CN104476109A - Skin structure accurate positioning machining method - Google Patents

Skin structure accurate positioning machining method Download PDF

Info

Publication number
CN104476109A
CN104476109A CN201410498066.8A CN201410498066A CN104476109A CN 104476109 A CN104476109 A CN 104476109A CN 201410498066 A CN201410498066 A CN 201410498066A CN 104476109 A CN104476109 A CN 104476109A
Authority
CN
China
Prior art keywords
covering
machining
machine tool
processing
error
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201410498066.8A
Other languages
Chinese (zh)
Inventor
尹峰
姚为
张素敏
张珊珊
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Beijing Hangxing Technology Development Co Ltd
Original Assignee
Beijing Hangxing Technology Development Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Beijing Hangxing Technology Development Co Ltd filed Critical Beijing Hangxing Technology Development Co Ltd
Priority to CN201410498066.8A priority Critical patent/CN104476109A/en
Publication of CN104476109A publication Critical patent/CN104476109A/en
Pending legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23PMETAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00Making specific metal objects by operations not covered by a single other subclass or a group in this subclass

Abstract

The invention discloses a skin structure accurate positioning machining method. The skin structure accurate positioning machining method comprises the following steps of firstly presetting rough reference positioning before forming of the skin; secondly accurately measuring through an online measuring technology before machining and determining a finish machining standard; thirdly machining the skin shape through the accurate positioning machining standard, measuring three-dimensional space coordinates again after machining of the skin shape is achieved, comparing the three-dimensional space coordinates, enabling a comparative error to be the positioning error, performing the step two and the step three in a repeat mode if the error is larger than a design error until the comparative error confirms to the design error, feeding data back to a numerical control machine tool to perform accurate positioning machining. The skin structure accurate positioning machining method is simple and convenient and accurate in positioning, greatly improves the product yield, reduces costs and is applicable to application and popularization.

