Aircraft component finishing process rigidity increasing method

A technology for aircraft parts and finishing processing, applied in aircraft assembly and other directions, can solve the problems of machine tool spindle power failure, reduce processing efficiency, affect machine tool life and other problems, avoid long installation and disassembly cycles, simple and convenient installation and disassembly, avoid Effects of Part Interference Problems

Active Publication Date: 2021-10-12
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to their weak rigidity, these parts have the following problems in the finishing process of aircraft components: (1) Due to local weak rigidity, vibration or knife springs occur during component processing, which affects the quality and accuracy of the processed surface; (2) The processing During the process, the vibration is large, which affects the life of the machine tool, and even causes the power failure of the machine tool spindle; (3) causes increased tool wear and reduces tool life; efficiency

Method used

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  • Aircraft component finishing process rigidity increasing method
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  • Aircraft component finishing process rigidity increasing method

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Embodiment

[0049] Such as Figure 1-6 As shown, the present embodiment provides a method for increasing the rigidity of an aircraft component finishing process, comprising the following steps:

[0050] Step S1: Determine the area to be stiffened;

[0051]Step S2: Determine the gluing module 4 according to the area to be stiffened, and the specific steps include:

[0052] Step S21: In the digital model, measure the edge height Hy of the part to be stiffened, and select the module length a of the glue module 4 according to the edge height Hy;

[0053] Step S22: Measure the aperture D and the hole spacing e of the holes to be made in the area to be stiffened, and select the module width d of the adhesive module 4 according to the aperture D and the hole spacing e;

[0054] Step S23: According to the module length a and the module width d, and referring to the preset glue module standard series list, select the corresponding glue module 4; wherein, the glue module standard series list incl...

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Abstract

The invention discloses an aircraft component finishing process rigidity increasing method, and relates to the technical field of aircraft assembly. The method comprises the following steps: S1, determining an area for rigidity increasing; S2, determining an adhesive module according to the area for rigidity increasing; S3, determining an adhesive according to the determined adhesive module; S4, pasting a quick-release adhesive tape on the area for rigidity increasing, and pasting a quick-release adhesive tape on the outer surface of the determined adhesive module; S5, evenly smearing the adhesive which is determined in the step S3 on the back face of the quick-release adhesive tape in the area for rigidity increasing, and pressing the adhesive module determined in the step S2 at the position of the area for rigidity increasing, and, after the adhesive is cured, completing the rigidity increasing. The method has the advantages that the finishing process rigidity of a weak-rigidity area of an aircraft component can be effectively improved, finishing vibration and local deformation of an aircraft component are reduced, and the finishing precision of an aircraft component is improved.

Description

technical field [0001] The application relates to the technical field of aircraft assembly, in particular to a method for increasing the rigidity of an aircraft component finishing process. Background technique [0002] The finishing process of aircraft components has high requirements on the accuracy of the body shape. The aircraft body is mainly composed of thin-walled frame beam structures, in which there are a large number of thin-walled high-edge strips, long beams and other parts. There are many problems in the process of processing, such as difficulty and difficult to guarantee the processing accuracy. In the part processing stage, the parts can be clamped by designing special fixtures, vacuum adsorption and other methods to meet the processing requirements of the parts. Due to the weak rigidity of such parts, the following problems exist in the finishing process of aircraft components: (1) Due to local weak rigidity, vibration or knife springing occurs during part p...

Claims

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Application Information

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Patent Type & AuthorityApplications(China)
IPC IPC(8): B64F5/10
CPCB64F5/10
Inventor周裕力舒阳冯若琪何鹏陈雪梅陈清良叶翔宇李栎森
OwnerCHENGDU AIRCRAFT INDUSTRY GROUP