Method for judging machinability of aircraft component compensation layer

Abstract

The invention belongs to the technical field of aircraft component assembly, and particularly relates to a method for judging the machinability of an aircraft component compensation layer, which comprises the following steps of: obtaining a rule between a cutting load and a cutting parameter through a cutting test, and determining a limit cutting parameter; combining the structural characteristics of the section, partitioning the processing surface of the compensation layer, and calculating to obtain the deformation of all relative stiffness minimum points on the section and the minimum structural stiffness; designing a box section test piece according to requirements, performing partitioning according to box section structural characteristics, and obtaining deformation of all relative rigidity minimum points on a box section and the minimum structural rigidity through calculation; and determining critical machining deformation, and judging the machinability of the section compensation layer on the basis of the critical machining deformation in combination with rules among the parameters, so that optimization of the cutting parameters of all the partitions is achieved. According to the method, a process calculation and analysis method is provided for machinability judgment of the section compensation layer liner, the problems of machining vibration and debonding in the machining process can be predicted, and parts which cannot be machined can be accurately positioned.

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 ...

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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.

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