CN104109749B - A kind of aircraft slide rail class part method for controlling heat treatment deformation and control fixture - Google Patents
A kind of aircraft slide rail class part method for controlling heat treatment deformation and control fixture Download PDFInfo
- Publication number
- CN104109749B CN104109749B CN201410299395.XA CN201410299395A CN104109749B CN 104109749 B CN104109749 B CN 104109749B CN 201410299395 A CN201410299395 A CN 201410299395A CN 104109749 B CN104109749 B CN 104109749B
- Authority
- CN
- China
- Prior art keywords
- chuck body
- locating core
- locating
- stud
- preset pieces
- 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.)
- Active
Links
Landscapes
- Forging (AREA)
Abstract
The invention provides a kind of method for controlling heat treatment deformation that can control the multiple precision face of part well, particularly for complex-shaped irregular, curved transition is large, large and the slide rail class part that wall is thin stud is contour of volume, comprise a deformation control clamp, the upper surface of the locating platform of this fixture has the theoretical profile identical with part plane wing plate lower surface, the conformal space of part stud is formed between preset pieces and locating core, the connecting hole on column is coordinated to compress soon by wedge shape, again part is separated with deformation control clamp after deformation control clamp is heat-treated together with part.
Description
Technical field
The invention belongs to aircraft manufacturing technical field, relate to part heat treatment deformation control techniques, the slide rail class part method for controlling heat treatment deformation that specifically a kind of aircraft stud is contour.
Background technology
The slide rail class part that aircraft stud is contour, structure is thin, mostly is the deep groove structure of the vertical stud of large planar band, highly equal between stud.Length is long, belongs to thin-wall part.Need repeatedly digital control processing be carried out, rough mill, half finish-milling, the multiple working procedures such as finish-milling.
In the mechanical processing process of part, great internal stress can be produced, if these internal stresss can not get effective release, part can be made to produce gross distortion, or leave hidden danger in part military service process, cause stress concentration and the dire consequences of product fracture occurs.
Titanium alloy material intensity is high, elasticity large, and part, once distortion, is difficult to correct, and its workload is very large, and the cycle is very long; If distortion is serious, also part rejection can be caused.This schedule requirement that huge economic waste but also impact not only can be caused to produce.Therefore, after part digital control processing each time, all stress relief annealing will be carried out.
Stress relief annealing is by heat parts to proper temperature, is cooled to a kind of processing method of room temperature after held for some time again.This be one from being heated to cooling, the process that volume of part and micro-metallographic structure change, the generation of thermal stresses and structural stress is inevitable, therefore part produces distortion in the process is also inevitable, and part is larger, thiner, the distortion of generation also more greatly, more serious, more serious distortion will make correction work more difficult, even causes part rejection.
Along with present generation aircraft is to the raising of manufacturing technology accuracy requirement, adopting the special tooling of controlling distortion to limit and correct the distortion of part in heat treatment process as constraint becomes gesture and become.So heat treatment deformation controls special tooling and arises at the historic moment.This type of frock is different from common machining tool, and work under the cold cycling state that repeatedly repeatedly then cool in heat, there will be and expand with heat and contract with cold, self also will be faced with the problem of cold and hot distortion.Therefore, heat treatment deformation controls special tooling will in conjunction with the constructional feature of part, and how when ensureing that frock self structure is stable, also will play the effect controlling product parts distortion, this is the current difficult problem faced.
Summary of the invention
The object of the present invention is to provide a kind of method for controlling heat treatment deformation that can control the multiple precision face of part well, particularly for complex-shaped irregular, curved transition is large, volume is large and the slide rail class part that the stud that wall is thin is contour.
