CN114771805A - Negative Poisson ratio deformable flexible grid for gaps of flaps or ailerons - Google Patents
Negative Poisson ratio deformable flexible grid for gaps of flaps or ailerons Download PDFInfo
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- CN114771805A CN114771805A CN202210393789.6A CN202210393789A CN114771805A CN 114771805 A CN114771805 A CN 114771805A CN 202210393789 A CN202210393789 A CN 202210393789A CN 114771805 A CN114771805 A CN 114771805A
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- aileron
- flap
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- 238000000034 method Methods 0.000 claims abstract description 10
- 230000007704 transition Effects 0.000 claims description 14
- 238000010146 3D printing Methods 0.000 claims description 6
- 206010003694 Atrophy Diseases 0.000 abstract description 2
- 230000037444 atrophy Effects 0.000 abstract description 2
- 230000002265 prevention Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 230000001154 acute effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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Abstract
The application belongs to the technical field of aircraft structures, and particularly relates to a negative Poisson's ratio deformable flexible grid for a gap of a flap or an aileron. The method comprises the following steps: the aircraft wing structure comprises a first area, a second area and a third area which are sequentially connected, wherein the first area is a wing connecting area and is used for being connected with a wing; the second area is a negative Poisson ratio grid area, the second area comprises a plurality of regularly arranged unit cell structures, and each unit cell structure is formed by two hollow isosceles trapezoids with short sides butted with each other; the third region is a flap or aileron connection region for connection to a flap or aileron; the length of the whole structure formed by the first area, the second area and the third area is consistent with the length of a flap or an aileron gap, and the width of the second area is consistent with the width of the flap or the aileron gap. The flexible grid of negative poisson's ratio flexible of this application utilization is peculiar to draw bloated characteristic, solves current form grid and can produce phenomenons such as warpage, atrophy in the deformation process.
Description
Technical Field
The application belongs to the technical field of aircraft structures, and particularly relates to a negative Poisson ratio deformable flexible grid for a flap or aileron gap.
Background
In the prior art, structures such as sealing plates are usually installed in gaps of a flap and an aileron, and when the angles of the flap and the aileron are changed, a larger gap is exposed, so that the exposure risk of an airplane is greatly increased.
In order to improve the anti-exposure performance of the airplane, all openings and cavity structures on the surface of the airplane body are shielded by adopting grids. The gap cavities at the flap and aileron parts can not use the existing fixed structure metal shielding grids, so the flexible deformable shielding grids become important parts for solving the problem of exposure prevention of the movable opening structure. However, the conventional grid may warp or shrink during the deformation process, which is not good for the exposure prevention purpose.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a negative poisson's ratio deformable flexible grid for a flap or aileron slot to address at least one problem with the prior art.
The technical scheme of the application is as follows:
a negative poisson's ratio deformable flexible grid for a flap or aileron slot, comprising: a first region, a second region, and a third region connected in sequence, wherein,
the first area is a wing connecting area and is used for being connected with a wing;
the second area is a negative Poisson ratio grid area, the second area comprises a plurality of unit cell structures which are regularly arranged, each unit cell structure is formed by two hollow isosceles trapezoids with the short sides butted, the base angle of each isosceles trapezoid is 60 degrees, and the side edge L1, the long side L2 and the short side L3 meet the following requirements:
wherein r is the radius of a circumscribed circle of the unit cell structure;
the third region is a flap or aileron connection region for connection to a flap or aileron;
the length of the integral structure formed by the first area, the second area and the third area is consistent with the length of a flap or an aileron gap, and the width of the second area is consistent with the width of the flap or the aileron gap.
In at least one embodiment of the present application, a plurality of connecting portions are disposed at an edge of one side of the first region, which is away from the second region, bolt holes are opened on the connecting portions, and the first region is connected with a wing through bolts.
In at least one embodiment of the present application, a plurality of connecting portions are provided at an edge of one side of the third region, which is far away from the second region, bolt holes are opened on the connecting portions, and the third region is connected with a flap or an aileron through bolts.
