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Method and device for verifying RS422 bus data of aircraft landing gear system

An aircraft landing gear, RS422 technology, applied in aircraft component testing, electrical digital data processing, detection of faulty computer hardware, etc., can solve problems such as hidden dangers to personnel safety, long cycle, and inability to verify the rationality of landing gear position sensors, etc. Achieve the effect of avoiding potential safety hazards and shortening the verification cycle

Active Publication Date: 2017-05-31
LANDING GEAR ADVANCED MFG
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At present, the verification of the aircraft landing gear control system requires the landing gear to be retracted and retracted, and the verification is performed by simulating the failure state of the landing gear at different positions. This verification method has the following shortcomings: (1). Multiple times of retracting and retracting work, the cycle is long; (2), the position sensor needs to be disassembled during the verification process, the process is cumbersome and has potential safety hazards for personnel (3), the rationality of the landing gear position sensor cannot be fully verified; ( 4) It is impossible to verify the working status of the landing gear system for standby switching when the landing gear control unit fails

Method used

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  • Method and device for verifying RS422 bus data of aircraft landing gear system
  • Method and device for verifying RS422 bus data of aircraft landing gear system
  • Method and device for verifying RS422 bus data of aircraft landing gear system

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Embodiment Construction

[0016] The present invention includes a normally closed switch, two RS422 bus transceivers and an information processor, the normally closed switch is placed on the bus communication line between devices, and the bus verification method is controlled by closing and disconnecting, such as figure 1 shown.

[0017] The normally closed switch is closed, the communication bus data between the two devices is directly connected to the corresponding device, the bus receiver receives the parallel bus data and transmits it to the information processor, and the information processor outputs the collected signal to the visualization device to verify whether the data is consistent with the preset electrical The interface parameters are consistent, such as figure 2 shown.

[0018] The normally closed switch is disconnected, the communication bus data is connected to two bus transceivers, and the collected bus data of the control unit is transmitted to the information processor. The inform...

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Abstract

The invention discloses a method and device for verifying the RS422 bus data of an aircraft landing gear system. The device comprises a normally closed switch, two RS422 bus data receivers and an information processor. The RS422 bus data between two equipment in the landing gear system mainly transmits landing gear positions and the working states and current parameters of the equipment, and whether the responding conditions of the whole system satisfy design requirements or not when the landing gear positions and control unit parameters change can be verified by the receiving, reconstruction and transferring of the RS422 data between two mutual-backup control units. The method and device has the advantages that the bus data between the equipment is collected in real time, and the safety and integrity of system verification are guaranteed.

Description

technical field [0001] The invention relates to the field of ground testing of landing gear, in particular to a method and device for verifying RS422 bus data of an aircraft landing gear system. Background technique [0002] At present, the verification of the aircraft landing gear control system requires the landing gear to be retracted and retracted, and the verification is performed by simulating the failure state of the landing gear at different positions. This verification method has the following shortcomings: (1). Multiple times of retracting and retracting work, the cycle is long; (2), the position sensor needs to be disassembled during the verification process, the process is cumbersome and has potential safety hazards for personnel (3), the rationality of the landing gear position sensor cannot be fully verified; ( 4) It is impossible to verify the working status of the backup switch of the landing gear system when the landing gear control unit fails. Contents of...

Claims

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Application Information

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IPC IPC(8): B64F5/60G06F11/22
CPCG06F11/221
Inventor 王鹏路红伟陈各立赵云峰胡纯邓志云
Owner LANDING GEAR ADVANCED MFG
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