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Method for two-sided numeric controlled manufacture of large-scale integral complex constructional element

A complex structure, large-scale technology, applied in the direction of metal processing machinery parts, metal processing equipment, manufacturing tools, etc., to achieve the effect of increasing stability, good condition, and avoiding deformation of parts

Inactive Publication Date: 2007-10-31
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Since numerical control machining places special emphasis on positioning, especially for large-scale overall complex structures, the purpose of this invention is to provide a solution to the problem of the same reference positioning for double-sided machining of large-scale overall complex structures, so as to ensure that the two sides are positioned after two positioning installations. The position and size of the outline are coordinated to ensure the accuracy of the profile

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0019] For beam parts, the beam zero is placed horizontally, and the two process holes are set on the process boss. Since there are several groove features on the part, which are basically evenly distributed, the method of setting compression grooves around the part is adopted. According to the method, the operator only needs to press the pressing groove of the part before processing, and does not need to change the clamping state of the part during the processing.

[0020] For frame parts: the parts are placed horizontally. The part is positioned on one side with two holes, and the two process holes are set on the process boss. Since most of the ribs of the part are at the same height, it is planned to be positioned on the side of the rib. Due to the large size of the parts, it is inconvenient to clamp and disassemble. The backing plate tooling is used, and the process bosses are set around the parts, and the countersunk pressing holes are made on the process bosses, the thre...

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PUM

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Abstract

The invention relates to the dual face digital controlled machining of complex structures that composed of horizontal beam components, positioned using two holes set on the process boss with compression slot set around the component, horizontally set frame component using one side of two holes to position, two process holes set on the boss which set surrounding the component with rib surface as the positioning face, cushion plate as the tool, using countersunk bolt compressing the fixed plate, horizontal set wall plate components using special vacuum sucking tool, machining from the side with less slot, then regarding it as the positioning baseline. It changes the process complexity of existing techniques. It is simple in locating, stable, simple in compression, good in universality, free from special making, avoiding component deformation, compression damage or dimension precision worsening due to clamp change. It can be co-used with other components with certain universality, economical in tooling.

Description

technical field [0001] The invention relates to a process method for double-sided numerical control machining of a large integral complex structural part. Background technique [0002] A large number of aircraft skeleton parts are large-scale overall complex structural parts, which are mainly divided into frames, beams, wall panels, and other types. Usually, the processing of these large parts has the following two situations: [0003] 1. When the part itself has holes and planes, the holes and planes of the part itself, such as the assembly process hole and the web surface of the part, are usually used as the processing and positioning reference. In this way, during the processing, the worker needs to adjust the pressing position while processing. Too much manual intervention, and more processing program segmentation, so that the high-efficiency CNC machining is greatly reduced. [0004] 2. If the part itself has no holes, it will be converted to edge positioning of the pa...

Claims

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Application Information

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IPC IPC(8): B23Q3/00
Inventor 陈雪梅
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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