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Aircraft landing gear position detection method for fault self-diagnosis

A technology for aircraft landing gear and detection methods, applied to measuring devices, electrical devices, instruments, etc., can solve problems such as difficult coil identification, and achieve the effects of preventing unsafe effects, long life, and high reliability

Inactive Publication Date: 2015-05-27
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, it is difficult for existing inductive proximity sensors to identify faults such as coil open circuit and short circuit.

Method used

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  • Aircraft landing gear position detection method for fault self-diagnosis
  • Aircraft landing gear position detection method for fault self-diagnosis

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0013] The implementation process of embodiment 1 is as follows:

[0014] first step, see figure 2 , the proximity sensor is installed near the structure of the upper lock of the landing gear and the lower lock of the landing gear through the installation bracket. To be sure, the anti-rotation gasket of the proximity sensor should be installed correctly. The body of the proximity sensor cannot rotate around the axis. The material of the target is stainless steel, the grade is 0Cr15Ni5Cu4Nb. After the target is installed, it should be able to move up and down with the landing gear of the aircraft. For movement, the installation gap between the target and the proximity sensor is 2mm, and the tolerance is plus or minus 0.4mm. The sensing surface of the proximity sensor and the target plane should be kept parallel, see figure 2 , the distance X between the center of the sensing surface of the proximity sensor and the edge of the target should be greater than or equal to 3mm. Ac...

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Abstract

The invention relates to the technical field of aircraft landing gear control, in particular to an aircraft landing gear position detection method for fault self-diagnosis. The current position of an aircraft landing gear is judged by an inductance type proximity sensor according to the position of a regular-shaped metallic object mounted on the aircraft landing gear; state information, acquired by the inductance type proximity sensor, is outputted through a sensor acquisition chip; when faults, such as circuit break and short circuit, of a coil in the inductance type proximity sensor take place, fault information is outputted through a fault output port of the sensor acquisition chip, so that when the position information of the aircraft landing gear is used, the incredible position information of the inductance type proximity sensor is shielded by an aircraft upper-level system, and unsafe influences on an aircraft landing gear system due to wrong position indication are prevented.

Description

technical field [0001] The invention relates to the technical field of aircraft landing gear control, in particular to an aircraft landing gear position detection method for fault self-diagnosis. Background technique [0002] Whether the aircraft landing gear position indication system can work normally will seriously affect the safety of the aircraft. Now the aircraft landing gear position indication system uses an inductive proximity sensor to obtain the position information of the aircraft landing gear, and the inductive proximity sensor is a two-wire passive sensor. The detection principle adopts the variable reluctance technology, and the target of the metal object is used as the target. When the target approaches the sensor detection surface, the impedance of the sensor changes, thereby judging the distance between the target and the sensor. The inductive proximity sensor has the characteristics of high reliability, long life, non-contact measurement, full metal seal,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01B7/00
Inventor 李志勇常凯李胜军
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA