A Judgment Method for Machinability of Compensation Layer of Aircraft Parts

A technology of aircraft parts and compensation layers, applied in the direction of sustainable transportation, instruments, geometric CAD, etc., can solve the problems of insufficient machinability judgment methods, low efficiency, debonding, etc., to ensure work efficiency, low cost, and easy implementation Effect

Active Publication Date: 2022-01-11
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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.

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  • A Judgment Method for Machinability of Compensation Layer of Aircraft Parts
  • A Judgment Method for Machinability of Compensation Layer of Aircraft Parts
  • A Judgment Method for Machinability of Compensation Layer of Aircraft Parts

Examples

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Embodiment 1

[0069] This embodiment discloses a method for judging the machinability of an aircraft component compensation layer, as a basic implementation of the present invention, such as figure 1 shown, including the following steps:

[0070] S1, design the cutting test, obtain the law between the cutting load and the cutting parameters through the cutting test, and determine the limit cutting parameters;

[0071] S2, combined with the structural characteristics of the section (the section structure is left-right symmetrical, bounded by the mid-plane of the web of the rib, frame and beam, and the edge of the edge), the processing surface of the compensation layer liner is divided to form Section processing area, such as Figure 6 and Figure 7 As shown, it is divided into 83 section processing areas, Figure 7 (1-1)~(1-83) in each represent a section processing area, and each section processing area has a relative stiffness minimum point ( Figure 8 As shown, the edge of the compe...

Embodiment 2

[0086] This example discloses a method for judging the machinability of an aircraft component compensation layer. As a preferred embodiment of the present invention, that is, in Example 1, the cutting test in step S1 is to select EW100 fiberglass composite material as the compensation layer lining Pad, carry out mechanical performance test, and calibrate the cutting mechanical performance of compensation layer pad, including the following steps:

[0087] S1-1, bonding a 2mm thick compensation layer liner on the aluminum alloy plate;

[0088] S1-2, the bottom of the aluminum alloy plate is connected to the dynamometer, and the dynamometer is directly below the pad of the compensation layer, such as Figure 5 shown;

[0089] S1-3, based on the numerical control system of the machine tool, set the processing parameters for the compensation layer liner. Among the processing parameters, the radial depth of cut ; Preferably, the cutting tool used by the machine tool for processin...

Embodiment 3

[0096] This example discloses a method for judging the machinability of an aircraft component compensation layer. As a preferred embodiment of the present invention, that is, in Example 2, the limit cutting parameter in step S1 is the maximum machinable value of the compensation layer liner. radial depth of cut , and the maximum radial depth of cut is based on the bond-peel strength of the compensation liner To determine the bond-peel strength of the compensation layer liner Including the tear-off strength between the FRP composite material and the glue and the tear-off strength between the aluminum alloy plate and the glue is , then the maximum radial depth of cut The determination includes the following steps:

[0097] S1-6, based on , combined with of axis, axis and range of axis orientations, obtain the formula and , then during the cutting process, the tangential cutting load borne by the compensation layer liner ;

[0098] S1-7, order and ...

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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 ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/17G06F30/20G06F111/10G06F119/14
CPCG06F30/15G06F30/17G06F30/20G06F2111/10G06F2119/14Y02T90/00
Inventor 陈雪梅舒阳叶翔宇陈清良骆金威益建朋潘雨勾江洋
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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