In at least one embodiment of the present application, the outer diameter D of the connecting portion is 15mm, the diameter D of the bolt hole is 6mm, and the distance between two adjacent bolt holes is 25mm to 45 mm.
In at least one embodiment of the present application, the first region includes a first transition region connected to the second region and a first connection region connected to the wing, wherein the first transition region has a gradually changing thickness, the thickness gradually increases from the second region side to the first connection region side, and the thickness of the first connection region has a constant value, which is not less than 3 mm.
In at least one embodiment of the present application, the third region includes a third transition region connected to the second region and a third connection region connected to the flap or aileron, wherein the third transition region has a gradually changing thickness, the thickness gradually increases from the second region side to the third connection region side, and the thickness of the third connection region has a constant value, which is not less than 3 mm.
In at least one embodiment of the present application, the second region is formed using a 3D printing process.
In at least one embodiment of the present application, an included angle inside the unit cell structure of the second region is chamfered.
The invention has at least the following beneficial technical effects:
the negative Poisson ratio deformable flexible grid for the gaps of the flaps or the ailerons utilizes the special expansion characteristic of the negative Poisson ratio deformable flexible grid, solves the problems that the existing grid can generate warping, atrophy and the like in the deformation process, and achieves the purpose that the grid still has invisible performance when being deformed.
Drawings
FIG. 1 is a schematic view of an overall negative Poisson's ratio deformable flexible grid for a flap or aileron slot according to an embodiment of the present application;
FIG. 2 is a schematic view of a junction between a first region and a third region according to an embodiment of the present application;
FIG. 3 is a schematic thickness diagram of a first region and a third region of an embodiment of the present application;
FIG. 4 is a schematic diagram of a unit cell structure according to an embodiment of the present application.
Wherein:
1-a first region; 2-a second region; 3-the third zone.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described are some, but not all embodiments of the disclosure. The embodiments described below with reference to the accompanying drawings are illustrative and intended to explain the present application and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort belong to the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "central," "longitudinal," "lateral," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings, which are based on the orientation or positional relationship shown in the drawings, and are used for convenience in describing the present application and for simplicity in description, but do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 4.
The present application provides a negative poisson's ratio deformable flexible grid for a flap or aileron slot, comprising: a first region 1, a second region 2, and a third region 1 connected in this order.
Specifically, referring to fig. 1, the first area 1 is a wing connection area for connecting to a wing; the second area 2 is a negative Poisson ratio grid area, and the second area is composed of a plurality of unit cell structures which are regularly arranged, wherein the unit cell structures in the same row are connected in an initial position, the unit cell structures in two adjacent rows are arranged in a cross mode, each unit cell structure is composed of isosceles trapezoids with two hollowed-out short sides in butt joint, the size of the unit cell structure of the grid is determined according to the anti-exposure design requirement, the base angle of the isosceles trapezoids is 60 degrees, and the side edge L1, the long edge L2 and the short edge L3 meet the following requirements:
wherein r is the circumscribed circle radius of the unit cell structure meeting the anti-exposure design requirement;
further, the third region 1 is a flap or aileron connection region for connection to a flap or aileron; the length of the overall structure formed by the first region 1, the second region 2 and the third region 1 is consistent with the length of a flap or aileron gap to be filled, and the width of the second region 2 is consistent with the width of the flap or aileron gap.
In a preferred embodiment of the present application, as shown in fig. 2, a plurality of protruding connecting portions are disposed at an edge of one side of the first region 1 away from the second region 2, the connecting portions are provided with bolt holes, and the first region 1 is connected to the wing through bolts. A plurality of protruding connecting parts are arranged at one side edge of the third area 1, which is far away from the second area 2, bolt holes are formed in the connecting parts, and the third area 1 is connected with a flap or an aileron through bolts. In the present embodiment, considering the structural bearing and connecting region, the outer diameter D of the connecting portion of the first region 1 and the third region 3 is generally 15mm, the diameter D of the bolt hole on the connecting portion is generally 6mm, and the distance between two adjacent bolt holes is between 25mm and 45 mm.
