CN104109747B - Edge strip part method for controlling heat treatment deformation and control fixture under aircraft - Google Patents
Edge strip part method for controlling heat treatment deformation and control fixture under aircraft Download PDFInfo
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- CN104109747B CN104109747B CN201410298624.6A CN201410298624A CN104109747B CN 104109747 B CN104109747 B CN 104109747B CN 201410298624 A CN201410298624 A CN 201410298624A CN 104109747 B CN104109747 B CN 104109747B
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Abstract
Edge strip part method for controlling heat treatment deformation and control fixture under a kind of aircraft, the theoretical profile of known part, control fixture and contain chuck body, preset pieces, muscle strongback and pressing plate, top board, preset pieces has the upper surface matched with part wing plate profile, muscle strongback has the sidewall coincide with stud profile, pressing plate has the presser feet matched with wing plate curvature, is separated by part after deformation control clamp being heat-treated together with part with deformation control clamp again.
Description
Technical field
The present invention relates to the heat treatment technics in airplane parts manufacture, specifically edge strip part method for controlling heat treatment deformation under a kind of aircraft.
Background technology
In aircraft manufacturing, have a lot of long edge strip machines to add part, the woollen state of these parts is mostly Ti-6Al-4V forging, structure is thin, is mostly on a large curved surface and has a stud, need carry out three digital control processings, numerical control is rough milled, half finish-milling, the theoretical outer mold surface of finish-milling and stud face.All stress relief annealing will be carried out after each digital control processing.Along with the development of aircraft technology, in some large aircrafts, these long edge strip parts are longer, and the longest has 3 meters, complex-shaped, and curvature is large and wall is thin, and such stud place is more yielding.
Under titanium alloy edge strip machine add part mechanical workout produce in can produce great internal stress, these internal stresss can cause afterwards part gross distortion or part installation be on active service in cause stress corrosion fracture.Part produces distortion, and cause correction work amount large, difficulty is large, and man-hour is long; Sometimes greatly, can cause the overproof or cracking of part and scrap, this not only causes tremendous economic lose and affect production schedule in distortion.Therefore, add in process at machine and need to carry out the internal stress that part exists by stress relief annealing repeatedly and eliminate.
Stress relief annealing is by workpiece heat to proper temperature, the processing method of Slow cooling gradually after held for some time.The machine that there is internal stress adds part internal stresses release in stress relief annealing heat treatment process and can produce distortion.Thermal treatment be one from the process being heated to cooling shedder sum tissue change, produce thermal stresses and structural stress inevitable, the distortion that therefore part produces also is inevitable, and part is larger, shape is more complicated, its distortion is also more large more serious, and it is very difficult that larger distortion makes mechanical workout correct, and even causes part rejection.
Recent years, along with the development of aircraft technology, heat treatment deformation frock is arisen at the historic moment.It is different from general jig frock that heat treatment deformation controls frock, and it does not have powerful cutting force, but in heat treatment process, frock also can deform.Simple for structural shape, volume is little, and precision face requires few part, and heat treatment deformation can control very well.But for complex-shaped irregular, bulky long edge strip part, when particularly will control the distortion in multiple precision face, tangible experience lacks very much.
Summary of the invention
The object of this invention is to provide a kind of for edge strip part method for controlling heat treatment deformation under aircraft and control fixture.
Edge strip part method for controlling heat treatment deformation under a kind of aircraft, described part is made up of thin wall shape curved surface wing plate and the stud being positioned at wing plate center, the theoretical profile of known part, it is characterized in that comprising a deformation control clamp, this fixture contains chuck body, preset pieces, muscle strongback and pressing plate, top board, preset pieces is fixed in chuck body, preset pieces has the upper surface matched with part wing plate profile, muscle strongback has the sidewall coincide with stud profile, pressing plate has the presser feet matched with wing plate curvature, before thermal treatment, the wing plate of part is placed in the upper surface of preset pieces, the sidewall of muscle strongback is fitted on stud, the two ends of muscle strongback are fixed in chuck body by web member, muscle strongback and stud are fixed by clamping element, with the presser feet of pressing plate, the both sides of wing plate are pressed on preset pieces, pressing plate is fixed in chuck body by web member, the front end of top board can be pressed on muscle strongback, top board is fixed in chuck body by web member equally, again part is separated with deformation control clamp after deformation control clamp is heat-treated together with part.
The invention has the advantages that: the heat treatment deformation that the thin wall shape curved surface wing plate of lower edge strip 1) can be controlled by the pressing plate of fixture and preset pieces very well; 2) the stud heat treatment deformation of lower edge strip can be controlled very well by the muscle strongback of fixture; 3) clamp structure is reasonable, manufactures easy to use; 4) fixture manufactures according to the theoretical profile precision work of part, also has the school shape kinetic energy to part.
Below in conjunction with embodiment accompanying drawing, the application is described in further detail.
