CN107570628A - Crotch class aircraft skin product shaping frock and forming technology - Google Patents
Crotch class aircraft skin product shaping frock and forming technology Download PDFInfo
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- CN107570628A CN107570628A CN201710840243.XA CN201710840243A CN107570628A CN 107570628 A CN107570628 A CN 107570628A CN 201710840243 A CN201710840243 A CN 201710840243A CN 107570628 A CN107570628 A CN 107570628A
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- plate
- left socle
- right support
- roller bearing
- mould
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Abstract
The invention provides a kind of crotch class aircraft skin product shaping frock and forming technology, including left socle and right support, roller bearing is housed on left socle and right support, roller bearing both ends are fixed by left end cap and right end cap with left and right support, and horizontal key and axial bond are respectively equipped with the inner side of left socle and right support；Forming technology includes：Left and right support is fixedly connected by key and mould, blanking, pre-bending plate, plate is installed, clamps plate, adjusts the jaw angle of stretcher binding clip, plate is stretched using the left stretching cylinder and right stretching cylinder of stretcher and the step such as plate edge trimming.Advantage is：The globality of covering product can not only be ensured, reduce the dividing number of covering product, increase the bulk strength and rigidity of covering product；But also the technique of crotch class aircraft skin product can be simplified and reduce difficulty of processing, the advanced manufacture level of plate muscle class product in production efficiency and plastic working field is effectively improved, production cost is greatly lowered.
Description
Technical field
The invention belongs to sheet metal component Forming Technique field, is shaped more particularly to a kind of crotch class aircraft skin product
With frock and forming technology.
Background technology
Skin stretch forming is the typical sheet material forming method of Field of Aviation Manufacturing, and mainly for the production of forming, aircraft is pneumatic
The large-scale covering class product of profile, its technical process are：First sheet material is clamped by the clamp positioned at sheet material both sides, then passes through folder
The cladding extensional motion or pull-shaped mould of pincers jack motion vertically upward, sheet material is gradually fitted to pull-shaped die surface and occur
Stretcher strain is to obtain final shape.The characteristics of pull-shaped technique is to add tangential pulling force while sheet material is bent, and cuts open sheet material
Stress in face tends to uniformity and reduces moment of flexure caused by flexural deformation, so pull-shaped technique resilience is smaller, drip molding essence
Degree is higher, is widely used in the manufacture of the aircraft skin class product higher to forming quality requirement.
Skin stretch forming metal thin plate class shapes, and mainly applies pulling force and curved to stretching woollen by the jaw of stretcher
The motion of square, woollen and the binding face of stretch forming frock is set progressively to extend, and the final manufacturing process being bonded completely.Covering is drawn
Stretch much more complicated than other kinds of forming process of forming process, it be related to drawing, it is curved, turn round Combined Loading action and combinations thereof, and
Influenceed simultaneously by material property, material deformation tendency, drawing and forming mode, equipment operational factor etc..
When processing crotch class covering product, because material flow direction is the same side, with skin drawing machine jaw direction
Not in same direction, therefore it can not use and cover drawing process shaping, traditional forming technology beats manufacture using manual more, or use will make
Part is divided into two (or being divided into multiple), avoids the partial plastic forming at crotch, then again passes through two or more molded parts
Welding or the crotch class covering product that riveting is shape needed for drawing.Using foregoing forming mode make covering product with
The product of overall processing is compared, and its structural integrity is poor, influences product bulk strength and rigidity；Extra increase is needed to connect simultaneously
Frame is connect, increases the positioning difficulty of product, production efficiency is reduced, consumes substantial amounts of installation time and production cost, is reduced
The competitiveness of enterprise.
The content of the invention
The present invention provides a kind of achievable that crotch class product is quick for technical problem present in solution known technology
Shaping, the globality for ensureing product and the crotch class aircraft skin product shaping that product bulk strength and rigidity can be increased substantially
With frock and forming technology.