A kind of Titanium Alloy Aircraft slide rail class part method for controlling heat treatment deformation, described part is made up of two studs that thin wall shape plane wing plate is equal with the height running through wing plate, the theoretical profile of known part, it is characterized in that: 1) comprise a deformation control clamp, this fixture contains chuck body, be fixed on the locating platform in chuck body, locating core, preset pieces, multiple press strip, be fixed on column in chuck body and wedge and web member composition, the upper surface of described locating platform has the theoretical profile identical with part plane wing plate lower surface, described locating core is a rectangular lumphy structure, and the spatial match between part two studs, described preset pieces is the trench structure of a strip, can be buckled on locating core, the conformal space of part stud is formed between the cell wall of both sides and locating core, described press strip is fixed in chuck body by wedge and column, 2) by part storage on the locating platform of described chuck body, the two ends of part are located by web member, locating core is placed between part stud, preset pieces snaps onto the outside of locating core and stud, press strip is crimped on the upper surface of preset pieces, coordinates the connecting hole on column to compress press strip soon by wedge shape, 3) again part is separated with deformation control clamp after deformation control clamp being heat-treated together with part.
The invention has the advantages that: 1) the present invention adopts the preset pieces of a set of frock and press strip to control the heat treatment deformation in multiple precision faces of the contour slide rail class part of titanium alloy stud, cost-saving, raises the efficiency.2) clamp structure is reasonable, manufactures easy to use; 3) fixture manufactures according to the theoretical profile precision work of part, also has the school shape function to part.
Below in conjunction with enforcement illustration, the application is described in further detail:
Accompanying drawing explanation
Fig. 1 is the signal of Titanium Alloy Aircraft slide rail class design of part
Fig. 2 is that Titanium Alloy Aircraft slide rail class part heat treatment deformation controls schematic diagram;
Fig. 3 is the left view of Fig. 2;
Fig. 4 is the section structure schematic diagram of Fig. 2;
Fig. 5 is for controlling clamp body and location platform arrangement schematic diagram
Fig. 6 is the combination schematic diagram of locating core and preset pieces
Number description: 1 part, 2 studs, 3 wing plates, 4 locating platforms, 5 locating cores, 6 preset piecess, 7 press strips, 8 columns, 9 wedges, 10 chuck body, 11 ventilation holes
Embodiment
See accompanying drawing, part in embodiment is the contour slide rail class part of the middle stud of certain model aircraft, the material of this part is Ti-6Al-4V forging, as shown in Figure 1, part 1 is made up of two studs 2 that thin wall shape plane wing plate 3 is equal with the height running through wing plate, the theoretical profile of known part, because part is about 3 meters, wall thickness and stud thickness are less than 4mm, part plane wing plate 3 upper, the two sides of lower surface and stud 2 are all precision faces, the i.e. face of necessary controlling distortion, stud is perpendicular to plane wing plate, stud root is focal point of stress, during stress relief, can moderate finite deformation be there is in stud.
In order to control the distortion of this part in heat treatment process, the invention discloses control method as shown in Figure 2, first a deformation control clamp is had, this fixture contains chuck body 10, be fixed on the locating platform 4 in chuck body, locating core 5, preset pieces 6, multiple press strip 7, be fixed on column 8 in chuck body 10 and wedge 9 and web member composition, the upper surface of described locating platform 4 has the theoretical profile identical with the lower surface of part plane wing plate 3, described locating core 5 is rectangular lumphy structures, and the spatial match between part two studs 2, described preset pieces 6 is trench structures of a strip, can on snapping locating core, fixed by web member bottom the grooved of locating core and preset pieces, the grooved space of preset pieces is wider than the width of locating core, make the conformal space forming part two studs between the cell wall of preset pieces both sides and locating core respectively, both sides cell wall also offers multiple ventilation hole 11, described press strip 7 is fixed in chuck body by wedge 9 and column 8, when part needs thermal treatment, part 1 is seated on the locating platform 4 of described chuck body, the two ends of part are located by web member, locating core 5 is placed between part stud, preset pieces 6 snaps onto the outside of locating core and stud, press strip 7 is crimped on the upper surface of preset pieces 6, coordinates the connecting hole on column 8 to compress press strip by wedge shape fast 9, again part is separated with deformation control clamp after finally deformation control clamp being heat-treated together with part.
Concrete Deformation control feature of the present invention is as follows:
(1) first, chuck body 10 adopts transverse and longitudinal stainless steel plate material welded construction, and frock self will have higher structural stability, not yielding.The rigidity of frock should be ensured, also need the weight alleviating frock.
