CN211071428U - Wing leading edge skin processingequipment of aircraft - Google Patents
Wing leading edge skin processingequipment of aircraft Download PDFInfo
- Publication number
- CN211071428U CN211071428U CN201922208669.0U CN201922208669U CN211071428U CN 211071428 U CN211071428 U CN 211071428U CN 201922208669 U CN201922208669 U CN 201922208669U CN 211071428 U CN211071428 U CN 211071428U
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- leading edge
- plate
- wing
- top surface
- wing leading
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Abstract
The utility model discloses a wing leading edge skin processingequipment of aircraft, including die carrier device and leading edge mould, the die carrier device includes that bottom plate and two are vertical and be parallel to each other and fix the backup pad at the bottom plate both ends, forms the gap between two backup pads, is provided with the pneumatic cylinder of fixing at the bottom plate top surface in the gap, and reciprocating motion can be vertically done to the output shaft of pneumatic cylinder, and the output shaft and the leading edge mould bottom of pneumatic cylinder are connected, leading edge mould and the wing leading edge skin phase-match of aircraft, die carrier device top surface is fixed with a metal sheet, and the leading edge mould pushes up the metal sheet for the metal sheet upwards be stretched into with required wing leading edge skin, the utility model discloses simple structure, the wing leading edge of making, the skin surface is smooth, and thickness is even, and is high with the laminating degree of.
Description
Technical Field
The utility model relates to an aircraft wing leading edge covering processing technology field, concretely relates to wing leading edge covering processingequipment of aircraft.
Background
The composite material is widely used along with the more and more outstanding advantages of the composite material compared with the traditional metal material, particularly in the aerospace industry, but the full-member skin of the aircraft wing has a complex three-dimensional structure and is not easy to form, the traditional aircraft wing leading edge skin basically adopts roll forming, the web plate surface needs to be rolled for many times due to the small top end radius of the wing leading edge skin, the fibers of the deformed part of the aluminum alloy part are not elongated, the crystal lattice in the material does not slide, the surface defect of the skin is large, the surface has edges, the elasticity of the skin is large, and the fitting degree with the leading edge of the wing after the skin is formed is low.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a wing leading edge covering processingequipment of aircraft for solve the defect that there is the arris in the wing leading edge covering of aircraft, it is low with the laminating degree of wing leading edge, little to the width, the comparatively difficult problem of the wing covering shaping of the higher degree of depth.
In order to solve the technical problem, the utility model discloses a following scheme:
the utility model provides a wing leading edge covering processingequipment of aircraft, includes die carrier device and leading edge mould, the die carrier device includes bottom plate and two vertical and the backup pad of fixing at the bottom plate both ends that are parallel to each other, forms the gap between two backup pads, is provided with the pneumatic cylinder of fixing at the bottom plate top surface in the gap, and the output shaft of pneumatic cylinder can be vertical reciprocating motion, and the output shaft and the leading edge mould bottom of pneumatic cylinder are connected, and leading edge mould and the wing leading edge covering phase-match of aircraft, die carrier device top surface is fixed with a metal sheet, and the leading edge mould pushes up the metal sheet for the metal sheet is upwards stretched into required wing leading edge covering.
By adopting the technical scheme, the utility model comprises a die carrier device and a front edge die, the front edge die is matched with the required aircraft wing skin, the die carrier device comprises a bottom plate which is horizontally arranged, two supporting plates which are parallel to each other are vertically fixed on two sides of the bottom plate, a gap with a certain distance is formed between the two supporting plates, a hydraulic cylinder is arranged in the gap and is fixed on the top surface of the bottom plate, an output shaft of the hydraulic cylinder is vertically upward and can do reciprocating motion, the output shaft of the hydraulic cylinder is firmly connected with the bottom surface of the front edge die, a metal plate is fixed on the top surface of the die carrier device, the front edge die moves upwards slowly through the output shaft of the hydraulic cylinder under the action of the hydraulic cylinder, the top of the front edge die is contacted with the metal plate and continues moving upwards slowly, so that the metal plate is stretched upwards until, because the leading edge mould makes progress and constantly stretches to the metal sheet, the metal sheet material fibre is evenly elongated for the inside lattice interval of metal sheet takes place to slide, just so makes the aluminium alloy surface arris can not appear, and the surface is smooth, and the metal sheet thickness after being stretched is even, and just very high with the laminating degree of wing leading edge, the utility model discloses a leading edge mould can be according to the degree of depth of wing leading edge, the different leading edge mould of width preparation, thereby it is less to satisfy the width, and the darker wing leading edge covering of the degree of depth can also guarantee that the product quality of making is more excellent.