Technical scheme：
Crotch class aircraft skin product shaping frock, including symmetrically arranged left socle 1 and right support 2, the He of left socle 1
Right support 2 coordinates on roller bearing 4, and the one end of roller bearing 4 is fixed by left end cap 7 and left socle 1, and the other end of roller bearing 4 passes through right-hand member
Lid 8 is fixed with right support 2；The horizontal key 3 and axial bond of installation mold 11 are respectively provided with the inner side of left socle 1 and right support 2
6。
The position that left socle 1 and right support 2 contact with roller bearing 4 is embedded with compound guide bushing 10, compound guide bushing 10 and left socle 1
It is interference fit with right support 2；
The screw 9 disengaged for roller bearing 4 and left socle 1, right support 2 is equipped with the outside of the both ends of roller bearing 4；
Being provided with the outside of compound guide bushing 10 in left socle 1 by trip bolt prevents compound guide bushing 10 from left socle
The pressing plate skidded off in 1.
The forming technology of crotch class aircraft skin product shaping frock, step are as follows：
A, left socle 1, right support 2 are connected by horizontal key 3 and axial bond 6 with mould 11 first, pretension are carried out by screw 9,
Compound guide bushing 10 is fitted into the axis hole of left socle 1, right support 2, using interference fit, then penetrated roller bearing 4 with compound
In the left socle 1 of guide pin bushing 10 and the axis hole of right support 2；
B, blanking：Size according to the width of mould 11 sets the width dimensions of plate 12, the width of plate 12 of setting
The width ratio of size and the width dimensions of mould 11 is 96:100, the length of plate 12 is ensured the length more than the type face of mould 11, together
When to reserve jaw clamping length；
C, pre-bending plate：By plate 12 be pre-bent to the approximate shape of the profile of mould 11, then to the plate after pre-bending
Material 12 is heat-treated；
Plate 12 is installed d,：First roller bearing 4 is extracted out from left socle 1, stayed between mould 11 and left socle 1, right support 2
Go out to insert the gap of plate 12, now, the pre-bending side of plate 12 is put on mould 11, then roller bearing 4 is inserted into left socle 1 and right branch
In frame 2, left socle 1 and right support 2 are then fastenedly connected by left end cap 7, right end cap 8 and screw 9, with prevent roller bearing 4 into
Left and right play during shape；
E, plate 11 is clamped：Clamp the both ends of plate by the jaw of stretcher binding clip, adjustment mould 11 upper and lower or
Right position and angle, the angle be using the center of stretcher workbench as pivot, from the horizontal by certain angle,
To ensure jaw when stretching plate 12, plate 12 can be fitted in the mould surface portion on mould 11 completely；
G, plate is stretched by the left stretching cylinder and right stretching cylinder of stretcher, plate 12 is sticked on mould completely
Have on 11 type faces, while also to ensure that plate 12 leaves deflection；
H, after product stretch forming, in the nand-type face region of mould 11 with part positioning hole is made, in order to follow-up numerical control cutting
The positioning of plate in the process of side；
I, trimming is carried out to the product edge after stretch forming, after the completion of the above-mentioned drawing and forming of plate 12, roller bearing extracted out,
Product is removed, pulls down left socle 1, right support 2 and roller bearing 4, then mould 11 is fixed on numerically controlled machine, product is thick
The product after slightly cutting is positioned on mould 11 by the positioning hole in nand-type face region after cutting, then entered by five-axle number control machine tool
Row milling.
Beneficial effects of the present invention：Because the present invention is using roller bearing rotation and key connection mode, and changed using roller bearing
The shaping direction of crotch class product, it by the control of skin drawing machine tensile force, can be achieved that the product of crotch (negative angle) will be carried
Quick-forming.It so can not only ensure the globality of covering product, reduce the dividing number of covering product, increase covering product
Bulk strength and rigidity；But also the technique of crotch class aircraft skin product can be simplified and reduce difficulty of processing, effectively improve
The advanced manufacture level of metal plate parts, considerably reduces production cost in production efficiency and plastic working field.
Brief description of the drawings
Fig. 1 is the front view of frock of the present invention；
Fig. 2 is Fig. 1 left view；
Fig. 3 is Fig. 1 top view；
Fig. 4 is Fig. 3 A-A sectional views；
Fig. 5 is the frock and mould confined state schematic diagram of the present invention；
Fig. 6 is Fig. 5 left view；
Fig. 7 is the position relationship schematic diagram of plate, mould and roller bearing in forming technology of the present invention；
Fig. 8 is the pre-bending plate schematic diagram in forming technology of the present invention.