(2) thermal expansivity difference is added due to differing materials, the material Ti-6Al-4V identical with product is preferably adopted with the locating platform 4 of part joint place, locating core 5, preset pieces 6, the 1Cr18Ni9Ti that molecular structure is close with it is all selected at other positions, under the prerequisite realizing conformal function, frock cost can be reduced like this.
(3) the present invention not only considers to prevent part deformation, more considers conformal, namely allows the tolerance zone internal strain that product is allowing, by locating core 5 and the preventing deformation vallecular cavity of preset pieces 6 component part stud and the conformal space of stud.
(4) design of locating platform 4, locating core 5 and preset pieces 6 can enable frock effectively locate part, to ensure the requirement of the structural shape size conforms product digital-to-analogue of part.
(5) consider to need heating and heat radiation in heat treatment process, make part be in a good heat treatment environment, the stud location conformal vallecular cavity formed at locating core 5 and preset pieces 6 all offers ventilation hole 11 at four direction.
(6) according to part length, compression point is evenly set.After preventing metallic substance temperature distortion, screw thread cannot turn, and hold-down mechanism can kill on part, can not adopt screw thread compacted form, and therefore the present invention adopts voussoir compacted form.Because locating core 5 and the gravity of preset pieces 6 own have played certain pressuring action to part, therefore, the strength of knocking voussoir is motionless to be fixed by press strip, can not apply excessive strength, otherwise be unfavorable for the release of compression place part stress.
Claims (2)
1. a Titanium Alloy Aircraft slide rail class part method for controlling heat treatment deformation, described part is made up of two studs that thin wall shape plane wing plate is equal with the height running through wing plate, the theoretical profile of known part, it is characterized in that: 1) comprise a deformation control clamp, this fixture contains chuck body, be fixed on the locating platform in chuck body, locating core, preset pieces, multiple press strip, be fixed on column in chuck body and wedge and web member, the upper surface of described locating platform has the theoretical profile identical with part plane wing plate lower surface, described locating core is a rectangular lumphy structure, and the spatial match between part two studs, described preset pieces is the trench structure of a strip, can be buckled on locating core, the conformal space of part stud is formed between the cell wall of both sides and locating core, described press strip is fixed in chuck body by wedge and column, 2) by part storage on the locating platform of described chuck body, the two ends of part are located by web member, locating core is placed between part stud, preset pieces snaps onto the outside of locating core and stud, press strip is crimped on the upper surface of preset pieces, coordinates the connecting hole on column to compress press strip with wedge, 3) again part is separated with deformation control clamp after deformation control clamp being heat-treated together with part.
2. a Titanium Alloy Aircraft slide rail class part heat treatment deformation controls fixture, described part is made up of two studs that thin wall shape plane wing plate is equal with the height running through wing plate, the theoretical profile of known part, it is characterized in that this fixture contains chuck body, be fixed on the locating platform in chuck body, locating core, preset pieces, multiple press strip, be fixed on column in chuck body and wedge and web member composition, the upper surface of described locating platform has the theoretical profile identical with part plane wing plate lower surface, described locating core is a rectangular lumphy structure, and the spatial match between part two studs, described preset pieces is the trench structure of a strip, can be buckled on locating core, the conformal space of part stud is formed between the cell wall of both sides and locating core, described press strip is fixed in chuck body by wedge and column.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410299395.XA CN104109749B (en) | 2014-06-27 | 2014-06-27 | A kind of aircraft slide rail class part method for controlling heat treatment deformation and control fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410299395.XA CN104109749B (en) | 2014-06-27 | 2014-06-27 | A kind of aircraft slide rail class part method for controlling heat treatment deformation and control fixture |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104109749A CN104109749A (en) | 2014-10-22 |
| CN104109749B true CN104109749B (en) | 2016-02-24 |
