Weakly rigid aviation structural member small stress filling and shock absorption clamping machining method

Abstract

The invention relates to the field of machining of aviation structural members, in particular to a weakly rigid aviation structural member small stress filling and shock absorption clamping machining method. The method includes the steps of firstly, installing clamps which can support an aviation structural member at the two ends of the aviation structural member in the length direction; secondly, fixedly installing a supporting body penetrating through the aviation structural member between the clamps at the two ends of the aviation structural member; thirdly, filling the inner portion of the aviation structural member with fluid capable of being solidified, wrapping a supporting body in the fluid, and filling the internal space of the aviation structural member; fourthly, solidifying the fluid, completing clamping, and conducting machining. The invention aims at providing the weakly rigid aviation structural member small stress filling and shock absorption clamping machining method which can reduce the machining cost, improve the machining efficiency and reduce the study cost of workers.

Description

technical field [0001] The invention relates to the processing field of aeronautical structural parts, in particular to a small-stress filling and shock-absorbing clamping processing method for weakly rigid aeronautical structural parts. Background technique [0002] Some of the aeronautical structural parts are frame-type parts, which have poor rigidity, and mechanical processing will cause strong vibrations, and even cannot be processed; [0003] In the prior art, the solution to this problem is to use a large number of fixtures and adopt different clamping schemes for parts with different rigidities. At the same time, the cutting parameters are also individually matched. To make a complete scheme, it is necessary to produce Manufacture a large number of fixtures, and at the same time the clamping position, contact area, etc., need to go through long-term experience accumulation, or complex finite element analysis, and after clamping, for the processing of structural parts...

AI Technical Summary

Problems solved by technology

[0002] Some of the aeronautical structural parts are frame-type parts, which have poor rigidity, and mechanical processing will cause strong vibrations, and even cannot be processed;

[0003] In the prior art, the solution to this problem is: using a large number of fixtures, adopting different clamping schemes for parts with different rigidities, and at the same time, the cutting parameters are also individually matched, and to make a complete scheme, production is required. Manufacture a large number of fixtures, and at the same time the clamping position, contact area, etc., need to go through long-term experience accumulation, or complex finite element analysis, and after clamping, for the processing of structural parts, due to the different rigidity of each part, so The processing plan also requires long-term experience accumulation or complex finite element analysis, which is usually very conservative, because the rigidity of this frame-type aerospace structural part is not enough, and if vibration occurs during processing, there will be large errors;

[0004] As mentioned above, these processes will seriously increase the processing cost of aerospace structural parts, and at the same time, the efficiency is very low, and the learning cost of workers is relatively high.

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