Further, as a preferred technical scheme, the top edge of the supporting plate is provided with a fixing block, the fixing block is flush with the top surface of the supporting plate, the fixing block is provided with a bolt hole, the top surface of the supporting plate is also provided with a pressing plate used for clamping a metal plate, the front end and the rear end of the pressing plate are provided with through holes corresponding to the bolt holes, and the through holes are used for bolts to pass through.
By adopting the technical scheme, the front edge and the rear edge of the top end of the supporting plate are uniformly provided with the fixing blocks, the fixing blocks are flush with the top surface of the supporting plate, the bolt holes are formed in the two sides of the fixing blocks and internally threaded, the top surface of the supporting plate is provided with the pressing plate for fixedly clamping the metal plate, the front end and the rear end of the pressing plate are provided with the through holes corresponding to the bolt holes, the bolts penetrate through the through holes and the bolt holes, the threaded connection is firm, the metal plate is fixedly clamped, and the metal plate is conveniently mounted and dismounted through the threaded connection between the pressing plate.
Further, as a preferred technical scheme, a plurality of identical hydraulic cylinders are arranged on the upper surface of the bottom plate along the vertical central line direction of the gap.
Owing to adopt above-mentioned technical scheme, a plurality of the same pneumatic cylinders are installed along the direction of the vertical central line in gap to the upper surface of bottom plate, the utility model discloses select equidistant three pneumatic cylinder of installation, make the leading edge mould enough to the ascending tensile force of metal sheet like this, even interval distribution can guarantee that the leading edge mould stretches evenly to the top of metal sheet, guarantees that the metal sheet is by tensile surface smoothness, the arris can not appear.
Further, as a preferred technical scheme, the top surface of the supporting plate and the bottom surface of the pressing plate are both fixedly connected with anti-skidding rubber plates.
Due to the adoption of the technical scheme, the anti-skid rubber plates are connected to the top surface of the supporting plate and the bottom surface of the pressing plate, so that the edges of the metal plate can be protected from being damaged in the process of being stretched, and the metal plate is prevented from being pulled out from the space between the pressing plate and the supporting plate, so that the product is unqualified and the material is wasted.
Furthermore, as a preferred technical scheme, the side of the supporting plate is vertically fixed with a supporting rod, the top of the supporting rod is vertically connected with a positioning rod, and the positioning rod is used for positioning the stretched height of the metal plate.
By adopting the technical scheme, the supporting rod is vertically and fixedly connected to the side surface of the supporting plate, the positioning rod is horizontally connected to the top of the supporting rod, the supporting rod and the positioning rod are integrally designed, and the positioning rod is used for positioning the metal plate at the stretched height, namely when the front edge mold stretches the metal plate upwards to contact with the positioning rod, the action of the hydraulic cylinder is stopped, so that the metal plate is prevented from being too stretched to be damaged.
Further, as a preferred technical scheme, the metal plate is an aluminum alloy, a titanium alloy or a high-temperature alloy.
The utility model discloses beneficial effect who has:
1. the utility model discloses fix the top surface at the die carrier device with the metal sheet, leading edge mould is under the effect of pneumatic cylinder, upwards slowly top stretch, drive the metal sheet by tensile, until forming required aircraft wing leading edge skin product, because the metal sheet is evenly stretched, inside material fiber is also stretched, the inside lattice interval of metal sheet takes place to slide, just so make the arris can not appear on the aluminum alloy surface, the surface is smooth, the metal sheet thickness after being stretched is even, just very high with the laminating degree of wing leading edge, moreover the utility model discloses a leading edge mould can be according to the degree of depth of wing leading edge, the different leading edge mould of width preparation to satisfy the width less, the deeper wing leading edge skin of the degree of depth, the product quality that can also guarantee to make is more excellent.
Drawings
Fig. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of the metal plate of the present invention after being stretched;
fig. 3 is a left side view of fig. 1.
Reference numerals: 1-mould frame device, 101-support plate, 102-bottom plate, 2-front edge mould, 3-hydraulic cylinder, 301-output shaft, 4-metal plate, 5-pressure plate, 6-fixing block, 7-bolt hole, 8-through hole, 9-bolt, 10-antiskid rubber plate, 11-support rod, 12-positioning rod and 13-gap.
Detailed Description
The present invention will be described in further detail with reference to the following examples and drawings, but the present invention is not limited thereto.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "longitudinal", "lateral", "horizontal", "inner", "outer", "front", "rear", "top", "bottom", and the like indicate the position or positional relationship based on the position or positional relationship shown in the drawings, or the position or positional relationship which is usually placed when the product of the present invention is used, and the terms are only for convenience of description of the present invention and simplifying the description, but do not indicate or imply that the device or element to which the term refers must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention.
