model predictive controller, when the afterburner is ...
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IPC IPC(8): F02C9/00
CPCF02C9/00F05D2270/704
Inventor 孙希明冯川杜宪杨斌温思歆
Owner DALIAN UNIV OF TECH