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Numerically controlled processing method for plane wing rib beam part

A processing method and wing technology, which is applied to metal processing machine parts, metal processing, metal processing equipment, etc., can solve the problems of complex structure, easy deformation of processing, and difficult clamping, so as to achieve stable processing and control of processing deformation , the effect that the surface quality of the part is satisfied

Active Publication Date: 2009-07-15
XIAN AIRCRAFT BRANCH OF XIAN AIRCRAFT INT
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This type of parts generally has the characteristics of complex structure, easy deformation during processing, and difficult clamping.

Method used

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  • Numerically controlled processing method for plane wing rib beam part
  • Numerically controlled processing method for plane wing rib beam part
  • Numerically controlled processing method for plane wing rib beam part

Examples

Experimental program
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Embodiment Construction

[0019] figure 1 The outline size of the aircraft upper lip parts shown is 2300×230×220mm, the main structural feature is the double edge plate structure with notches on the web and the bottom, the maximum closed angle is 22.6 degrees, and the height of the edge plate is 72-95mm , web thickness 5-8mm, edge plate thickness 5-8mm. Parts processing accuracy requirements: web tolerance ±0.2, edge plate tolerance ±0.2, shape tolerance +0.05 / -0.30, flatness overall length 0.8, edge plate spacing tolerance +0.5 / -0.1, machined surface Ra3.2.

[0020] processing figure 1 The profile wool 2 such as figure 2 As shown, it is a stretch-bending profile, and the section of the profile is a double cross structure. The processing equipment adopts five-coordinate CNC machine tools, which meet the requirements of speed, stroke, swing angle range, spindle power, control system, etc. according to the specific product structure characteristics.

[0021] Processing flow such as image 3 As show...

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Abstract

The invention discloses a digital control processing method for a rib boom part of the aircraft wing, comprising a rough lumber profile with processing margin and a positioning clamp. The rough lumber profile is a multi-surface structure which is provided with a long-striped web plate and a rim plate, and the web plate and the rim plate are drawn bent and molded and form a certain angle. The positioning clamp is provided with a supporting plane and a positioning pin. The particular processing method is that a stress releasing gap is arranged on the web plate, and processing positioning reference is firstly set up before the extensive processing and intensive processing.

Description

technical field [0001] The invention relates to the technical field of aircraft manufacturing, in particular to a high-efficiency numerical control machining method for aircraft wing ribs. Background technique [0002] Ribs are typical connecting parts in aircraft structures, which are generally difficult to process and require high precision. The main structural features of the ribs involved in the present invention are webs and webs that form a certain angle with the webs. The long strip structure is formed, the wool of the rib and edge parts is formed by stretch bending, the section of the profile is small, and the structural characteristics of the ultra-long length, the aspect ratio is about 10 times. Such parts generally have the characteristics of complex structure, easy deformation during processing, and difficult clamping. Contents of the invention [0003] The purpose of the invention is to disclose a numerical control machining method of aircraft wing rib flange...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23Q3/00B23Q15/00B23P25/00
Inventor 田辉周文东
Owner XIAN AIRCRAFT BRANCH OF XIAN AIRCRAFT INT
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