Aero-engine active fault-tolerant control method based on error interval observer

A technology of aero engine and error interval, applied in the field of aviation control

Active Publication Date: 2019-04-16
DALIAN UNIV OF TECH
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Problems solved by technology

[0004] The technical solution of the present invention is to solve the problems of the existing control methods in view of the actuator and sensor faults of the aeroengine, and the control system is affected by the noise signal interference. The present invention provides an error interval observer based The active fault-tolerant control method of the aero-engine can ensure that the aero-engine can track the reference model without changing the structure and parameters of the controller, that is, the reconfigured system has the same state and output as the original non-faulty system. To achieve the desired control objectives, and enable the system to have the ability to eliminate faults independently, improve the reliability of aero-engine operation, and reduce the maintenance cost of aero-engines

Method used

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  • Aero-engine active fault-tolerant control method based on error interval observer
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  • Aero-engine active fault-tolerant control method based on error interval observer

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Embodiment Construction

[0099] The examples of the present invention will be described in further detail below in conjunction with the accompanying drawings and technical solutions.

[0100] Overall structure of the present invention is as figure 1 As shown, the specific steps are as follows:

[0101] Step 1.1: Establish an affine parameter-dependent aeroengine LPV model, and use the relative conversion speed n of the high-pressure turbine of the aeroengine 2 To change the parameter θ, the speed n 2 =88%, 89%, ..., 100% for normalization processing, that is, θ∈[-1,1], the available model is

[0102]

[0103] in

[0104]

[0105] State variable initial value x p (0)=[0,0] T , the disturbance variable d f (t) upper and lower bounds Pick Sensor noise margin V = 0.01. ΔA(θ) and ΔB(θ) have and set up

[0106]

[0107] Step 1.2: The reference model of the aero-engine fault-free system is

[0108]

[0109] Among them, the reference model state vector takes a constant value x pr...

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Abstract

The invention provides an aero-engine active fault-tolerant control method based on an error interval observer, and belongs to the technical field of aviation control. The method comprises the steps that an aero-engine tracks the state and the output of a reference model through an error feedback controller; an aero-engine control system with a disturbance signal and with an actuator fault and a sensor fault is compensated through a virtual sensor and a virtual actuator; the error between an aero-engine fault system and the reference model of the aero-engine fault system is observed through the error interval observer, and the error is fed back to the error feedback controller; and finally, the difference between the reference model output of the fault system and the virtual actuator output is used as a control signal to achieve active fault-tolerant control of the aero-engine. According to the method, when the actuator and the sensor of the aero-engine breaks down, even the disturbance signal exists, the system can be ensured to operate in a desired state without changing the controller, so that the system has good fault-tolerant capability and anti-interference capability.

Description

technical field [0001] The invention relates to an active fault-tolerant control method of an aero-engine based on an error interval observer, which belongs to the technical field of aviation control, and specifically refers to an active fault-tolerant control applied to an aero-engine when actuators and sensors fail and disturbance signals exist method. Background technique [0002] As the only power device of an aircraft, the aero-engine directly affects the safety, reliability and economy of the aircraft. Although a reliable control system design can reduce the occurrence rate of system failures, the actual system structure is complex and the operation is high-intensity. The factors that may cause failures in the system have increased significantly, and the types of failures have become increasingly diverse, and component failures are inevitable. As the driving element of the aero-engine, the actuator is inseparable from the state adjustment of the system. Its workload i...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C9/00
CPCF02C9/00
Inventor 王晔汪锐马艳华杜宪孙希明
Owner DALIAN UNIV OF TECH
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