Description

A kind of accurate positioning and processing method of stressed-skin construction
Technical field
The invention belongs to processing and manufacturing technical field, be specifically related to a kind of accurate positioning and processing method of complex space stressed-skin construction.
Background technology
Along with the development of Aero-Space cause, the performance of aircraft, spacecraft is had higher requirement, with regard to the manufacture of modern spacecraft, be characterized in lightweight, structural strength is high.Reduce self structure weight, just mean improve aircraft mobility, increase and take load-carrying ability and farther flying distance.For this reason, in structural design, the large complicated lightweight structure of more employing, makes complicated stressed-skin construction part be on the increase, but cannot accurately locate after complicated stressed-skin construction forming parts, bring very large difficulty to following process.
Summary of the invention
The object of this invention is to provide a kind of accurate positioning and processing method of complex space stressed-skin construction, the difficult point cannot accurately located after overcoming complicated stressed-skin construction forming parts, achieve the accurate location processing of complex space stressed-skin construction, solve space stressed-skin construction in manufacture process shaping after the shortcoming that cannot accurately locate.
In order to reach above-mentioned purpose of design, the technical solution used in the present invention is as follows:
An accurate positioning and processing method for stressed-skin construction, concrete steps are as follows:
The first step: preset roughing standard location before covering forming:
(1) on covering forming mould, arranging sample rushes a little,
(2) adopt covering forming mould to carry out shaping to covering, the sample punching point pre-set can be protruding in the correspondence position formation sample punching of mould at covering in the process of covering forming, and namely this projection can be used as the roughing standard of covering processing.
Second step: adopt line Measurement Technique accurately to measure before processing, determine fine finishining benchmark:
(1) measurement is carried out in same frock with processing, according to the roughing standard of step one, carries out centering, carries out processing reset after clamping completes, the spatial surface of covering is chosen measurement point uniformly and measures;
(2) will to gather and the measurement point space coordinates be stored on Digit Control Machine Tool is transferred to computer, utilize machining 3 D model to carry out the space coordinates comparison of measurement point, obtain measurement point position deviation;
(3) on threedimensional model, carry out the matching of minimum work difference according to the space coordinates of measurement point, obtain covering and accurately locate machining benchmark;
3rd step: adopt Digit Control Machine Tool to utilize accurately location machining benchmark numerical programming procedure to carry out the processing of covering external form, after machining, remeasure the three dimensional space coordinate of the covering external form point that second step is chosen, computer is transmitted back after record, again contrast with threedimensional model, compare error is position error, if this error is greater than design tolerance, repeat step 2, three, until compare error meets design tolerance, by this data feedback Digit Control Machine Tool, accurately locate processing.
Preferably, there is relative size position relationship with mould in sample punching point, tentatively can determine locating and machining benchmark, but due to the extension relation of covering forming, sample fills point location error generally more than 1mm, only for processing coarse positioning after covering forming.
Preferably, in step 2, described measurement point of choosing uniformly on the spatial surface of covering carries out measuring method and is: adopt Digit Control Machine Tool as measuring table, machine tool chief axis installs and measures head, use side head to measure the measurement point chosen one by one, obtain the space coordinates of measurement point and be stored on Digit Control Machine Tool.
Preferably, in step 2, the method of carrying out the matching of minimum work difference according to the space coordinates of measurement point on threedimensional model is: by adjusting X, Y, Z tri-translation shaft and completing around three turning cylinders of X, Y, Z, record the coordinate motion track of three-dimensional matching, as the foundation of adjustment Digit Control Machine Tool Cutter coordinate system, the method for adjustment Digit Control Machine Tool Cutter coordinate system is adopted to carry out external form digitlization adjustment to covering.
The beneficial effect of the accurate positioning and processing method of complex space stressed-skin construction of the present invention is: the method is simple, convenient, and accurate positioning, drastically increases the qualification rate of product, decrease cost, be suitable for application.
The present invention proposes the accurate positioning and processing method of a kind of complex space stressed-skin construction class part, improve in complex space stressed-skin construction class part process and accurately locate a difficult problem, improve positioning precision.This intellectual achievement applies to produce very large economic benefit in actual production, has very strong application prospect.
Detailed description of the invention
Below in conjunction with accompanying drawing, optimum implementation of the present invention is described in further detail.
The accurate positioning and processing method of the complex space stressed-skin construction described in the embodiment of the present invention, concrete steps are as follows:
The first step: preset roughing standard location before covering forming:
(1) on covering forming mould, arranging sample rushes a little, there is relative size position relationship with mould in this sample punching point, tentatively can determine locating and machining benchmark after covering forming, but due to the extension relation of covering forming, sample fills point location error generally more than 1mm, only for processing coarse positioning;
(2) adopt covering forming mould to carry out shaping to covering, the sample punching point pre-set can be protruding in the correspondence position formation sample punching of mould at covering in the process of covering forming, and namely this projection can be used as the roughing standard of covering processing.
Second step: adopt line Measurement Technique accurately to measure before processing, determine fine finishining benchmark:
(1) measurement is carried out in same frock with processing, according to the roughing standard of step one, carry out centering, processing reset is carried out after clamping completes, the spatial surface of covering is chosen measurement point uniformly measure, this measurement adopts Digit Control Machine Tool as measuring table, and machine tool chief axis installs and measures head, use side head to measure the measurement point chosen one by one, obtain the space coordinates of measurement point and be stored on Digit Control Machine Tool;
(2) will to gather and the measurement point space coordinates be stored on Digit Control Machine Tool is transferred to computer, utilize machining 3 D model to carry out the space coordinates comparison of measurement point, obtain measurement point position deviation;
(3) on threedimensional model, the matching of minimum work difference is carried out according to the space coordinates of measurement point, this matching is by adjustment X, Y, Z tri-translation shaft and complete around three turning cylinders of X, Y, Z, record the coordinate motion track of three-dimensional matching, as the foundation of adjustment Digit Control Machine Tool Cutter coordinate system, adopt the method for adjustment Digit Control Machine Tool Cutter coordinate system to carry out external form digitlization adjustment to covering, obtain covering and accurately locate machining benchmark;
3rd step: adopt Digit Control Machine Tool to utilize accurately location machining benchmark numerical programming procedure to carry out the processing of covering external form, after machining, remeasure the three dimensional space coordinate of the covering external form point that second step is chosen, computer is transmitted back after record, again contrast with threedimensional model, compare error is position error, if this error is greater than design tolerance, repeat step 2, three, until compare error meets design tolerance, by this data feedback Digit Control Machine Tool, accurately locate processing.
Embodiment:
Adopt the hot forming of 6mm titanium alloy covering, carry out after shaping being processed to form final products.Technical scheme is:
One, design covering expanded view, design shaping corner surplus, clearly punching point position, design hot forming frock, in frock, design sample according to punching point position and rush a little, carry out thermoforming work;
Two, utilize sample to rush point and carry out centering, processing reset is carried out after clamping completes, Cutter coordinate system is utilized to carry out on-line measurement work, computer and gross data measurement result is used to compare, carry out the inching of in-process measurement coordinate system according to comparing result, result feedback process equipment will be adjusted, again measure, compare, until measurement result meets design tolerance;
Three, final data is fed back system of processing, accurately locate processing; Holotype face DATA REASONING is carried out after processing.Measurement result shows, the positioning precision of part meets design instructions for use.
Above content is the further description done the present invention in conjunction with concrete preferred embodiment, and being convenient to these those skilled in the art can understand and apply the invention, and can not assert that specific embodiment of the invention is confined to these explanations.For general technical staff of the technical field of the invention, some simple deduction or replace can also be made without departing from the inventive concept of the premise, and need not through performing creative labour.Therefore, those skilled in the art are according to announcement of the present invention, and the simple modifications made the present invention all should within protection scope of the present invention.