In figure：1 left socle；2 right supports；3 horizontal keys；4 roller bearings；5 pressing plates；6 axial bonds；7 left end caps；8 right end caps；9 screws；10
Compound guide bushing；11 moulds；12 plates.
Embodiment
In order to further understand the content, features and effects of the present invention, hereby enumerating following examples, and coordinate accompanying drawing
Describe in detail as follows：
Refer to Fig. 1-Fig. 4, crotch class aircraft skin product shaping frock, including symmetrically arranged left socle 1 and the right side
Support 2, the left socle and right support are provided with concentric axis hole, cooperation are moved on left socle and right support axis hole roller bearing 4 is housed,
Described roller bearing one end is fixed by left end cap 7 with left socle, and the roller bearing other end is fixed by right end cap 8 with right support, the left side
The horizontal key 3 and axial bond 6 of installation mold are respectively provided with support and the corresponding inner side of right support.
In the present embodiment, the position that the left socle and right support contact with roller bearing is embedded with compound guide bushing 10, described multiple
It is interference fit that guide pin bushing, which is closed, with left socle and right support, and is coordinated with roller bearing 4 for gap, and the roller bearing is in product forming process
It is freely rotatable.
In the present embodiment, the roller bearing is made using 45# forged steel, its intensity and wearability ratio ordinary steel high 30% with
On, roller surface ensures that roughness is not more than 0.8 using grinding, reduces between roller bearing and compound guide bushing, shaping plate
Frictional force, increase the gearing in favor of the flowing of shaping plate of roller bearing.Suitable roller bearing diameter is chosen by bending to calculate, is protected
In loading process is shaped, roller bearing will not occur bending and deformation card.
In the present embodiment, the screw 9 disengaged for roller bearing and left socle, right support is equipped with the outside of the roller bearing both ends.
In the present embodiment, being provided with the compound guide bushing outside in left socle by trip bolt prevents composite guide
Cover the pressing plate 5 skidded off from left socle.
Refer to Fig. 5-Fig. 8, using crotch class aircraft skin product shaping frock crotch class aircraft skin product into
Shape technique, comprises the following steps：
A, left socle 1, right support 2 are connected by horizontal key 3 and axial bond 6 with mould first, pretension is carried out by screw 9, will
Compound guide bushing 10 is fitted into the concentric axis hole of left socle, right support using interference fit, then penetrates roller bearing 4 with composite guide
In the left socle of set and the axis hole of right support.
B, blanking, the width dimensions of plate 12, the plate width of setting are set according to the size of the width of mould 11
The width ratio of size and die width size is 96:100, plate length is ensured the length more than die face, while will be
Jaw clamping length is reserved on plate.
C, pre-bending plate, by manually first by plate be pre-bent to the approximate shape of die shape, then to pre-bending
Plate afterwards is heat-treated.Different according to the thickness of plate, material, the heat treatment mode of blank is also different, this implementation
In example, such as covering product material is 2B06, and thickness 2.2mm alloy plate materials, its heat-treatment quenching temperature control is in 500-508
DEG C, the time of heat treatment is 34-40min, and water is then entered in 5-7s.
D, feed, first roller bearing is extracted out from left socle, insertion plate is reserved between mould 11 and left socle, right support
Gap, now, plate pre-bending side is inserted from gap, is placed on mould 11, then roller bearing is loaded into left socle and right branch
In frame, left socle and right support are then fastenedly connected by left end cap 7, right end cap 8 and screw 9, to prevent roller bearing from shaping
Left and right play in journey.
E, plate is clamped, the both ends of plate 12 are clamped by the jaw of stretcher binding clip, adjust the upper and lower or left of mould
Right position and angle, the angle be using the center of stretcher workbench as pivot, can horizontal direction it is angled, with
Just ensure that jaw when stretching plate, enables plate to be completely covered on the mould surface portion on mould.
F, jaw angle, the right position and swing angle of bracket of stretcher binding clip, the angle of pitch of the jaw are adjusted
Spend for 0-60 °, the swing angle of bracket is ± 15 °.