In a preferred embodiment of the present application, as shown in fig. 3, the first area 1 comprises a first transition area and a first connection area, the first transition area is connected with the second area 2, the first connection area is connected with the wing, wherein the first transition area adopts a gradual thickness, the thickness of the first connection area gradually increases from the side of the second area 2 to the side of the first connection area, and the thickness of the first connection area is a fixed value, and the fixed value is determined according to the required extrusion strength of the bolt hole and is generally not less than 3 mm. The third region 3 comprises a third transition region and a third connection region, the third transition region is connected with the second region, the third connection region is connected with a flap or an aileron, the third transition region is of gradually-changed thickness, the thickness from one side of the second region 2 to one side of the third connection region is gradually increased, the thickness of the third connection region is a fixed value, and the fixed value is determined according to the extrusion strength required by a bolt hole and is generally not less than 3 mm.
In the preferred embodiment of the present application, the negative poisson's ratio grating region of the second region 2 is designed to have a thickness that is determined by the actual requirements of the aircraft design, and the unit cell structure is sized according to the requirements of the anti-exposure design. Preferably, the second area 2 is formed by adopting a 3D printing process, the included angle in the single cell structure of the second area 2 is chamfered, and the chamfer R in the single cell structure is related to the 3D printing process; the thickness t1 of each side of the unit cell structure is also related to the 3D printing process, the acute angle of the unit cell structure is 60 degrees, the obtuse angle of the unit cell structure is 120 degrees, and the radius r of the circumscribed circle is determined according to the anti-exposure requirement.
In one embodiment of the application, specific parameters of the deformable flexible grid with negative poisson ratio for the gap of the flap or the aileron are designed, wherein the length of the gap at the flap of an airplane is 500mm, the gap is 50mm, the circumscribed radius of a unit cell structure required by exposure prevention is not more than 5mm, the thickness of the grid area with negative poisson ratio is 1mm, and the specific parameters of the deformable flexible grid with negative poisson ratio for the gap of the flap or the aileron designed according to the exposure prevention and related requirements are as follows:
a) the total length of the whole structure formed by the first area 1, the second area 2 and the third area 1 is 500mm, the width of the negative poisson ratio grating area is 50mm, the widths of the first area 1 and the third area 1 are both 30mm, the thickness of the second area 2 is 1mm, and the thicknesses of the first connecting area of the first area 1 and the third connecting area of the third area 1 are both 3 mm;
b) the diameter of a bolt hole connected with the wing and the flap is 6mm, and the outer diameter D of the connecting part is 15 mm;
c) the chamfer R of the unit cell structure is 0.5mm, and the thickness t1 of each side of the unit cell structure is 0.32 mm;
d) unit cell structure size of negative poisson ratio grating region: r 5mm, L1 6.65mm, L2 4.36mm, and L3 1.09 mm.
According to the negative Poisson ratio deformable flexible grid for the gaps of the flaps or the ailerons, when the angles of the flaps or the ailerons are changed, the negative Poisson ratio deformable flexible grid can be always connected with the wings and the flaps or the ailerons, the gaps are always covered by the grid in the deformation process, and the grid unit cell structure shape before deformation and after deformation always has good exposure prevention performance. And, due to the maturity of the 3D printing technology at present, the production cost of this kind of grid is extremely low, and is light, and is extremely suitable for using on the anti-riot aircraft.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A negative poisson's ratio deformable flexible grid for a flap or aileron slot, comprising: a first region (1), a second region (2) and a third region (1) connected in this order, wherein,
the first area (1) is a wing connection area and is used for being connected with a wing;
the second area (2) is a negative Poisson ratio grid area, the second area comprises a plurality of unit cell structures which are regularly arranged, each unit cell structure is formed by two hollow isosceles trapezoids with butt-jointed short sides, the base angle of each isosceles trapezoid is 60 degrees, and the side edge L1, the long edge L2 and the short side L3 meet the following requirements:
wherein r is the radius of a circumscribed circle of the unit cell structure;
the third region (1) is a flap or aileron connection region for connection to a flap or aileron;
the length of the integral structure formed by the first region (1), the second region (2) and the third region (1) is consistent with the length of a flap or an aileron gap, and the width of the second region (2) is consistent with the width of the flap or the aileron gap.
