CN210479007U - Light wing of small unmanned aerial vehicle - Google Patents
Light wing of small unmanned aerial vehicle Download PDFInfo
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- CN210479007U CN210479007U CN201920998693.6U CN201920998693U CN210479007U CN 210479007 U CN210479007 U CN 210479007U CN 201920998693 U CN201920998693 U CN 201920998693U CN 210479007 U CN210479007 U CN 210479007U
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Abstract
The utility model discloses a light-duty wing of small-size unmanned aerial vehicle, the wing includes the covering, wing spar and wing rib, the wing spar includes the front beam, well roof beam and back beam all include web and perpendicular to web and are located the flange of web both ends, web and flange all have multilayer axisymmetric combined material to spread the layer, the cross section all is the I font, and for variable cross section ladder beam, its material is carbon fiber and epoxy, on following the wing axial direction, the cross sectional shape of wing spar is the same, the thickness of wing spar diminishes gradually, the covering includes first panel, the light sandwich layer between second panel and the two panels, first panel is the fine cloth of carbon, the second panel is multilayer combined material to spread the layer, its material is carbon fiber and epoxy. Wing spar and covering adopt combined material, and the wing spar is laid for variable cross section roof beam and combined material axial symmetry simultaneously, and the intensity of wing increases, the deformation rate reduces, stress distribution is more even, has lightweight, high rigidity, improves unmanned aerial vehicle high specific strength, high specific modulus.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle field, in particular to light-duty wing of unmanned aerial vehicle.
Background
As a hotspot in the development of the international aviation field, the unmanned aircraft can meet the requirements of low cost, long endurance, large overload and high maneuverability only by reducing the structural weight as much as possible. The wing has born the approximate aerodynamic load of unmanned aerial vehicle as unmanned aerial vehicle owner load structure, is main lift part, and its structural performance plays decisive effect to whole unmanned aerial vehicle's flight performance. Therefore, under the condition of ensuring the structural strength, the wing structure with the characteristics of light weight and high rigidity is a key element for improving various performances of the unmanned aerial vehicle.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to provide a light-duty wing of unmanned aerial vehicle, the wing spar and the covering of wing adopt combined material for the wing has high than excellent characteristics such as intensity, high ratio modulus, mechanical properties designability, easily whole shaping processing and stealthy.
In order to solve the technical problem, the utility model discloses a technical scheme does:
a light wing of a small unmanned aerial vehicle comprises a skin, wing spars and wing ribs, wherein the wing spars comprise a front beam, a middle beam and a rear beam, the cross sections of the front beam, the middle beam and the rear beam are all in an I shape, the front beam, the middle beam and the rear beam respectively comprise a web plate and edge strips which are perpendicular to the web plate and are positioned at the two ends of the web plate, the web plate and the edge strip are respectively provided with a plurality of layers of axisymmetric composite material layers, the front beam, the middle beam and the rear beam are stepped beams with variable cross sections, the section shapes of the wing spars are the same along the axial direction of the wing, the thickness of the wing spars is gradually reduced, the front beam, the middle beam and the rear beam are made of carbon fiber and epoxy resin, the skin comprises a first panel, a second panel and a light core layer glued between the two panels, the first panel is a wing surface layer, the first panel is carbon fiber cloth, the second panel is a multilayer composite material laying layer, and the second panel is made of carbon fibers and epoxy resin.
Preferably, the front beam, the middle beam and the rear beam are made of T700 carbon fiber and epoxy resin.
Preferably, the thickness of the single-layer T700 carbon fiber and epoxy resin composite material is 0.15 mm.
Preferably, the carbon fiber cloth is formed by interweaving longitudinal fibers and transverse fibers.
Preferably, the thickness ratio of the first panel, the second panel and the lightweight core layer is 1: 10: 12.
preferably, the lightweight core layer is a honeycomb core layer.
The utility model relates to a light wing of a small unmanned aerial vehicle, the wing comprises a covering, a wing beam and a wing rib, the wing beam comprises a front beam, a middle beam and a back beam, the cross sections of the front beam, the middle beam and the rear beam are all in an I shape, the front beam, the middle beam and the rear beam respectively comprise a web plate and edge strips which are parallel to the web plate and are positioned at the two ends of the web plate, the web plate and the edge strip are respectively provided with a plurality of layers of axisymmetric composite material layers, the front beam, the middle beam and the rear beam are stepped beams with variable cross sections, the section shapes of the wing spars are the same along the axial direction of the wing, the thickness of the wing spars is gradually reduced, the front beam, the middle beam and the rear beam are made of carbon fiber and epoxy resin, the skin comprises a first panel, a second panel and a light core layer glued between the two panels, the first panel is a wing surface layer, the first panel is carbon fiber cloth, the second panel is a multilayer composite material laying layer, and the second panel is made of carbon fibers and epoxy resin. The utility model discloses a wing spar and covering in the wing adopt combined material, and the wing spar is laid for variable cross-section roof beam and combined material axial symmetry simultaneously, and the intensity of wing increases, the deformation rate reduces, the stress distribution of wing is more even, has characteristics such as lightweight, high rigidity, improves unmanned aerial vehicle high specific strength, high specific modulus, the easy whole contour machining of unmanned aerial vehicle wing.