G, plate is stretched by the left stretching cylinder and right stretching cylinder of stretcher, plate is sticked on mould completely
On type face, while also to ensure that plate leaves certain deflection, according to different, the change of blank with material of the thickness of processing plate
Shape amount is also different.In the present embodiment, such as covering product material is 2B06, the total change of thickness 2.2mm alloy plate materials
Shape amount is controlled within 15%, and deflection, which crosses conference, causes covering product coarse-grain, influences the fatigue strength of covering product, deflection
It is too small, covering product resilience can be caused, mould state is not pasted in appearance.
H, after product stretch forming, in the nand-type face region of mould with part positioning hole is made, in order to follow-up numerical control trimming
The positioning of plate in process.
I, trimming is carried out to the product edge after stretch forming, after the completion of above-mentioned sheet metal stretching shaping, roller bearing is extracted out, taken
Lower product, left socle, right support and roller bearing are pulled down, then mould is fixed on numerically controlled machine, led to after product is slightly cut
Product after slightly cutting is positioned on mould by the positioning hole for crossing nand-type face region, then carries out milling by five-axle number control machine tool.
Under normal circumstances, milling processing includes the milling to product edge, product lightening grooves and product irregularly-shaped hole.
Natrual ageing, storage are carried out to the product after the completion of milling.
Embodiment described in accompanying drawing of the present invention is exemplary, is only used for explaining the present invention, and it is not intended that to this
The limitation of invention.
Claims (2)
- A kind of 1. crotch class aircraft skin product shaping frock, it is characterised in that described crotch class aircraft skin product into Shape frock includes symmetrically arranged left socle (1) and right support (2), and left socle (1) and right support (2), which coordinate, is mounted in roller bearing (4) on, roller bearing (4) one end is fixed by left end cap (7) and left socle (1), and roller bearing (4) other end passes through right end cap (8) and the right side Support (2) is fixed；The horizontal key (3) of installation mold (11) is respectively provided with the inner side of left socle (1) and right support (2) and is erected Key (6)；The position that left socle (1) and right support (2) contact with roller bearing (4) is embedded with compound guide bushing (10), compound guide bushing (10) with Left socle (1) and right support (2) are interference fit；The screw (9) disengaged for roller bearing (4) and left socle (1), right support (2) is equipped with the outside of roller bearing (4) both ends；Being provided with the outside of compound guide bushing (10) in left socle (1) by trip bolt prevents compound guide bushing (10) from left branch The pressing plate skidded off in frame (1).
- 2. a kind of forming technology of crotch class aircraft skin product shaping frock, it is characterised in that step is as follows：A, left socle (1), right support (2) are connected by horizontal key (3) and axial bond (6) with mould (11) first, entered by screw (9) Row pretension, compound guide bushing (10) is fitted into the axis hole of left socle (1), right support (2), using interference fit, then by roller bearing (4) penetrate in the axis hole of the left socle (1) with compound guide bushing (10) and right support (2)；B, blanking：Size according to the width of mould (11) sets plate (12) width dimensions, and the plate (12) of setting is wide The width ratio for spending size and mould (11) width dimensions is 96:100, plate (12) length is ensured more than mould (11) type face Length, while reserve jaw clamping length；C, pre-bending plate：By plate (12) be pre-bent to the approximate shape of mould (11) profile, then to the plate after pre-bending Material (12) is heat-treated；Plate (12) d, is installed：First roller bearing (4) is extracted out from left socle (1), in mould (11) and left socle (1), right support (2) gap of insertion plate (12) is reserved between, now, plate (12) pre-bending side is put on mould (11), then by roller bearing (4) Insert in left socle (1) and right support (2), left socle is then fastenedly connected by left end