In the description of the present invention, it should be further noted that, unless otherwise explicitly specified or limited, the terms "disposed," "opened," "mounted," "connected," and "connected" are to be construed broadly, e.g., as either a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Examples
The utility model provides a wing leading edge covering processingequipment of aircraft, includes die carrier device 1 and leading edge mould 2, die carrier device 1 includes that bottom plate 102 and two are vertical and parallel to each other fix the backup pad 101 at bottom plate 102 both ends, forms gap 13 between two backup pads 101, is provided with in the gap 13 to fix the pneumatic cylinder 3 at bottom plate 102 top surface, and reciprocating motion can be done in vertical to the output shaft 301 of pneumatic cylinder 3, and the output shaft 301 and the 2 bottoms of leading edge mould of pneumatic cylinder 3 are connected, leading edge mould 2 and the wing leading edge covering phase-match of aircraft, 1 top surface of die carrier device is fixed with a metal sheet 4, and leading edge mould 2 upwards pushes up metal sheet 4 for metal sheet 4 upwards is stretched into required wing leading edge covering.
Specifically, as shown in fig. 1 and 2, the utility model comprises a mold frame device 1 and a leading edge mold 2, the leading edge mold 2 is matched with the required aircraft wing skin, the mold frame device 1 comprises a bottom plate 102 horizontally arranged, two parallel supporting plates 101 are vertically fixed on two sides of the bottom plate 102, a gap 13 with a certain distance is formed between the two supporting plates 101, a hydraulic cylinder 3 is arranged in the gap 13, the hydraulic cylinder 3 is fixed on the top surface of the bottom plate 102, an output shaft 301 of the hydraulic cylinder 3 is vertically upward and can do reciprocating motion vertically, the output shaft 301 of the hydraulic cylinder 3 is firmly connected with the bottom surface of the leading edge mold 2, a metal plate 4 is fixed on the top surface of the mold frame device 1, the metal plate is aluminum alloy, titanium alloy or high-temperature alloy leading edge mold 2, under the action of the hydraulic cylinder 3, the output shaft 301 of the hydraulic cylinder 3 moves slowly upward, the, and continue slow upward movement for metal sheet 4 is upwards stretched, until metal sheet 4 is stretched into required wing leading edge covering, because leading edge mould 2 upwards is constantly stretched to metal sheet 4, metal sheet 4 material fibre is evenly elongated, make the inside lattice interval of metal sheet 4 take place to slide, just so make the aluminium alloy surface can not appear the arris, the surface is smooth, 4 thickness of metal sheet after being stretched are even, just very high with the laminating degree of wing leading edge, the utility model discloses a leading edge mould 2 can be according to the degree of depth of wing leading edge, the different leading edge mould 2 of width preparation, thereby it is less to satisfy the width, and the deep wing leading edge covering of degree of depth can also guarantee that the product quality of manufacturing is more excellent.
On the basis of the above embodiment, the top edge of the supporting plate 101 is provided with the fixing block 6, the fixing block 6 is flush with the top surface of the supporting plate 101, the fixing block 6 is provided with the bolt hole 7, the top surface of the supporting plate 101 is also provided with the pressing plate 5 for clamping the metal plate 4, the front end and the rear end of the pressing plate 5 are provided with the through hole 8 corresponding to the bolt hole 7, and the through hole 8 is used for the bolt 9 to pass through.
Specifically, the front edge and the rear edge of the top end of the supporting plate 101 are uniformly designed with the fixing blocks 6, the fixing blocks 6 are flush with the top surface of the supporting plate 101, bolt holes 7 are formed in two sides of the fixing blocks 6 and internally tapped, the top surface of the supporting plate 101 is provided with the pressing plate 5 for fixedly clamping the metal plate 4, the front end and the rear end of the pressing plate 5 are provided with through holes 8 corresponding to the bolt holes 7, the bolts 9 penetrate through the through holes 8 and the bolt holes 7, the threaded connection is firm, the metal plate 4 is fixedly clamped, and the metal plate 4 is conveniently installed and detached through the threaded connection of the pressing plate 5 and the fixing blocks.
On the basis of the above embodiment, the upper surface of the bottom plate 101 is provided with a plurality of identical hydraulic cylinders 3 along the vertical central line direction of the gap 13.
Specifically, a plurality of the same pneumatic cylinders 3 are installed along the direction of the vertical central line in gap 13 to the upper surface of bottom plate 101, the utility model discloses select equidistant three pneumatic cylinder 3 of installation, make leading edge mould 2 enough to the ascending tensile force of metal sheet 4 like this, even interval distribution can guarantee that leading edge mould 2 stretches evenly to the top of metal sheet 4, guarantees that metal sheet 4 is by tensile surperficial smooth, the arris can not appear.
On the basis of the above embodiment, the anti-skid rubber plate 10 is fixedly connected to both the top surface of the supporting plate 101 and the bottom surface of the pressing plate 5.
