CN108480481A - A kind of method of stretch forming of airplane wingtip skins front edges - Google Patents
A kind of method of stretch forming of airplane wingtip skins front edges Download PDFInfo
- Publication number
- CN108480481A CN108480481A CN201810340547.4A CN201810340547A CN108480481A CN 108480481 A CN108480481 A CN 108480481A CN 201810340547 A CN201810340547 A CN 201810340547A CN 108480481 A CN108480481 A CN 108480481A
- Authority
- CN
- China
- Prior art keywords
- forming
- auxiliary mould
- top plate
- end top
- jaw
- Prior art date
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D37/00—Tools as parts of machines covered by this subclass
- B21D37/10—Die sets; Pillar guides
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D22/00—Shaping without cutting, by stamping, spinning, or deep-drawing
- B21D22/20—Deep-drawing
- B21D22/22—Deep-drawing with devices for holding the edge of the blanks
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D53/00—Making other particular articles
- B21D53/92—Making other particular articles other parts for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Blow-Moulding Or Thermoforming Of Plastics Or The Like (AREA)
Abstract
A kind of method of stretch forming of airplane wingtip skins front edges, there are one shaping dies and a pair of of auxiliary mould, shaping dies contains pedestal, the coupling part of forming surface and forming surface and pedestal, the auxiliary mould is symmetrical two eccentric T-type structures, a pair of of auxiliary mould is relatively fixed on the jaw of stretcher both sides, the plate of part forming is clamped at the jaw of stretcher both sides again, when pulling into forming, plate is pressed on the root of shaping dies forming face by the front end top plate of auxiliary mould by jaw, agree with forming surface root and the wedge-shaped side of pedestal junction the bevel edge part of auxiliary mould front end top plate.
Description
Technical field
It is specifically a kind of by by auxiliary mould, expanding the present invention relates to airplane component processing and manufacturing technology
The skin stretch forming equipment range of work produces the manufacturing process of airplane wingtip skins front edges part.
Background technology
Airplane wingtip skins front edges main function is the induced drag for reducing wing, improves lift resistance ratio and dissipation wingtip vortex
Stream.For wingtip device while improving aircraft aerodynamic performance, to its architectural characteristic, there is also certain influences, especially to reach
The technology requirement of aircraft wing Flutter Boundaries characteristic, construction weight characteristic and the rigidity of structure and wing flexible deformation etc..
These features cause such External Shape and rigidity to suffer from strict requirements.Dehisce since wing tip skins front edges part is small, on
Narrow distinctive appearance under width so that its processing technology is excessively poor, processes and the equipment such as conventional roll bending, stretching, lock pressure
It can not finally be shaped.By taking certain type wing tip covering as an example, assisted at present using roll bending, the process based on craft carries out
Production, but there are roll bending curvatures it is not in place, hand finish is difficult the problems such as, there are uneven, tool marks, slight for piece surface
Distortion, the mass defects such as external form is overproof, even if completing, part forming also is difficult to meet the higher shape of part and surface quality is wanted
It asks.
Skin stretch forming is widely used due to its excellent part forming quality, but stretch forming lathe is due to it
Jaw feature limits the range that can process part, with existing equipment it is difficult to shape such wing tip skins front edges part.
Find that a kind of new process solves the forming of airplane wingtip leading edge class skin part difficulty, forming quality difference is asked
Topic, be manufacture high quality airplane wingtip skins front edges part and ensure aircraft safety flight there is an urgent need to.
Invention content
A kind of method of stretch forming of airplane wingtip skins front edges, it is characterised in that：1) there are one shaping dies and a pair
Auxiliary mould, the shaping dies contain the coupling part of pedestal, forming surface and forming surface and pedestal, the forming surface
It is an irregular bullet corresponding with airplane wingtip skins front edges, forming surface root and pedestal junction are a wedge shapes
Side, the auxiliary mould are symmetrical two eccentric T-type structures, auxiliary mould horizontal front end top plate and vertical configuration
Riser between with rib reinforcement is reinforced, the edge of front end top plate is made of straight portion and bevel edge part, straight portion and tiltedly
The angle of rim portion is corresponding with the forming face of shaping dies, and rear end top plate is one convex with the matched step of stretcher jaw
It rises；2) a pair of of auxiliary mould is relatively fixed on the jaw of stretcher both sides, then the plate of part forming is clamped in
At the jaw of stretcher both sides, in stretch forming, plate is pressed on forming by jaw by the front end top plate of auxiliary mould
The root of section of mould molding surface, the wedge-shaped side contract of the bevel edge part and forming surface root and pedestal junction of auxiliary mould front end top plate
Conjunction.
