CN104109749A - Deformation control method and control fixture for heat treatment of airplane sliding rail component - Google Patents
Deformation control method and control fixture for heat treatment of airplane sliding rail component Download PDFInfo
- Publication number
- CN104109749A CN104109749A CN201410299395.XA CN201410299395A CN104109749A CN 104109749 A CN104109749 A CN 104109749A CN 201410299395 A CN201410299395 A CN 201410299395A CN 104109749 A CN104109749 A CN 104109749A
- Authority
- CN
- China
- Prior art keywords
- chuck body
- locating core
- locating
- fixture
- wing plate
- 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.)
- Granted
Links
Abstract
The invention relates to a deformation control method for heat treatment of an airplane sliding rail component, particularly of high sliding rail components such as vertical ribs with complex and irregular shape, large curvature change, large volume and thin wall. The invention also relates to a deformation control fixture. An upper surface of a positioning platform of the fixture has a theoretical shape identical to a lower surface of a component planar wing plate. A shape-keeping space of the vertical ribs of the component is formed between a positioning block and a positioning core. A wedge-shaped block is used to press a press bar tightly in cooperation of a connecting hole on a vertical column. The deformation control fixture and the component are subjected to the heat treatment together and then separated from each other.
Description
Technical field
The invention belongs to aircraft manufacturing technical field, relate to part heat treatment deformation control techniques, specifically the contour slide rail class part method for controlling heat treatment deformation of a kind of aircraft stud.
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 carry out repeatedly digital control processing, rough mill, half finish-milling, the multiple working procedures such as finish-milling.
In the mechanical processing process of part, can produce great internal stress, if these internal stresss can not get effective release, can make part 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 is large, once part distortion is difficult to proofread and correct, its workload is very large, and the cycle is very long; If distortion is serious, also can cause part to scrap.The schedule requirement that this not only can cause huge economic waste but also impact to produce.Therefore, after part digital control processing each time, all to carry out stress relief annealing.
Stress relief annealing is that part is heated to proper temperature, is cooled to a kind of processing method of room temperature after insulation certain hour again.This be one cooling from being heated to, the process that volume of part and micro-metallographic structure change, the generation of thermal stresses and structural stress is inevitable, therefore part in this process, produce distortion be also inevitable, and part is larger, thiner, the distortion of generation also just more greatly, more serious, more serious distortion will make correction work more difficult, even causes part to scrap.
Along with the raising of present generation aircraft to manufacturing technology accuracy requirement, adopt control distortion special tooling as constraint limit and correct the distortion of part in heat treatment process become gesture become.So heat treatment deformation control special tooling arises at the historic moment.This type of frock is different from common machining tool, be repeatedly repeatedly then under cooling cold cycling state, works in heat, there will be and expands with heat and contract with cold, and self also will be faced with the problem of cold and hot distortion.Therefore, heat treatment deformation control special tooling will be in conjunction with the constructional feature of part, how, in the situation that ensureing that frock self structure is stable, also will play the effect of controlling product parts distortion, and this is the current difficult problem facing.
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 well the multiple precision faces of part, particularly for the contour slide rail class part of complex-shaped stud irregular, that curved transition is large, volume is large and wall is thin.
A kind of Titanium Alloy Aircraft slide rail class part method for controlling heat treatment deformation, described part is made up of thin wall shape plane wing plate and two studs that the height that runs through wing plate equates, the theoretical profile of known part, it is characterized in that: 1) comprise a Deformation control fixture, this fixture contains chuck body, be fixed on the locating platform in chuck body, locating core, preset pieces, multiple press strips, be fixed on column and wedge and web member composition in chuck body, 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 mate in the space between two studs of part, described preset pieces is the trench structure of a strip, can be buckled on locating core, between the cell wall of both sides and locating core, form the conformal space of part stud, described press strip is fixed in chuck body by wedge and column, 2) by part storage on the locating platform of described chuck body, locate by web member at the two ends of part, 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 soon connecting hole on column to compress press strip by wedge shape, 3) after being heat-treated together with part, Deformation control fixture again part is separated with Deformation control fixture.
The invention has the advantages that: 1) the present invention adopts the heat treatment deformation of multiple precision faces of the preset pieces of a set of frock and the contour slide rail class part of press strip control titanium alloy stud, cost-saving, raises the efficiency.2) clamp structure is reasonable, manufactures easy to use; 3) fixture is manufactured according to the theoretical profile precision work of part, also has the school shape function to part.
