A method of increasing the rigidity of aircraft component finishing process

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, and affect machine tool life, etc., to avoid long installation and disassembly cycles, easy installation and disassembly, and avoid Effects of Part Interference Problems

Active Publication Date: 2022-01-25
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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  • A method of increasing the rigidity of aircraft component finishing process
  • A method of increasing the rigidity of aircraft component finishing process
  • A method of increasing the rigidity of aircraft component finishing process

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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 present application discloses a method for increasing the rigidity of an aircraft component finishing process, which relates to the technical field of aircraft assembly, and includes the following steps: Step S1: Determine the area to be stiffened; Step S2: Determine the adhesive module according to the area to be stiffened; Step S3: Determine the adhesive according to the determined gluing module; Step S4: Paste the quick-release tape on the area to be stiffened, and at the same time paste the quick-release tape on the outer surface of the determined gluing module; Step S5: Apply the adhesive determined in Step S3 Apply evenly on the back of the quick-release tape in the area to be stiffened, press the adhesive module determined in step S2 on the area to be stiffened, and complete the stiffening after the adhesive is cured. This application has the ability to effectively improve the weakness of aircraft components The rigidity of the machining process in the rigid area, the advantages of reducing machining vibration and local deformation of aircraft components, and improving the finishing accuracy of aircraft components.

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 & AuthorityPatents(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