CN104476109A - Skin structure accurate positioning machining method - Google Patents
Skin structure accurate positioning machining method Download PDFInfo
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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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
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.
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| CN201410498066.8A CN104476109A (en) | 2014-09-25 | 2014-09-25 | Skin structure accurate positioning machining method |
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| CN201410498066.8A CN104476109A (en) | 2014-09-25 | 2014-09-25 | Skin structure accurate positioning machining method |
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Cited By (14)
| 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 |
| CN107138762A (en) * | 2017-06-19 | 2017-09-08 | 湖北三江航天红阳机电有限公司 | A kind of large-scale global shell opens porous processing method and system |
| 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 |
| CN115179065A (en) * | 2022-06-20 | 2022-10-14 | 成都飞机工业（集团）有限责任公司 | Air inlet channel type composite material tooling template machining support structure and allowance adjusting method |
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Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104858865A (en) * | 2015-05-13 | 2015-08-26 | 南昌航空大学 | Aircraft body skin end face allowance cutting mechanical arm |
| 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 |
| CN107138762A (en) * | 2017-06-19 | 2017-09-08 | 湖北三江航天红阳机电有限公司 | A kind of large-scale global shell opens porous processing method and system |
| CN107138762B (en) * | 2017-06-19 | 2023-08-15 | 湖北三江航天红阳机电有限公司 | Processing method and system for opening multiple holes in large ball shell |
| 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 |
| 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 |
| 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 |
| 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 |
| CN114211200B (en) * | 2021-11-04 | 2023-04-14 | 宝武集团马钢轨交材料科技有限公司 | High-precision wheel spoke hole machining method |
| CN115179065A (en) * | 2022-06-20 | 2022-10-14 | 成都飞机工业（集团）有限责任公司 | Air inlet channel type composite material tooling template machining support structure and allowance adjusting method |
| CN115179065B (en) * | 2022-06-20 | 2023-12-08 | 成都飞机工业（集团）有限责任公司 | Air inlet channel composite tool template processing supporting structure and allowance adjusting method |
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