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A sensor fault adjustment method for aero-engine

A technology for aero-engine and sensor failures, applied in control/regulation systems, instruments, adaptive control, etc., can solve problems such as slow response speed and large amount of computation

Active Publication Date: 2021-04-06
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

Although this fault detection-isolation-reconstruction measurement signal scheme can reduce the impact of sensor faults on the control system, it has a large amount of calculation and a slow response speed.

Method used

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  • A sensor fault adjustment method for aero-engine
  • A sensor fault adjustment method for aero-engine
  • A sensor fault adjustment method for aero-engine

Examples

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example

[0150] 1. Establish aero-engine dynamics model

[0151] The aeroengine of the present invention includes all gas turbine engines, and the engine model used in this example is a turbofan engine with a large bypass ratio, dual rotors, and non-adjustable nozzle area, and it is not limited to the turbofan engine. Only the dynamic characteristics of the two rotors are considered, so the state variable of the system is selected as: x=[N 1 N 2 ] T , N 1 , N 2 are the rotational speeds of the low-pressure rotor and the high-pressure rotor, respectively. The input variable is u=W f , W f For fuel supply. According to the common turbofan engine sensor arrangement scheme, the output variable is selected as y=[N 1 N 2 Pt 3 Tt 46 ], Pt 3 is the total pressure at the outlet of the high pressure compressor, Tt 46 is the total outlet temperature of the low-pressure turbine.

[0152] For a turbofan engine with a large bypass ratio, most of its thrust is generated by the fan, ...

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Abstract

The invention discloses a sensor fault adjustment method for an aero-engine, which includes establishing an aero-engine dynamics model, designing a fractional-order integral sliding mode observer according to the model, reconstructing fault signals, and using the reconstructed fault signals to perform measurement data fix. The fault signal is reconstructed by the fractional sliding mode observer, and the measurement signal of the sensor is directly compensated and corrected to eliminate the influence of the sensor fault on the control system. The invention can still obtain correct measurement parameters when the sensor fails, and improves the robustness of the aeroengine control system, wherein the calculation amount is smaller and the adjustment speed is faster.

Description

technical field [0001] The invention belongs to the technical field of aero-engine fault-tolerant control, and in particular relates to an aero-engine sensor fault adjustment method based on a fractional-order integral sliding mode observer. Background technique [0002] Aero-engine is a multi-loop, multi-variable, nonlinear complex system. Its control system is completely based on the sensor measurement signal, and the control command signal is obtained through the controller operation to adjust the working state of the engine. However, because aeroengines work under harsh conditions of high temperature, high pressure, and high stress, and often change their working states and bear large and changing loads, the sensor becomes one of the fault-prone components. If the sensor fails, it will provide wrong information to the control system, which will affect the performance of the engine and even cause catastrophic consequences. Therefore, it is crucial to take fault-tolerant ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 肖玲斐何晓聪
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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