Below in conjunction with implementing illustration, the application is described in further detail:
Brief description of the drawings
Fig. 1 is the signal of Titanium Alloy Aircraft slide rail class design of part
Fig. 2 is Titanium Alloy Aircraft slide rail class part heat treatment deformation control 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 locating platform structural representation
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
Referring to 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 thin wall shape plane wing plate 3 and two studs 2 that the height that runs through wing plate equates, 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, must control the face of distortion, stud is perpendicular to plane wing plate, stud root is focal point of stress, when stress relief, can there is moderate finite deformation 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 there is a Deformation control fixture, this fixture contains chuck body 10, be fixed on the locating platform 4 in chuck body, locating core 5, preset pieces 6, multiple press strips 7, be fixed on column 8 and wedge 9 and web member composition in chuck body 10, 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 mate in the space between two studs 2 of part, described preset pieces 6 is trench structures of a strip, on can snapping locating core, the grooved bottom of locating core and preset pieces is fixed by web member, the grooved space of preset pieces is wider than the width of locating core, make to form respectively between the cell wall of preset pieces both sides and locating core the conformal space of two studs of part, on the cell wall of both sides, also offer multiple ventilation holes 11, described press strip 7 is fixed in chuck body by wedge 9 and column 8, in the time that part needs thermal treatment, part 1 is seated on the locating platform 4 of described chuck body, locate by web member at the two ends of part, 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, with the connecting hole compression press strip on the fast 9 cooperation columns 8 of wedge shape, after finally Deformation control fixture being heat-treated together with part, again part is separated with Deformation control fixture.
Concrete Deformation control feature of the present invention is as follows:
(1) first, chuck body 10 adopts transverse and longitudinal stainless steel plate welded construction, and frock self will have higher structural stability, not yielding.Should ensure the rigidity of frock, also need to alleviate the weight of frock.
(2) add thermal expansivity difference due to differing materials, preferably adopt the material Ti-6Al-4V identical with product with locating platform 4, locating core 5, the preset pieces 6 of part joint place, molecular structure close 1Cr18Ni9Ti with it is all selected at other positions, can realize under the prerequisite of conformal function like this, reduce frock cost.
(3) the present invention not only considers to prevent part deformation, more considers conformal, allows product in the tolerance zone internal strain allowing, and is the conformal space of stud by the preventing deformation vallecular cavity of locating core 5 and preset pieces 6 component part studs.
(4) design of locating platform 4, locating core 5 and preset pieces 6 can make frock effectively locate part, to ensure the requirement of structural shape size conforms product digital-to-analogue of part.
(5) consider to need heating and heat radiation in heat treatment process, make part in a good heat treatment environment, the stud location conformal vallecular cavity forming at locating core 5 and preset pieces 6 is all offered ventilation hole 11 at four direction.
(6), according to part length, compression point is evenly set.For preventing that, after metallic substance temperature distortion, screw thread cannot turn, 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 so that press strip is fixed, and can not apply excessive strength, otherwise is 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 thin wall shape plane wing plate and two studs that the height that runs through wing plate equates, the theoretical profile of known part, it is characterized in that: 1) comprise a Deformation control fixture, this fixture contains chuck body, be fixed on the locating platform in chuck body, locating core, preset pieces, multiple press strips, be fixed on column and wedge and web member composition in chuck body, 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 mate in the space between two studs of part, described preset pieces is the trench structure of a strip, can be buckled on locating core, between the cell wall of both sides and locating core, form the conformal space of part stud, described press strip is fixed in chuck body by wedge and column, 2) by part storage on the locating platform of described chuck body, locate by web member at the two ends of part, 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 soon connecting hole on column to compress press strip by wedge shape, 3) after being heat-treated together with part, Deformation control fixture again part is separated with Deformation control fixture.