The beneficial benefit of the application is：By the use of this auxiliary mould, it is wide to increase the most narrow processing of drawing machine tool
Degree, while drawing force load is born, guided features stretch the flowing of transition region material, and the deformation of constraint part side surface solves tool
The manufacture problem for having the wing tip skins front edges of complex appearance has been produced the wing tip skins front edges part of good quality, has been made simultaneously
The manufacture for obtaining such part has new approaches.Auxiliary mould is skillfully constructed, is simple in structure, easy to operate, the great wound of manufacturing process
New property.
Attached drawing is described in further detail this application with reference to embodiments：
Description of the drawings
Fig. 1 is airplane wingtip skins front edges design of part schematic diagram；
Fig. 2 is airplane wingtip skins front edges part forming mold structure diagram；
Fig. 3 is airplane wingtip skins front edges part auxiliary mould structure schematic diagram；
Fig. 4 is airplane wingtip skins front edges part stretch forming principle schematic；
Fig. 5 is airplane wingtip skins front edges part method of stretch forming schematic diagram；
Explanation is numbered in figure：1 airplane wingtip skins front edges part, 2 shaping dies, 3 forming faces, 4 pedestals, 5 coupling parts,
6 wedge-shaped sides, 7 auxiliary moulds, 8 front end top plates, 9 risers, 10 reinforcing ribs, 11 bevel edge parts, 12 straight portions, 13 rear end top plates,
14 jaws, 15 plates
Specific implementation mode
Referring to the manufacturing process for the airplane wingtip skins front edges that attached drawing, the application propose, by shaping dies 2 and auxiliary mould
Tool 7, the minimum spacing of extension drawing machine tool jaw 14, auxiliary mould, which gets involved in External Shape and completes part, when stretch forming stretches
Forming.Coupling part 5 of the shaping dies 2 containing pedestal 4, forming surface 3 and forming surface and pedestal, as shown in Fig. 2, at
Type face 2 is an irregular bullet corresponding with airplane wingtip skins front edges part 1, and forming surface root is with pedestal junction
One wedge-shaped side 6, the auxiliary mould 7 is symmetrical two eccentric T-type structures, as shown in figure 3,7 water of auxiliary mould
It is reinforced with ribs 10 between the riser 9 of flat-shaped front end top plate 8 and vertical configuration, the edge of front end top plate 8 is by straight portion 12
It is constituted with bevel edge part 11, the angle of straight portion 12 and bevel edge part 11 is corresponding with the forming face 3 of shaping dies 2, rear end
Top plate 13 is one and stretcher jaw 14 matched step protrusion.
Part stretch before, a pair of of auxiliary mould 7 is relatively fixed on the jaw 14 of stretcher both sides, then by part at
The plate 15 of shape is clamped at the jaw 14 of stretcher both sides, when stretch forming, front end that jaw 14 passes through auxiliary mould 7
Plate 15 is compressed the root to 2 forming face 3 of shaping dies by top plate 8, the bevel edge part 11 of 7 front end top plate 8 of auxiliary mould at
3 root of type face and the wedge-shaped side 6 of pedestal junction are agreed with, it is ensured that the forming face of the fitting shaping dies completely of plate 15, it is complete
At part forming.
Above-mentioned auxiliary mould is symmetrical two, and shape is eccentric T-type, and there are force transmission holes four on each auxiliary mould
Auxiliary mould, is fixed on jaw by a, location hole six with bolt, with pin stick by load transmission suffered by auxiliary mould to stretch
On equipment jaw, there are two ribs on every piece of auxiliary mould, for reinforcing auxiliary mould intensity.
By taking certain model skin stretch forming equipment as an example, equipment jaw minimum spacing is 100mm, stretchable part width
Must be up-narrow and down-wide, the limit is upper similarly hereinafter wide.After using proposed auxiliary mould, the minimum spacing of stretcher jaw by
100mm has been extended to 610mm so that wing tip skins front edges it is this kind of it is small dehisce, part wide at the top and narrow at the bottom can be with stretch forming.
Claims (3)
1. a kind of method of stretch forming of airplane wingtip skins front edges, it is characterised in that：1) there are one shaping dies and a pair are auxiliary
Mold, the shaping dies is helped to contain the coupling part of pedestal, forming surface and forming surface and pedestal, the forming surface is
One irregular bullet corresponding with airplane wingtip skins front edges, forming surface root are a wedge-shaped sides with pedestal junction,
The auxiliary mould is symmetrical two eccentric T-type structures, the horizontal front end top plate of auxiliary mould and vertical configuration
With rib reinforcement is reinforced between riser, the edge of front end top plate is made of straight portion and bevel edge part, straight portion and bevel edge
Partial angle is corresponding with the forming face of shaping dies, and rear end top plate is one and the matched step protrusion of stretcher jaw；
2) a pair of of auxiliary mould is relatively fixed on the jaw of stretcher both sides, then the plate of part forming is clamped in stretching
At the jaw of equipment both sides, when pulling into forming, plate is pressed on shaping dies by jaw by the front end top plate of auxiliary mould
The root of forming face, bevel edge part and the forming surface root and the wedge-shaped side of pedestal junction of auxiliary mould front end top plate are agreed with i.e.