Claims (4)

1. an accurate positioning and processing method for stressed-skin construction, is characterized in that: concrete steps are as follows:
The first step: preset roughing standard location before covering forming:
(1) on covering forming mould, arranging sample rushes a little;
(2) adopt covering forming mould to carry out shaping to covering, the sample punching point pre-set can be protruding in the correspondence position formation sample punching of mould at covering in the process of covering forming, and namely this projection can be used as the roughing standard of covering processing;
Second step: adopt line Measurement Technique accurately to measure before processing, determine fine finishining benchmark:
(1) measurement is carried out in same frock with processing, according to the roughing standard of step one, carries out centering, carries out processing reset after clamping completes, the spatial surface of covering is chosen measurement point uniformly and measures;
(2) will to gather and the measurement point space coordinates be stored on Digit Control Machine Tool is transferred to computer, utilize machining 3 D model to carry out the space coordinates comparison of measurement point, obtain measurement point position deviation;
(3) on threedimensional model, carry out the matching of minimum work difference according to the space coordinates of measurement point, obtain covering and accurately locate machining benchmark;
3rd step: adopt Digit Control Machine Tool to utilize accurately location machining benchmark numerical programming procedure to carry out the processing of covering external form, after machining, remeasure the three dimensional space coordinate of the covering external form point that second step is chosen, computer is transmitted back after record, again contrast with threedimensional model, compare error is position error, if this error is greater than design tolerance, repeat step 2, three, until compare error meets design tolerance, by this data feedback Digit Control Machine Tool, accurately locate processing.
2. the accurate positioning and processing method of stressed-skin construction according to claim 1, it is characterized in that: in step one, relative size position relationship is there is in sample punching point with mould, locating and machining benchmark can be tentatively determined after covering forming, but due to the extension relation of covering forming, sample fills point location error generally more than 1mm, only for processing coarse positioning.
3. the accurate positioning and processing method of stressed-skin construction according to claim 1, it is characterized in that: in step 2, described measurement point of choosing uniformly on the spatial surface of covering carries out measuring method and is: adopt Digit Control Machine Tool as measuring table, machine tool chief axis installs and measures head, use side head to measure the measurement point chosen one by one, obtain the space coordinates of measurement point and be stored on Digit Control Machine Tool.
4. the accurate positioning and processing method of stressed-skin construction according to claim 1, it is characterized in that: in step 2, the method of carrying out the matching of minimum work difference according to the space coordinates of measurement point on threedimensional model is: by adjusting X, Y, Z tri-translation shaft and completing around three turning cylinders of X, Y, Z, record the coordinate motion track of three-dimensional matching, as the foundation of adjustment Digit Control Machine Tool Cutter coordinate system, the method for adjustment Digit Control Machine Tool Cutter coordinate system is adopted to carry out external form digitlization adjustment to covering.
CN201410498066.8A 2014-09-25 2014-09-25 Skin structure accurate positioning machining method Pending CN104476109A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201410498066.8A CN104476109A (en) 2014-09-25 2014-09-25 Skin structure accurate positioning machining method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201410498066.8A CN104476109A (en) 2014-09-25 2014-09-25 Skin structure accurate positioning machining method

Publications (1)

Publication Number Publication Date
CN104476109A true CN104476109A (en) 2015-04-01

