Method for stress monitoring of aircraft assembly process based on appearance detection

A technology for aircraft assembly and shape detection. It is applied in the direction of measuring force, measuring device, and optical device. It can solve problems such as lack of monitoring and parts deformation, and achieve the effect of improving assembly quality, prolonging aircraft life, and easy operation.

Active Publication Date: 2019-06-11
CHENGDU AIRCRAFT INDUSTRY GROUP
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AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a stress monitoring method in the aircraft assembly process based on shape detection, which is used to solve the problem in the prior art that the lack of monitoring in the assembly process easily causes deformation of parts

Method used

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Embodiment 1

[0039] A method for monitoring stress in an aircraft assembly process based on shape detection, comprising:

[0040] Step S100: hoisting component A and component B into place;

[0041] Step S200: Set the public measurement points on the ground, establish the aircraft coordinate system and measure the key points of the shape of parts A and B respectively, and adjust the attitude of parts A and B according to the key points of the shape; after the attitude adjustment of parts A and B is completed The coordinates of the key points of the shape of the vehicle are used as the initial value, recorded to the initial data storage unit, and transmitted to the data operation unit together with the record of the sortie;

[0042] Step S300: fix component A, move component B along the course to approach component A, and perform pre-alignment of component A and component B;

[0043] Step S400: Trial assembly of the skeleton and skin of the transition section, monitor the process position ...

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Abstract

The invention discloses a method for stress monitoring of an aircraft assembly process based on appearance detection. The method comprises the following steps of hoisting a component A and a componentB into places; establishing an aircraft coordinate system and measuring appearance key points of the component A and the component B respectively, recording coordinate records of the appearance key points after posture adjustment of the component A and the component B to an initial data storage unit and transmitting to a data operation unit; pre-aligning the component A and the component B; carrying out trail assembly on a transition section framework and skin, monitoring process positions of the appearance key points by using a measuring instrument, and sending the process positions to the data operation unit; comparing location degree of the appearance key points through the data operation unit, if the change exceeds a preset threshold value, giving out an alarm, and otherwise installing the transition section framework and the skin. According to the method, the transition section framework is installed under a condition of monitoring the coordinate condition of the appearance key points, so that the deformation of the parts at a docking part due to the assembly stress generated by forced assembly is avoided, the assembly quality is improved, the service life of the aircraft isprolonged, and the assembly stress of the docking process of the aircraft is reduced.

Description

technical field [0001] The invention relates to the technical field of aircraft manufacturing and assembly, in particular to a stress monitoring method for an aircraft assembly process based on shape detection. Background technique [0002] Aircraft manufacturing is generally divided into multiple large parts such as front fuselage, middle fuselage, rear fuselage, and wings. As a key link in aircraft manufacturing, an important task of aircraft component assembly is to use tooling and equipment to combine these large components into a whole according to the principle of size coordination. The traditional assembly of large aircraft components is guaranteed by special matching tooling, using optical instruments such as levels and theodolites for measurement, and relying on the cooperation of cranes and traction for component attitude adjustment and docking. The efficiency is low, stress assembly is easy to occur, and assembly quality is poor. With the development of digital a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01L1/00G01B11/00
Inventor 刘顺涛郭喜锋李松郑和银宋金辉彭志军谭明维
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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