PI controller design method capable of preventing integral saturation during engine control strategy switching

Abstract

The invention discloses a PI controller design method capable of preventing integral saturation during aero-engine control strategy switching, and relates to PI controller design of multiple control strategies of high-pressure rotating speed closed loop control, exhaust temperature closed loop limit, low-pressure rotating speed closed loop limiting, gas compressor outlet pressure closed loop limiting, acceleration closed loop limiting, deceleration closed loop limiting and the like and switching of all the control strategies. All closed loop controllers adopt a manner that a deviation is multiplied by a proportional action coefficient, then added with a fuel oil flow given value at the previous time and multiplied by a first-order inertia link transfer function, the fuel oil flow given values of all the control strategies at the current moment begin to be calculated from the fuel oil flow given values selected from the previous moments, large deviations of the non-selected control strategies cannot be accumulated, integral saturation cannot appear, however, substantially, it is still a PI controller, an integration element is included, and similarly, the offset can be removed.

Description

technical field [0001] The invention belongs to the field of controller design, and relates to a design method of a PI control system, in particular to a design method of a PI controller for preventing integral saturation during control strategy switching of an aero-engine, and to controller design and control strategies of various control strategies of an aero-engine. Switching between various control strategies. Background technique [0002] The main control loop of an aero-engine is the main fuel control loop that takes the high-pressure rotor speed as the controlled variable. Due to the complex working state of the aero-engine, it may sometimes operate in some potentially destructive states, so in addition to the main fuel control loop Also set limit protection controls to prevent this from happening by enforcing additional limits. Key concerns include: [0003] 1) When the maximum limit value of the low-pressure rotor speed is exceeded, the possible disc rupture or bl...

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Problems solved by technology

[0013] The purpose of the present invention is to provide a kind of PI controller design method that prevents integral saturation in aero-engine control strategy switching in order to solve the problems such as overshoot and system oscillation caused by integral saturation in the existing aero-engine control strategy switching process, In the present invention, the controller of each control strategy is designed in the form of multiplying the deviation by the proportional action coefficient plus the given value of the fuel flow at the previous moment multiplied by the first-order inertial link transfer function, and the current moment of all control strategies The given value of fuel flow is calculated from the given value of fuel flow at the previous moment, and the large deviation of the unselected control strategy will not be accumulated, which avoids integral saturation. Since it is still a PI controller in essence, it still includes an integral link , so it can also eliminate the static error of the system

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