Family
ID=51706735
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410299395.XA Active CN104109749B (en) | 2014-06-27 | 2014-06-27 | A kind of aircraft slide rail class part method for controlling heat treatment deformation and control fixture |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104109749B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104404420B (en) * | 2014-10-29 | 2018-07-13 | 北京航星机器制造有限公司 | A kind of titanium alloy welding component vacuum heat deformation control method for opening big window |
| 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 |
| CN105274285B (en) * | 2015-12-07 | 2018-01-05 | 沈阳飞机工业（集团）有限公司 | Boot last soldering part heat treatment deformation fixture and application method |
| CN105441659A (en) * | 2015-12-28 | 2016-03-30 | 无锡透平叶片有限公司 | Anti-deformation thermal treatment tool for high-temperature alloy precisely-forged structural component |
| CN106092724B (en) * | 2016-08-04 | 2019-01-22 | 清华大学 | Concrete temperature stress testing machine with temperature deformation self-compensating function |
| CN106269996B (en) * | 2016-08-23 | 2018-05-15 | 中国航空工业集团公司北京航空制造工程研究所 | Suitable for corrector and method with muscle siding |
| CN106381373A (en) * | 2016-11-25 | 2017-02-08 | 沈阳黎明航空发动机(集团)有限责任公司 | Correction method and device for plate type multilayered structure titanium alloy parts |
| CN112210653A (en) * | 2020-09-28 | 2021-01-12 | 重庆长安工业(集团)有限责任公司 | Heat treatment quenching method for high-precision space curve track type parts |
-
2014
- 2014-06-27 CN CN201410299395.XA patent/CN104109749B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN104109749A (en) | 2014-10-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104109749B (en) | A kind of aircraft slide rail class part method for controlling heat treatment deformation and control fixture | |
| CN104109748B (en) | Edge bar part method for controlling heat treatment deformation on a kind of aircraft | |
| CN104004982B (en) | A kind of titanium alloy component stablizes heat treatment process method | |
| CN104213059A (en) | Titanium alloy double layer curved surface wing plate part heat treatment deformation control method | |
| CN103668025B (en) | Titanium alloy high-temperature state eliminates stress correcting deformed heat treatment tooling and technique | |
| CN204396531U (en) | A kind of mould for school shape inside and outside titanium alloy member | |
| CN105057990A (en) | Forming method of lightweight missile wing with integral diffusion bonding structure of envelope and framework | |
| CN104218121A (en) | Weld strip welding method capable of lowering cell fragment rate | |
| CN104109747B (en) | Edge strip part method for controlling heat treatment deformation and control fixture under aircraft | |
| CN203751615U (en) | Assembly-welding and anti-deforming assembly for top flange of nuclear power station structure module | |
| CN104120235B (en) | A kind of stud height unequal slide rail class part method for controlling heat treatment deformation | |
| CN204396532U (en) | The mould positioning mechanism of a kind of school shape titanium alloy member | |
| CN103886919A (en) | Method for improving fusion reactor inner wall plasma irradiation prevention performance through lamination | |
| BR112013023355A2 (en) | rolling mill method and rolling mill for rolling a piece of metal to be rolled produced in an ingot casting process, control and / or regulation device for a rolling mill, machine readable program code for a control device and / or regulation and storage medium | |
| CN108256133A (en) | The Dynamic Rolling Process analogy method of aluminum alloy compounded ingot and its application | |
| CN104498847B (en) | Thin-walled cavity structure aluminium alloy post method for controlling heat treatment deformation | |
| BRPI0822310A2 (en) | METHOD OF MANUFACTURE OF SPHERICAL BEARINGS RINGS BY LAMINATING STEEL BEARING MODELS USING A LAMINATING MACHINE | |
| CN102672091A (en) | Efficient isothermal forging mould base | |
| CN104778305A (en) | Part bend springback compensation method | |
| CN206356409U (en) | A kind of school shape fixture of square frame-shaped titanium alloy member | |
| US10124400B2 (en) | Casting die | |
| CN202072731U (en) | Fixture for heat treatment of large-sized wallboards | |
| CN206509361U (en) | It is a kind of continuously to adjust the fixture in school shape gap | |
| CN104573206A (en) | Profile steel section thermal shape and size design method based on finite element thermal coupling | |
| RU2013157406A (en) | METHOD FOR PRODUCING METAL PANELS |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
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. |
|
| CP03 | Change of name, title or address | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210610 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. |
|
| TR01 | Transfer of patent right |