CN103586515A

CN103586515A - Numerically-controlled milling method for skin-covered components

Info

Publication number: CN103586515A
Application number: CN201310574914.4A
Authority: CN
Inventors: 段雪锋; 张新娟; 王新磊; 林阳凯; 梁超芳
Original assignee: AVIC Aircraft Corp Xian Aircraft Branch
Current assignee: AVIC Aircraft Corp Xian Aircraft Branch
Priority date: 2013-11-15
Filing date: 2013-11-15
Publication date: 2014-02-19

Abstract

The invention discloses a numerically-controlled milling method for skin-covered components. The numerically-controlled milling method comprises the following steps: inner contour data and outer contour data of a component are known; the component is clamped on a flexible fixture for milling an inner contour line and an outer contour line; while machining of outer contour, a plurality of notches as deep as the outer contour line of the component are uniformly machined on the outer edge of the outer contour of the component first, and then the outer contour is milled along the outer contour line; during machining of an inner contour, a zigzag slot of which the edge stops at the inner contour line is machined in the inner contour line of the component first, and then the inner contour is milled along the inner contour line.

Description

A kind of covering class part by numerical control milling method

Technical field

The present invention relates to aero-manufacturing technology, relate to the milling method of the large complicated covering of aircraft, is directly a kind of milling method of covering class part by numerical control machining profile.

Background technology

At present, along with the develop rapidly of Computerized Numerical Control processing technology, airplane design technology, the large former hand cut before this of skin part on aircraft, existing these large skin parts adopt flexible clamping and 5 Shaft and NC Machining Test milling machines to carry out milling profile.And typical feature during aircraft skin class part by numerical control processing milling profile is that part is thin, curvature is large, easy chatter, and covering outer rim (also claiming overlap) easily causes cutting tool chatter.How making skin part milling smoothly, solve covering overlap chatter, the phenomenon of forging a knife, is a problem that must solve in covering class part modernization processing.

Summary of the invention

The object of the present invention is to provide a kind of covering class part by numerical control milling method, more particularly the method for the inside and outside profile of digital control milling after covering class flexible part clamping.

A kind of covering class part by numerical control milling method, the inside and outside profile shape data of known part, by parts fixation on flexible fixture, the inside and outside outline line of milling, it is characterized in that: while 1) processing outline, first the profile outer rim at part processes a plurality of breach uniformly, and the degree of depth of breach terminates in the outer contour of part, and then goes out outline along outer contour milling; 2) while processing interior profile, first in the inner outline of part, process "the" shape groove, the edge of " it " word groove terminates in inner outline place, and then goes out interior profile along inner outline milling.

The invention has the advantages that in covering outer rim to be on overlap, to process uniformly breach, during milling covering outline, overlap is understood one, one falling down, thereby can make overlap under the smooth milling of skin part.Profile in processing first in profile, mills out " it " word groove in part, mill off " it " word groove, and the cutter that do not quiver around the corner of the interior profile cutters track after completing, has solved covering turning chatter and has gnawed cutter phenomenon, has guaranteed quality and the efficiency of skin part.Solve that aircraft skin (on flexible fixture) digital control milling profile overlap is forged a knife and the problem of chatter.

By reference to the accompanying drawings, with reference to detailed description below, the present invention itself will be able to clearer understanding with its object and thing followed advantage.

Accompanying drawing explanation

Fig. 1 is aircraft skin part schematic diagram.

Fig. 2 is that aircraft skin parts fixation is illustrated on flexible fixture.

Fig. 3 is the signal of aircraft skin part by numerical control process.

Number description: 1 skin part, 2 breach, 3 outer contours, 4 "the" shape grooves, 5 inner outlines, 6 flexible frocks

Specific embodiment

Referring to accompanying drawing, Figure 1 shows that aircraft skin part 1 locates on flexible frock 6, the inside and outside profile shape data of this skin part 1 is known, during processing outline, first the profile outer rim at part processes a plurality of breach 2 uniformly, the degree of depth of breach terminates in the outer contour 3 of part, and then cuts out outline along the clean side milling of outer contour, now; During the interior profile of processing, first in the inner outline of part, process "the" shape groove 4, the edge of "the" shape groove terminates in inner outline 5 places, and then cuts out interior profile along the clean side milling of inner outline 5.

Although the present invention is suitable for the aircraft digital control milling inside and outside contour of skin part on flexible frock of boarding a plane, and is also applicable to clamping and the milling of various covering class parts, and the material on part can be aluminium, steel, and titaniums etc., also have some nonmetallic materials.

Claims

1. a covering class part by numerical control milling method, the inside and outside profile shape data of known part, by parts fixation, on flexible fixture, the inside and outside outline line of milling, is characterized in that:

1) while processing outline, first the profile outer rim at part processes a plurality of breach uniformly, and the degree of depth of breach terminates in the outer contour of part, and then goes out outline along outer contour milling;

2) while processing interior profile, first in the inner outline of part, process "the" shape groove, the edge of " it " word groove terminates in inner outline place, and then goes out interior profile along inner outline milling.