cap (7), right end cap (8) and screw (9) (1) and right support (2), to prevent roller bearing (4) left and right play in forming process；E, plate (11) is clamped：The both ends of plate (12) are clamped by the jaw of stretcher binding clip, adjust stretcher binding clip Jaw angle, the right position and swing angle of bracket, the luffing angle of the jaw is 0-60 °, and the swing angle of bracket is ±15°；Using the center of stretcher workbench as pivot, from the horizontal by certain angle, to ensure that jaw is being drawn When stretching plate (12), plate (12) is fitted in the mould surface portion on mould (11) completely；G, plate is stretched by the left stretching cylinder and right stretching cylinder of stretcher, plate (12) is sticked on mould completely (11) on type face, while ensure that plate (12) leaves deflection；H, after product stretch forming, in the nand-type face region of mould (11) with part positioning hole is made, in order to follow-up numerical control trimming The positioning of plate in process；I, trimming is carried out to the product edge after stretch forming, after the completion of above-mentioned plate (12) drawing and forming, roller bearing is extracted out, taken Lower product, left socle (1), right support (2) and roller bearing (4) are pulled down, then mould (11) is fixed on numerically controlled machine, will Product after slightly cutting is positioned on mould (11) by product after slightly cutting by the positioning hole in nand-type face region, then passes through five number of axle Control lathe and carry out milling.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710840243.XA CN107570628B (en) | 2017-09-18 | 2017-09-18 | Crotch class aircraft skin product forming tooling and forming technology |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710840243.XA CN107570628B (en) | 2017-09-18 | 2017-09-18 | Crotch class aircraft skin product forming tooling and forming technology |
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| CN107570628A true CN107570628A (en) | 2018-01-12 |
| CN107570628B CN107570628B (en) | 2019-03-05 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109530764A (en) * | 2018-12-07 | 2019-03-29 | 江西洪都航空工业集团有限责任公司 | A kind of sawtooth class aircraft skin clamping and numerical control shape milling method |
| CN111745027A (en) * | 2020-06-12 | 2020-10-09 | 陕西飞机工业（集团）有限公司 | Method for forming saddle-shaped skin part |
Citations (6)
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| GB1381183A (en) * | 1972-03-30 | 1975-01-22 | Imp Metal Ind Kynoch Ltd | Method of making structural metal panels |
| JPS60116595A (en) * | 1983-11-14 | 1985-06-24 | ユナイテツド・テクノロジーズ・コーポレイシヨン | Method and device for mounting skin body to skeleton-shaped frame |
| JP2001246424A (en) * | 2000-02-29 | 2001-09-11 | Japan Aircraft Mfg Co Ltd | Method and apparatus for press forming |
| CN101559442A (en) * | 2009-05-25 | 2009-10-21 | 吉林大学 | Sheet-stretching machine |
| JP5616209B2 (en) * | 2010-12-08 | 2014-10-29 | 川崎油工株式会社 | Stretch molding apparatus and method |
| CN106391816A (en) * | 2016-11-20 | 2017-02-15 | 吉林大学 | Pressure cylinder type plate drawing device and forming method thereof |
-
2017
- 2017-09-18 CN CN201710840243.XA patent/CN107570628B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1381183A (en) * | 1972-03-30 | 1975-01-22 | Imp Metal Ind Kynoch Ltd | Method of making structural metal panels |
| JPS60116595A (en) * | 1983-11-14 | 1985-06-24 | ユナイテツド・テクノロジーズ・コーポレイシヨン | Method and device for mounting skin body to skeleton-shaped frame |
| JP2001246424A (en) * | 2000-02-29 | 2001-09-11 | Japan Aircraft Mfg Co Ltd | Method and apparatus for press forming |
| CN101559442A (en) * | 2009-05-25 | 2009-10-21 | 吉林大学 | Sheet-stretching machine |
| JP5616209B2 (en) * | 2010-12-08 | 2014-10-29 | 川崎油工株式会社 | Stretch molding apparatus and method |
| CN106391816A (en) * | 2016-11-20 | 2017-02-15 | 吉林大学 | Pressure cylinder type plate drawing device and forming method thereof |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109530764A (en) * | 2018-12-07 | 2019-03-29 | 江西洪都航空工业集团有限责任公司 | A kind of sawtooth class aircraft skin clamping and numerical control shape milling method |
| CN111745027A (en) * | 2020-06-12 | 2020-10-09 | 陕西飞机工业（集团）有限公司 | Method for forming saddle-shaped skin part |
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| Publication number | Publication date |
|---|---|
| CN107570628B (en) | 2019-03-05 |
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