2. a Titanium Alloy Aircraft slide rail class part heat treatment deformation control fixture, described part is made up of thin wall shape plane wing plate and two studs that the height that runs through wing plate equates, 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 strips, be fixed on column and wedge and web member composition in chuck body, the upper surface of described locating platform has the theoretical profile identical with part plane wing plate lower surface, described described locating core is a rectangular lumphy structure, and mate in the space between two studs of part, described preset pieces is the trench structure of a strip, can be buckled on locating core, between the cell wall of both sides and locating core, form the conformal space of part stud, 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 true CN104109749A (en) | 2014-10-22 |
| CN104109749B 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) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104404420A (en) * | 2014-10-29 | 2015-03-11 | 北京航星机器制造有限公司 | Vacuum heat treatment deformation control method of titanium alloy welding member with large window |
| CN105039651A (en) * | 2015-09-14 | 2015-11-11 | 沈阳飞机工业（集团）有限公司 | Heat treatment clamp and method for large machining part |
| CN105274285A (en) * | 2015-12-07 | 2016-01-27 | 沈阳飞机工业（集团）有限公司 | Heat treatment anti-deformation jig for boot-shape welded part and using method thereof |
| 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 |
| CN106092724A (en) * | 2016-08-04 | 2016-11-09 | 清华大学 | There is the concrete temperature stress testing machine of temperature deformation self-compensating function |
| CN106269996A (en) * | 2016-08-23 | 2017-01-04 | 中国航空工业集团公司北京航空制造工程研究所 | It is applicable to corrector and the method for band muscle wallboard |
| 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
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104404420A (en) * | 2014-10-29 | 2015-03-11 | 北京航星机器制造有限公司 | Vacuum heat treatment deformation control method of titanium alloy welding member with large window |
| CN105039651A (en) * | 2015-09-14 | 2015-11-11 | 沈阳飞机工业（集团）有限公司 | Heat treatment clamp and method for large machining part |
| 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 |
| CN105274285A (en) * | 2015-12-07 | 2016-01-27 | 沈阳飞机工业（集团）有限公司 | Heat treatment anti-deformation jig for boot-shape welded part and using method thereof |
| 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 |
| CN106092724A (en) * | 2016-08-04 | 2016-11-09 | 清华大学 | There is the concrete temperature stress testing machine of temperature deformation self-compensating function |
| CN106092724B (en) * | 2016-08-04 | 2019-01-22 | 清华大学 | Concrete temperature stress testing machine with temperature deformation self-compensating function |
| CN106269996A (en) * | 2016-08-23 | 2017-01-04 | 中国航空工业集团公司北京航空制造工程研究所 | It is applicable to corrector and the method for band muscle wallboard |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104109749B (en) | 2016-02-24 |
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 | |
| CN104177110B (en) | The preparation method of corrugated configuration ceramic matric composite flat board | |
| CN104213059A (en) | Titanium alloy double layer curved surface wing plate part heat treatment deformation control method | |
| CN104004982B (en) | A kind of titanium alloy component stablizes heat treatment process method | |
| CN204396531U (en) | A kind of mould for school shape inside and outside titanium alloy member | |
| CN103668025B (en) | Titanium alloy high-temperature state eliminates stress correcting deformed heat treatment tooling and technique | |
| CN105057990A (en) | Forming method of lightweight missile wing with integral diffusion bonding structure of envelope and framework | |
| CN106002360A (en) | Thin-wall porous structure sheet material milling and clamping method and thin-wall porous structure sheet material clamping device | |
| CN203625438U (en) | Thermal treatment tempering correction fixture | |
| CN104109747B (en) | Edge strip part method for controlling heat treatment deformation and control fixture under aircraft | |
| CN104120235B (en) | A kind of stud height unequal slide rail class part method for controlling heat treatment deformation | |
| CN203751615U (en) | Assembly-welding and anti-deforming assembly for top flange of nuclear power station structure module | |
| CN204396532U (en) | The mould positioning mechanism of a kind of school shape titanium alloy member | |
| CN104498847B (en) | Thin-walled cavity structure aluminium alloy post method for controlling heat treatment deformation | |
| CN102806229B (en) | A kind of zerolling method preparing tungsten copper alloy foil | |
| BRPI0822310A2 (en) | METHOD OF MANUFACTURE OF SPHERICAL BEARINGS RINGS BY LAMINATING STEEL BEARING MODELS USING A LAMINATING MACHINE | |
| CN103397163A (en) | Flame strengthening method for H-beam | |
| CN104707926A (en) | Molding and forging method of large arched forging stock | |
| CN102672091A (en) | Efficient isothermal forging mould base | |
| CN104778305A (en) | Part bend springback compensation method | |
| CN102873095B (en) | Low-temperature rolling method for preparing molybdenum-copper alloy | |
| CN109822026A (en) | A kind of manufacturing method and mould therefor of abnormity blank | |
| CN202072731U (en) | Fixture for heat treatment of large-sized wallboards | |
| CN204396534U (en) | A kind of school shape mould for titanium alloy member |
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 |