2. The deformable flexible grid of negative poisson's ratio for a flap or aileron gap according to claim 1, characterised in that at the edge of one side of the first region (1) remote from the second region (2) there are connections, which are provided with bolt holes, and the first region (1) is connected to a wing by bolts.
3. The deformable flexible grid with negative poisson's ratio for flaps or aileron gaps according to claim 1, characterised in that a plurality of connecting parts are arranged at one side edge of the third area (1) far away from the second area (2), bolt holes are arranged on the connecting parts, and the third area (1) is connected with the flaps or ailerons through bolts.
4. A negative poisson's ratio deformable flexible grid for a flap or aileron gap according to claim 2 or 3, characterised in that the outer diameter D of the connecting part is 15mm, the diameter D of the bolt hole is 6mm, and the distance between two adjacent bolt holes is between 25mm and 45 mm.
5. The deformable flexible grid of negative poisson's ratio for slits in flaps or ailerons according to claim 1, characterised in that the first area (1) comprises a first transition zone connected to the second area (2) and a first connection zone connected to the wing, wherein the first transition zone is of a gradual thickness, increasing in thickness from the side of the second area (2) to the side of the first connection zone, the thickness of the first connection zone being of a constant value not less than 3 mm.
6. The deformable flexible grid of negative poisson's ratio for slits in flaps or ailerons according to claim 1, characterised in that said third zone (3) comprises a third transition zone connected to said second zone (2) and a third connection zone connected to a flap or aileron, wherein said third transition zone is of a gradual thickness, increasing from the side of said second zone (2) to the side of said third connection zone, the thickness of said third connection zone being of a constant value not less than 3 mm.
7. The negative poisson's ratio deformable flexible grid for flaps or aileron slots according to claim 1, characterized in that the second area (2) is shaped using a 3D printing process.
8. Negative poisson's ratio deformable flexible grid for flaps or aileron slots according to claim 1, characterised in that the second region (2) has its inner angle of unit cell structure chamfered.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210393789.6A CN114771805A (en) | 2022-04-14 | 2022-04-14 | Negative Poisson ratio deformable flexible grid for gaps of flaps or ailerons |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210393789.6A CN114771805A (en) | 2022-04-14 | 2022-04-14 | Negative Poisson ratio deformable flexible grid for gaps of flaps or ailerons |
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| Publication Number | Publication Date |
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| CN114771805A true CN114771805A (en) | 2022-07-22 |
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| CN202210393789.6A Pending CN114771805A (en) | 2022-04-14 | 2022-04-14 | Negative Poisson ratio deformable flexible grid for gaps of flaps or ailerons |
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| CN112922995A (en) * | 2019-12-06 | 2021-06-08 | 同济大学 | Composite energy absorption structure based on negative Poisson ratio structure |
| CN113148109A (en) * | 2021-03-26 | 2021-07-23 | 中国飞机强度研究所 | Intelligent lattice morphing wing of electric aircraft and design method |
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2022
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| US20100288887A1 (en) * | 2009-05-15 | 2010-11-18 | Simon John Parker | Hinge sealing element and an assembly including said element |
| US20150024160A1 (en) * | 2010-08-17 | 2015-01-22 | The Boeing Company | Composite Structures having Composite-to-Metal Joints and Method for Making the Same |
| EP2965985A1 (en) * | 2014-07-08 | 2016-01-13 | Swansea University | Morphable structure |
| CN105366034A (en) * | 2015-11-25 | 2016-03-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for shielding gap of unmanned aerial vehicle motion structure |
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