Family

ID=52750783

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201410498066.8A Pending CN104476109A (en) 2014-09-25 2014-09-25 Skin structure accurate positioning machining method

Country Status (1)

Country Link
CN (1) CN104476109A (en)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104858865A (en) * 2015-05-13 2015-08-26 南昌航空大学 Aircraft body skin end face allowance cutting mechanical arm
CN105373653A (en) * 2015-10-23 2016-03-02 内蒙古科技大学 Method for positioning large-scale weak-rigidity thin-shell workpieces
CN105436833A (en) * 2015-12-23 2016-03-30 北京航星机器制造有限公司 Precise manufacturing method of cover part with ribs on external
CN106091879A (en) * 2016-06-03 2016-11-09 湖南中岳显控科技股份有限公司 A kind of thin-wall curved-surface parts measurement method
CN106516152A (en) * 2015-09-11 2017-03-22 中国商用飞机有限责任公司 Technological method for finish machining of docking surface of vertical tail and fuselage of aircraft
CN109631773A (en) * 2018-11-22 2019-04-16 成都飞机工业(集团)有限责任公司 A kind of pneumatic face Surface inspection method of composite material parts based on shaping mould
CN109733088A (en) * 2018-12-28 2019-05-10 国营第六一六厂 A kind of numerical control processing technology card design method of process control
CN109746473A (en) * 2017-11-06 2019-05-14 成都飞机工业(集团)有限责任公司 A kind of covering positioning hole forming method
CN109954913A (en) * 2018-11-30 2019-07-02 航天特种材料及工艺技术研究所 A kind of complex profile aerogel plate trimming device and method
CN110116299A (en) * 2019-06-11 2019-08-13 江苏利伟智能制造有限公司 A kind of new-energy automobile inertial navigation unit abnormity sleeve member optimization processing technology
CN110300968A (en) * 2017-02-15 2019-10-01 本田技研工业株式会社 The modification method of molding die and the display methods of deviation information
CN114211200A (en) * 2021-11-04 2022-03-22 宝武集团马钢轨交材料科技有限公司 High-precision machining method for spoke plate holes of wheels

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101650756A (en) * 2009-08-26 2010-02-17 成都飞机工业(集团)有限责任公司 Skinning method of multi-point forming plane
CN201766277U (en) * 2010-09-14 2011-03-16 山东电力集团公司潍坊供电公司 Punching mould
CN102880756A (en) * 2012-09-26 2013-01-16 西北工业大学 Method for compensating precision milling deformation of thin-wall blade
CN103292760A (en) * 2013-06-17 2013-09-11 西北工业大学 Thin-wall blade error analytical method
CN103712532A (en) * 2012-10-09 2014-04-09 首都航天机械公司 Shape and position error detection and evaluation method for skin frame truss structure housing

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101650756A (en) * 2009-08-26 2010-02-17 成都飞机工业(集团)有限责任公司 Skinning method of multi-point forming plane
CN201766277U (en) * 2010-09-14 2011-03-16 山东电力集团公司潍坊供电公司 Punching mould
CN102880756A (en) * 2012-09-26 2013-01-16 西北工业大学 Method for compensating precision milling deformation of thin-wall blade
CN103712532A (en) * 2012-10-09 2014-04-09 首都航天机械公司 Shape and position error detection and evaluation method for skin frame truss structure housing
CN103292760A (en) * 2013-06-17 2013-09-11 西北工业大学 Thin-wall blade error analytical method

Non-Patent Citations (4)

* Cited by examiner, † Cited by third party
Title
刘维伟,李杰光,赵明,田卫军: "航空发动机薄壁叶片加工变形误差补偿技术研究", 《机械设计与制造》 *
北京航空制造工程研究所: "《航空制造技术》", December 2013, 航空工业出版社 *
李遇昌,曾庆亨: "《金属切削加工》", 31 December 1988, 成都科技大学出版社 *
米国发: "《金属加工工艺基础》", 31 March 2000, 东南大学出版社 *