Specifically, as shown in fig. 3, the top surface of the supporting plate 101 and the bottom surface of the pressing plate 5 are both connected with the anti-slip rubber plate 10, so that the edges of the metal plate 4 can be protected from being damaged in the stretching process, and the metal plate 4 is prevented from being pulled out from the space between the pressing plate 5 and the supporting plate 101, so that the product is unqualified and the material is wasted.
On the basis of the above embodiment, the side surface of the supporting plate 101 is vertically fixed with a supporting rod 11, the top of the supporting rod 11 is horizontally connected with a positioning rod 12, and the positioning rod 12 is used for positioning the stretched height of the metal plate 4.
Specifically, a vertical fixed connection bracing piece 11 in the side of backup pad 101, the top horizontally connected with locating lever 12 of bracing piece 11, bracing piece 11 is 90 with locating lever 12 contained angle, bracing piece 11 and locating lever 12 are the integrated design, locating lever 12 is used for the location of metal sheet 4 by tensile height, when leading edge mould 2 upwards stretched metal sheet 4 and locating lever 12 contact promptly, stop the action of pneumatic cylinder 3, prevent to stretch too much, cause the damage of metal sheet 4.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and the technical essence of the present invention is that within the spirit and principle of the present invention, any simple modification, equivalent replacement, and improvement made to the above embodiments are all within the protection scope of the technical solution of the present invention.
Claims (6)
1. A device for processing the front edge skin of an airplane wing comprises a mould frame device (1) and a front edge mould (2), the device is characterized in that the die carrier device (1) comprises a bottom plate (102) and two vertical supporting plates (101) which are parallel to each other and fixed at two ends of the bottom plate (102), a gap (13) is formed between the two supporting plates (101), a hydraulic cylinder (3) fixed on the top surface of the bottom plate (102) is arranged in the gap (13), an output shaft (301) of the hydraulic cylinder (3) can reciprocate vertically, the output shaft (301) of the hydraulic cylinder (3) is connected with the bottom of a front edge die (2), the front edge die (2) is matched with a wing front edge skin of an airplane, a metal plate (4) is fixed on the top surface of the die carrier device (1), and the front edge die (2) pushes the metal plate (4) upwards, so that the metal plate (4) is upwards stretched into a required wing front edge skin.
2. The aircraft wing leading edge skin processing device according to claim 1, characterized in that a fixing block (6) is arranged at the top end edge of the supporting plate (101), the fixing block (6) is flush with the top surface of the supporting plate (101), a bolt hole (7) is formed in the fixing block (6), a pressing plate (5) used for clamping the metal plate (4) is further arranged on the top surface of the supporting plate (101), through holes (8) corresponding to the bolt holes (7) are formed in the front end and the rear end of the pressing plate (5), and the through holes (8) are used for bolts (9) to penetrate through.
3. The wing leading edge skin processing device of an aircraft according to claim 1, characterized in that the upper surface of the base plate (102) is provided with a plurality of identical hydraulic cylinders (3) in the direction of the vertical centre line of the slot (13).
4. The wing leading edge skin processing device of an aircraft according to claim 1, characterized in that the top surface of the support plate (101) and the bottom surface of the pressure plate (5) are fixedly connected with an anti-skid rubber plate (10).
5. The device for processing the wing leading edge skin of the aircraft as claimed in claim 1, characterized in that a supporting rod (11) is vertically fixed to the side of the supporting plate (101), a positioning rod (12) is horizontally connected to the top of the supporting rod (11), and the positioning rod (12) is used for positioning the stretched height of the metal plate (4).
6. The wing leading edge skin processing device of an aircraft according to claim 1, characterized in that the metal sheet (4) is an aluminum alloy, a titanium alloy or a high temperature alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922208669.0U CN211071428U (en) | 2019-12-11 | 2019-12-11 | Wing leading edge skin processingequipment of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922208669.0U CN211071428U (en) | 2019-12-11 | 2019-12-11 | Wing leading edge skin processingequipment of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211071428U true CN211071428U (en) | 2020-07-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922208669.0U Expired - Fee Related CN211071428U (en) | 2019-12-11 | 2019-12-11 | Wing leading edge skin processingequipment of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211071428U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114798932A (en) * | 2022-04-22 | 2022-07-29 | 惠州左右家私有限公司 | Method for covering plate |
-
2019
- 2019-12-11 CN CN201922208669.0U patent/CN211071428U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114798932A (en) * | 2022-04-22 | 2022-07-29 | 惠州左右家私有限公司 | Method for covering plate |
| CN114798932B (en) * | 2022-04-22 | 2024-02-23 | 惠州左右家私有限公司 | Panel skin method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200724 Termination date: 20211211 |