It can.
2. a kind of auxiliary mould of airplane wingtip skins front edges stretch forming, which is characterized in that the auxiliary mould is left and right
Symmetrical two eccentric T-type structures, use between the horizontal front end top plate of auxiliary mould and the riser of vertical configuration and reinforce rib reinforcement,
The edge of front end top plate is made of straight portion and bevel edge part, before the angle and airplane wingtip of straight portion and bevel edge part
The forming face of edge skin part corresponds to, and rear end top plate is one and the matched step protrusion of stretcher jaw.
3. the auxiliary mould of airplane wingtip skins front edges stretch forming as described in claim 1, which is characterized in that before described
There are one arcing outer edges for the straight portion of end ceiling edge and bevel edge part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810340547.4A CN108480481B (en) | 2018-04-16 | 2018-04-16 | Stretch forming method for airplane wingtip front edge skin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810340547.4A CN108480481B (en) | 2018-04-16 | 2018-04-16 | Stretch forming method for airplane wingtip front edge skin |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108480481A true CN108480481A (en) | 2018-09-04 |
| CN108480481B CN108480481B (en) | 2023-06-23 |
Family
ID=63314666
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810340547.4A Active CN108480481B (en) | 2018-04-16 | 2018-04-16 | Stretch forming method for airplane wingtip front edge skin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108480481B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115871955A (en) * | 2023-02-21 | 2023-03-31 | 中国人民解放军95633部队 | Method for repairing front edge skin of airplane wing and empennage |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2811596A1 (en) * | 2000-07-13 | 2002-01-18 | Fokker Aerostructures Bv | Manufacture of sheet metal components e.g. for vehicles by forming and stretching uses template and locking heads with double curved surfaces |
| CN101894181A (en) * | 2010-06-30 | 2010-11-24 | 上海飞机制造有限公司 | Design method of loading trajectory of VTL type numerical control skin stretch forming machine |
| CN202591440U (en) * | 2012-03-22 | 2012-12-12 | 吉林省元隆达工装设备有限公司 | Internal high-pressure forming sleeved-connection device for camshafts |
| JP2013087309A (en) * | 2011-10-14 | 2013-05-13 | Mitsubishi Shindoh Co Ltd | Copper alloy sheet with deformed cross section having low anisotropy of bending work and method for manufacturing the same |
| CN104174733A (en) * | 2014-09-17 | 2014-12-03 | 安徽理工大学 | Four-degree-of-freedom series-parallel multi-point flexible shape pulling machine |
| CN104475514A (en) * | 2014-11-28 | 2015-04-01 | 上海理工大学 | Tensioning and bending device for metal sections |
| JP6133965B1 (en) * | 2015-12-17 | 2017-05-24 | 日新製鋼株式会社 | Evaluation method of stretch flangeability |
| CN208214068U (en) * | 2018-04-16 | 2018-12-11 | 西安飞机工业（集团）有限责任公司 | A kind of auxiliary mould of airplane wingtip skins front edges stretch forming |
-
2018
- 2018-04-16 CN CN201810340547.4A patent/CN108480481B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2811596A1 (en) * | 2000-07-13 | 2002-01-18 | Fokker Aerostructures Bv | Manufacture of sheet metal components e.g. for vehicles by forming and stretching uses template and locking heads with double curved surfaces |
| CN101894181A (en) * | 2010-06-30 | 2010-11-24 | 上海飞机制造有限公司 | Design method of loading trajectory of VTL type numerical control skin stretch forming machine |
| JP2013087309A (en) * | 2011-10-14 | 2013-05-13 | Mitsubishi Shindoh Co Ltd | Copper alloy sheet with deformed cross section having low anisotropy of bending work and method for manufacturing the same |
| CN202591440U (en) * | 2012-03-22 | 2012-12-12 | 吉林省元隆达工装设备有限公司 | Internal high-pressure forming sleeved-connection device for camshafts |
| CN104174733A (en) * | 2014-09-17 | 2014-12-03 | 安徽理工大学 | Four-degree-of-freedom series-parallel multi-point flexible shape pulling machine |
| CN104475514A (en) * | 2014-11-28 | 2015-04-01 | 上海理工大学 | Tensioning and bending device for metal sections |
| JP6133965B1 (en) * | 2015-12-17 | 2017-05-24 | 日新製鋼株式会社 | Evaluation method of stretch flangeability |
| CN208214068U (en) * | 2018-04-16 | 2018-12-11 | 西安飞机工业（集团）有限责任公司 | A kind of auxiliary mould of airplane wingtip skins front edges stretch forming |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115871955A (en) * | 2023-02-21 | 2023-03-31 | 中国人民解放军95633部队 | Method for repairing front edge skin of airplane wing and empennage |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108480481B (en) | 2023-06-23 |
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