Aero-engine online optimization and multivariable control design method based on model predictive control

An aero-engine, multi-variable control technology, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve the problem that the real-time performance of the controller control system is difficult to take into account

Active Publication Date: 2018-11-06
DALIAN UNIV OF TECH
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Although model predictive control has many excellent characteristics, it also has the disadvantage that it is

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  • Aero-engine online optimization and multivariable control design method based on model predictive control
  • Aero-engine online optimization and multivariable control design method based on model predictive control
  • Aero-engine online optimization and multivariable control design method based on model predictive control

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[0097] The specific implementation manners of the present invention will be further described below in conjunction with the accompanying drawings and technical solutions.

[0098] This embodiment is an online optimization and multivariable control design method for an aeroengine based on model prediction. The detailed design steps are as follows:

[0099] Step 1: Establish the aero-engine small deviation gain model with the current aero-engine actual input and external environmental parameters as the steady-state point; first obtain the steady-state point for calculating the linearized small-deviation model. In the present invention, the input quantity and environmental parameters at the last sampling moment of the engine are approximated as the steady state point to calculate the small deviation model at the current moment. The method of calculating the small deviation model of the engine near the steady state point is as follows.

[0100] During the working process of an a...

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Abstract

An aero-engine online optimization and multivariable control design method based on model predictive control achieves the control and online optimization of multiple variables of an aero-engine undera constraint and according to requirements of thrust and speed. A control system consists of two parts. The first part is a prediction model acquisition layer. Based on the actual working state of each control cycle and the external environmental parameters of the aero-engine, an engine small deviation linear model near different steady-state points is continuously established, and model parameters are provided for a model predictive controller. The second part is a control law decision layer. A closed-loop structure is formed by the model predictive controller and an external output feedback.The model predictive controller, based on an engine model in the current state, a control command and relevant constraint limits, determines the output of the controller at the next moment by solvinga linear optimization problem. The external output feedback introduces the aero-engine actual output into the decision on future controlled quantity of the controller to compensate for the influenceof model mismatch and external disturbances.

Description

technical field [0001] The invention provides an aeroengine online optimization and multivariable control design method based on model prediction, which belongs to the technical field of aerospace propulsion system control and simulation. Background technique [0002] With the continuous advancement of aero-engine technology, the structure of modern aero-engines has become increasingly complex, and the scope of work has also continued to expand. The requirements for aero-engine control systems have also become higher and higher. The traditional single-input / single-output control system has been difficult to meet the control requirements. . Therefore, selecting more control variables to realize the multi-variable control system that controls multiple parameters of the engine has become an important means to improve the performance of the engine control system. As a model-based multi-variable control algorithm, model predictive control can not only realize the effective contr...

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 王智民杜宪马艳华孙希明
Owner DALIAN UNIV OF TECH
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