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Method for designing aeroengine robust tracking controller

A technology for aero-engines and tracking controllers, applied in design optimization/simulation, instruments, calculations, etc., can solve problems such as parameter perturbation, modeling errors, and individual differences

Inactive Publication Date: 2017-07-14
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

In summary, nonlinearity, modeling error, parameter perturbation, individual differences, and noise issues pose challenges to aeroengine controller designers

Method used

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  • Method for designing aeroengine robust tracking controller
  • Method for designing aeroengine robust tracking controller
  • Method for designing aeroengine robust tracking controller

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Embodiment

[0162] The specific embodiment of the present invention takes the multivariable control system of a certain type of turbofan engine as an example, figure 1 It is a structural diagram of the engine control system of the present invention. Based on the component-level model of turbofan engine's aerodynamic thermodynamics, its state variable model is established to describe the turbofan engine under control. The reference state variable and reference control variable based on the given output instruction are obtained by using the reference model, and the tracking control system model is constructed together with the state variable model of the turbofan engine. Based on the model, a robust controller is designed to obtain control variables and transmit them to the turbofan engine to complete the closed-loop control.

[0163] The cross-sectional identification diagram of a certain type of turbofan engine air path components used in the present invention is as follows figure 2 As...

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Abstract

The present invention discloses a method for designing an aeroengine robust tracking controller, which is a Leitmann robust tracking control method for the problems of uncertainty, noise, and the like in the aeroengine and the aeroengine control system. The method comprises: establishing a nominal state variable model of the aeroengine; establishing a state variable model of the aeroengine control system with uncertainties and noises; establishing a dynamic model of the aeroengine tracking control system based on a reference model; and designing a Leitmann robust tracking controller. According to the method disclosed by the present invention, performance of ''bounded consistent tracking'' and "bounded consistent ultimate tracking" of the tracking control system is proposed, and the robust tracking method based on the Leitmann controller is proposed, so that problems of noise, uncertainty, and the like in the aeroengine control system are overcome, tracking requirements of the system are satisfied, and the controlled system is ensured to maintain good robustness when the working environment, the working state and dynamic performance of the engine changes.

Description

technical field [0001] The invention belongs to the technical field of aero-engine control, and in particular relates to a design method of an aero-engine robust tracking controller. Background technique [0002] In recent years, aircraft performance indicators have been continuously improved, such as thrust-to-weight ratio, economy and control performance, etc., which also put forward higher requirements for aero-engines. In order to obtain better control performance of aero-engines, the control and controlled quantities of aero-engine control systems continue to increase, and the system becomes more and more complex, including dynamic coupling between multiple control inputs and multiple outputs, nonlinear changing operating environment and Operating status (usually characterized by rotational speed). Considering the design of the controller, there are usually multiple modeling processes, such as first establishing a nonlinear component-level model based on the aerodynami...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20Y02T90/00
Inventor 潘慕绚张凯文黄金泉
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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