A Judgment Method for Machinability of Compensation Layer of Aircraft Parts

Abstract

The invention belongs to the technical field of aircraft component assembly, and particularly relates to a method for judging the machinability of compensation layers of aircraft components, including obtaining the law between cutting load and cutting parameters through cutting tests, and determining the limit cutting parameters; combined with the structural characteristics of sections, Divide the processing surface of the compensation layer, calculate and obtain the deformation and minimum structural stiffness of all points with the minimum relative stiffness on the section; design the test piece of the box section according to the requirements, and partition according to the structural characteristics of the box section, and calculate and obtain all the relative stiffness points on the box section. Deformation at the point of minimum stiffness and minimum structural stiffness; determine the critical machining deformation, based on the critical machining deformation, combined with the rules among the parameters, to judge the machinability of the section compensation layer, so as to realize the optimization of cutting parameters in each zone. The invention provides a process calculation and analysis method for judging the machinability of the section compensation layer liner, can predict the processing vibration and debonding problems in the processing process, and can accurately locate the unprocessable parts.

Description

technical field [0001] The invention belongs to the technical field of aircraft component assembly, in particular to a method for judging the machinability of compensation layers of aircraft components. Background technique [0002] When developing a new type of aircraft, in order to ensure the stealth performance of the aircraft, improve the shape accuracy and interchangeability of the aircraft components; after the skeleton assembly of the aircraft components is completed (such as figure 2 shown), a compensation layer needs to be bonded on the edge of the frame (such as image 3 As shown), the shape accuracy of the skeleton is guaranteed by CNC cutting the compensation layer. The component skeleton is composed of frames, beams and other structures, and the structure of the area to be processed is ribs, web surfaces, edge strips, and compensation layers (such as Figure 4 shown). [0003] The edge strip of the segmental skeleton structure is a thin-walled structure, the ...

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to solve the problem of "insufficient method for judging the machinability of the compensation layer bonded to the edge strip surface of the component, which leads to blindly increasing the rigidity and resistance of the edge strip surface of the component during the processing process, resulting in low efficiency, or the occurrence of snapping knives." , debonding and other problems”, a calculation and analysis method for judging the machinability of the compensation layer of aircraft parts is proposed, so as to predict the machinability of the compensation layer in the section design stage and judge the machinability of the structure in advance; Moreover, the method can optimize cutting parameters, improve processing efficiency, and is simple to implement and high in efficiency.

Images