Accompanying drawing explanation
Fig. 1 is edge strip part signal under aircraft
Fig. 2 is that under aircraft, edge strip part heat treatment deformation controls clamp structure signal
Fig. 3, Fig. 4 are the local signals of edge strip part thermal treatment control distortion clamping state under aircraft
Number description: 1 part, 2 wing plates, 3 studs, 4 technical lug, 5 web member 6 chuck body, 7 preset piecess, 8 pressing plates, 9 muscle strongbacks, 10 clamping elements, 11 top boards
Embodiment
See accompanying drawing, under aircraft, edge strip part 1 is made up of thin wall shape curved surface wing plate 2 and the stud 3 being positioned at wing plate center, this part is about three meters, wall thickness and muscle thick in four mm, and product is totally six faces, five faces are all precision faces, namely must the face of controlling distortion after thermal treatment, all leave the technical lug 4 of clamping at the two ends of part.The theoretical profile of known part.Deformation control clamp contains chuck body 6, preset pieces 7, muscle strongback 9 and pressing plate 8, top board 11, preset pieces 7 is fixed in chuck body 1, preset pieces 7 has the upper surface matched with part wing plate 2 lower surface profile, muscle strongback 9 has the sidewall coincide with part stud 3 profile, pressing plate 8 has the presser feet matched with wing plate curvature, before thermal treatment by part 1 clamping on fixture, the technical lug 4 at part two ends is fixed in chuck body 6 by web member and steady brace, the lower surface of wing plate 2 is placed in the upper surface of preset pieces 7, the sidewall of stud 3 with muscle strongback 9 is fitted, the two ends of muscle strongback 9 are fixed in chuck body 6 by web member 5, muscle strongback 9 is fixed by clamping element 10 with stud, preferably a clamping element 10 is established every 230mm in enforcement, better can control the distortion of stud 3, be pressed on preset pieces 7 with the presser feet of pressing plate 8 by the both sides of wing plate 2, pressing plate 8 is fixed in chuck body 1 by web member 5, preferably establishes one to compress point every 300mm in enforcement, so that better controlling distortion, the front end of top board 11 can be pressed on muscle strongback 9, auxiliary positioning effect is play to muscle strongback, top board 11 is fixed in chuck body by web member 5 equally, part is separated the part deformation that can effectively control in heat treatment process with deformation control clamp again after deformation control clamp being heat-treated together with part.
Claims (2)
1. edge strip part method for controlling heat treatment deformation under an aircraft, described part is made up of thin wall shape curved surface wing plate and the stud being positioned at wing plate center, the theoretical profile of known part, it is characterized in that comprising a deformation control clamp, this fixture contains chuck body, preset pieces, muscle strongback and pressing plate, top board, preset pieces is fixed in chuck body, preset pieces has the upper surface matched with part wing plate profile, muscle strongback has the sidewall coincide with stud profile, pressing plate has the presser feet matched with wing plate curvature, before thermal treatment, the wing plate of part is placed in the upper surface of preset pieces, the sidewall of muscle strongback is fitted on stud, the two ends of muscle strongback are fixed in chuck body by web member, muscle strongback and stud are fixed by clamping element, with the presser feet of pressing plate, the both sides of wing plate are pressed on preset pieces, pressing plate is fixed in chuck body by web member, the front end of top board is pressed on muscle strongback, top board is fixed in chuck body by web member equally, again part is separated with deformation control clamp after deformation control clamp is heat-treated together with part.
2. under an aircraft, edge strip part heat treatment deformation controls fixture, this fixture contains chuck body, preset pieces, muscle strongback and pressing plate, preset pieces is fixed in chuck body, preset pieces has the upper surface matched with part wing plate profile, muscle strongback has the sidewall coincide with stud profile, pressing plate has the presser feet matched with wing plate curvature, the two ends of muscle strongback are fixed in chuck body by web member, pressing plate is fixed in chuck body by web member, the front end of top board is pressed on muscle strongback, top board is fixed in chuck body by web member equally.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410298624.6A CN104109747B (en) | 2014-06-27 | 2014-06-27 | Edge strip part method for controlling heat treatment deformation and control fixture under aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410298624.6A CN104109747B (en) | 2014-06-27 | 2014-06-27 | Edge strip part method for controlling heat treatment deformation and control fixture under aircraft |
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| CN104109747A CN104109747A (en) | 2014-10-22 |
| CN104109747B true CN104109747B (en) | 2016-03-30 |
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| CN201410298624.6A Active CN104109747B (en) | 2014-06-27 | 2014-06-27 | Edge strip part method for controlling heat treatment deformation and control fixture under aircraft |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105039651B (en) * | 2015-09-14 | 2017-04-26 | 沈阳飞机工业（集团）有限公司 | Heat treatment clamp and method for large machining part |
| CN107538127B (en) * | 2016-06-23 | 2019-08-02 | 陕西飞机工业（集团）有限公司 | A method of it is quickly positioned about benchmark |
| CN114921627B (en) * | 2022-06-01 | 2023-10-31 | 沈阳飞机工业（集团）有限公司 | Aircraft support arm part shot blasting reverse deformation device and deformation control method using same |
| CN114959228A (en) * | 2022-06-01 | 2022-08-30 | 沈阳飞机工业（集团）有限公司 | Anti-deformation method for V-shaped belt plate part through heat treatment |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102168276A (en) * | 2011-04-06 | 2011-08-31 | 上海电机学院 | Heat treatment technology for automobile piston ring |
| CN204039444U (en) * | 2014-06-27 | 2014-12-24 | 中航飞机股份有限公司西安飞机分公司 | Under aircraft, edge strip part heat treatment deformation controls fixture |
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2014
- 2014-06-27 CN CN201410298624.6A patent/CN104109747B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102168276A (en) * | 2011-04-06 | 2011-08-31 | 上海电机学院 | Heat treatment technology for automobile piston ring |
| CN204039444U (en) * | 2014-06-27 | 2014-12-24 | 中航飞机股份有限公司西安飞机分公司 | Under aircraft, edge strip part heat treatment deformation controls fixture |
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| CN104109747A (en) | 2014-10-22 |
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Address after: No. 710089 in Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC Xi'an Aircraft Industry Group Co.,Ltd. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: AVIC AIRCRAFT Corp. |
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Effective date of registration: 20210617 Address after: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC AIRCRAFT Corp. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: XI'AN AIRCRAFT BRANCH OF XI'AN AIRCRAFT INTERNATIONAL Corp. |