Design method of aeronautical engine integral tangent fuzzy self - adaptive sliding mode controller

An aero-engine and fuzzy self-adaptive technology, applied in self-adaptive control, general control system, control/adjustment system, etc., can solve the problems of poor adaptability of parameters, difficult to ensure robustness, etc., to reduce steady-state error, improve Transient performance, the effect of ensuring flight safety

Inactive Publication Date: 2017-05-17
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

Wu Bin and others [5] Aiming at the difficulty of ensuring robustness and poor parameter adaptability in the design process of conventional ...

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  • Design method of aeronautical engine integral tangent fuzzy self - adaptive sliding mode controller
  • Design method of aeronautical engine integral tangent fuzzy self - adaptive sliding mode controller
  • Design method of aeronautical engine integral tangent fuzzy self - adaptive sliding mode controller

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Embodiment Construction

[0036] Taking the component-level model of a certain type of turbofan engine as an example below, the technical solution of the present invention is described in detail: Step 1

[0037] The aero-engine system is a relatively complex and nonlinear system, and its nonlinear model can generally be expressed as:

[0038]

[0039] Among them, f and h represent abstract functional relationships; x(t)∈R n is the state vector of the engine system, u(t)∈R p is the input vector of the engine system, y(t)∈R m is the output vector of the engine system. When the operating condition of the engine is uniquely determined, at a certain steady-state point (x 0 , u 0 ,y 0 ) near the Taylor series expansion, ignoring the quadratic and above high-order terms, the obtained state space variable model is:

[0040]

[0041] Among them, matrix A represents the state transition matrix, matrix B represents the input allocation matrix, matrix C represents the output coefficient matrix, and matri...

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Abstract

The invention discloses a design method of aeronautical engine integral tangent fuzzy self - adaptive sliding mode controller, which comprises the following steps: obtaining a model near a steady point to output data according to a nonlinear component level model of an aeroengine system, establishing a linear model of the aeroengine by using a least squares method; defining a tracking error of the aeroengine system, a reference signal for a given system, and assuming that a derivative of a reference signal is 0; designing a hyperbolic tangent plane by using a hyperbolic tangent function similar to a function of a saturation function; saturating an error for a case where the error is large, and enlarging a system error for a case where the error is small; improving a dynamic quality of a system approach motion by using an exponential approaching law; utilizing an adaptive control method to realize an adaptive estimation of an uncertainty upper bound, and the uncertainty upper bound is obtained; designing a sliding mode control law by means of the Lyapunov function verifying a stability of the system.

Description

technical field [0001] The invention belongs to the design technology of an aero-engine controller, in particular to a method for establishing an aero-engine model and designing a controller. Background technique [0002] The performance of the aero-engine control system directly affects the performance of the engine and aircraft. Among the control methods of aero-engines, the relatively complete and mature control method is still based on the linear model of the engine. [1]-[3] . In the actual control process, due to the harsh working environment, external disturbance, performance degradation, modeling error and other reasons, aero-engine inevitably has a lot of uncertainties. These uncertainties will have a great impact on the stability and dynamic performance of the aero-engine control system, so the control system needs to have good robustness. [0003] In recent years, scholars at home and abroad have conducted a series of studies on model uncertainty. At present, m...

Claims

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Application Information

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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 肖玲斐胡继祥
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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