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104858865A (en) * 2015-05-13 2015-08-26 南昌航空大学 Aircraft body skin end face allowance cutting mechanical arm
CN104858865B (en) * 2015-05-13 2016-07-06 南昌航空大学 A kind of aircraft fuselage skin end face surplus cutting manipulator
CN106516152A (en) * 2015-09-11 2017-03-22 中国商用飞机有限责任公司 Technological method for finish machining of docking surface of vertical tail and fuselage of aircraft
CN105373653A (en) * 2015-10-23 2016-03-02 内蒙古科技大学 Method for positioning large-scale weak-rigidity thin-shell workpieces
CN105373653B (en) * 2015-10-23 2018-09-28 内蒙古科技大学 A kind of localization method of large scale weak separation Thin-shell workpiece
CN105436833A (en) * 2015-12-23 2016-03-30 北京航星机器制造有限公司 Precise manufacturing method of cover part with ribs on external
CN106091879A (en) * 2016-06-03 2016-11-09 湖南中岳显控科技股份有限公司 A kind of thin-wall curved-surface parts measurement method
CN110300968A (en) * 2017-02-15 2019-10-01 本田技研工业株式会社 The modification method of molding die and the display methods of deviation information
CN110300968B (en) * 2017-02-15 2021-07-23 本田技研工业株式会社 Method for correcting forming die
CN109746473A (en) * 2017-11-06 2019-05-14 成都飞机工业(集团)有限责任公司 A kind of covering positioning hole forming method
CN109631773A (en) * 2018-11-22 2019-04-16 成都飞机工业(集团)有限责任公司 A kind of pneumatic face Surface inspection method of composite material parts based on shaping mould
CN109631773B (en) * 2018-11-22 2022-05-10 成都飞机工业(集团)有限责任公司 Pneumatic surface profile detection method for composite part based on forming die
CN109954913A (en) * 2018-11-30 2019-07-02 航天特种材料及工艺技术研究所 A kind of complex profile aerogel plate trimming device and method
CN109733088A (en) * 2018-12-28 2019-05-10 国营第六一六厂 A kind of numerical control processing technology card design method of process control
CN110116299A (en) * 2019-06-11 2019-08-13 江苏利伟智能制造有限公司 A kind of new-energy automobile inertial navigation unit abnormity sleeve member optimization processing technology
CN114211200A (en) * 2021-11-04 2022-03-22 宝武集团马钢轨交材料科技有限公司 High-precision machining method for spoke plate holes of wheels

Similar Documents

Publication Publication Date Title
CN104476109A (en) Skin structure accurate positioning machining method
CN104759945B (en) Mobile hole-making robot standard alignment method based on high precision industrial camera
CN107717342B (en) Special-shaped depth blind hole antenna house processing method
CN103753124B (en) Massive casting titanium alloy diamond cabin piece housing processing method
CN106425303B (en) A kind of large thin-wall bay section processing method of casing and fixture
CN104400092B (en) Milling finish machining method for three-dimensional profile with composite inclined surface on outline
CN108253911B (en) A kind of workpiece pose method of adjustment based on measurement point geometrical characteristic iteration registration
CN102865847B (en) Spline curve compensation method for measuring profile deviation based on path unit
CN101000499A (en) Contour machining method and system based on multi-sensor integral measuring
CN103901852B (en) A kind of aircraft is fitted to each other face digitized cushioning method
CN105467927A (en) Registration and alignment-based lineation-free forging-casting part machining positioning method
CN103586513B (en) A kind of processing method of PRECISION HOLE of airplane turbine casing mounting edge
CN103286440A (en) Fast positioning method of laser cutting part
CN110069041A (en) A kind of Work piece processing method and system based on on-machine measurement
CN107238352A (en) A kind of revolution class formation characteristic part profile laser on-machine measurement apparatus and method based on numerically controlled lathe
CN102205480B (en) Method for manufacturing spatial curved surface spiral box type component
CN102554304A (en) Method for machining 45-degree intersected shaft holes of milling head
CN105373078B (en) A kind of micro localization method for processing forging and casting blank
Wang et al. 3D machining allowance analysis method for the large thin-walled aerospace component
CN112757046A (en) Five-axis machine tool online measurement and compensation processing method for free-form surface of thin-wall jewelry
Zuo et al. Integrated geometric error compensation of machining processes on CNC machine tool
CN102267132B (en) Normal flexible scribing method of complicated space curved surface
CN105354360A (en) Method for closed-loop establishment of coordinate measuring control network in aircraft large-component assembling interface finish machining
CN202028810U (en) Milling system
CN110837715A (en) Complex curved surface machining error compensation method based on reverse engineering technology

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
RJ01 Rejection of invention patent application after publication

Application publication date: 20150401

RJ01 Rejection of invention patent application after publication