Drawings
Fig. 1 is a schematic structural view of a light wing of the small unmanned aerial vehicle;
FIG. 2 is the utility model discloses the plan view of the light-duty wing of unmanned aerial vehicle
Fig. 3 is a schematic cross-sectional view of a light wing of the small unmanned aerial vehicle of the present invention;
fig. 4 is a schematic structural view of a wing beam in a light wing of the small unmanned aerial vehicle;
FIG. 5 is a schematic view of the layering mode of the cross section of the wing beam in the light-weight wing of the small unmanned aerial vehicle;
FIG. 6 is a schematic view of the layering mode of the wing spars in the light wing of the unmanned aerial vehicle;
fig. 7 is a schematic structural view of the skin in the light wing of the small unmanned aerial vehicle of the present invention;
fig. 8 is a schematic structural view of a light core layer in a light wing of the small unmanned aerial vehicle of the present invention;
in the figure, 1-skin, 11-first panel, 12-second panel, 13-light core layer, 14-adhesive layer, 2-wing beam, 21-front beam, 22-middle beam, 23-rear beam, 24-web, 25-edge strip and 3-wing rib.
Detailed Description
The following describes the present invention with reference to the accompanying drawings. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. In addition, the technical features related to the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
As shown in fig. 1 and 2, the light wing of the small unmanned aerial vehicle comprises a skin 1, a wing spar 2 and a wing rib 3, wherein the wing spar 2 comprises a front beam 21, a middle beam 22 and a rear beam 23, as shown in fig. 3, the cross sections of the front beam 21, the middle beam 22 and the rear beam 23 are all in an I shape, the front beam 21, the middle beam 22 and the rear beam 23 respectively comprise a web 24 and a flange 25 which is perpendicular to the web 24 and is positioned at two ends of the web 24, as shown in fig. 5, the web 24 and the flange 25 respectively have multiple layers of axisymmetric composite material layers, so that the strength is increased, the deformation rate is reduced, and the stress distribution of the wing is more uniform.
As shown in fig. 4 and 6, the front beam 21, the middle beam 22 and the rear beam 23 are variable-section stepped beams, the section shapes of the spars 2 are the same in the wing axial direction, the thicknesses of the spars 2 are gradually reduced, the front beam 21, the middle beam 22 and the rear beam 23 are made of carbon fibers and epoxy resin, the front beam 21, the middle beam 22 and the rear beam 23 are made of T700 carbon fiber and epoxy resin composite materials, the layer angle of the composite materials is generally 0 degree, 45 degrees, -45 degrees and 90 degrees, the layer thicknesses of the laminated plates are integral multiples of the thicknesses of single-layer materials, and the thicknesses of the single-layer materials are generally constant values. In the present embodiment, the thickness of the single-layer T700 carbon fiber and epoxy resin composite material is 0.15 mm.
As shown in fig. 7, the skin 1 includes a first panel 11, a second panel 12 and a light core layer 13 bonded between the two panels through an adhesive layer 14, the first panel 11 is a wing surface layer, the first panel 11 is a carbon fiber cloth, the second panel 12 is a multilayer composite material layer, and the second panel 12 is made of carbon fibers and epoxy resin. The carbon fiber cloth is formed by crosswise weaving longitudinal fibers and transverse fibers. The skin 1, the wing beams 2 and the wing ribs 3 form a plurality of closed wing box structures, the skin 1 is mainly used for resisting torsion in the closed wing boxes, in order to improve the torsional rigidity of the skin 1 and enable the skin 1 to have high damage tolerance performance and anti-spalling performance, a layer of carbon fiber cloth is attached to the outermost layer of the wing, and the carbon fiber cloth is formed by cross weaving of longitudinal fibers and transverse fibers. The thickness ratio of the first panel 11, the second panel 12 and the light core layer 13 is 1: 10: 12. the total thickness of the skin 1 is 7.3 mm, wherein the thickness of the light core layer 13 is 4 mm, the thickness of the surface carbon fiber cloth 11 is 0.3 mm, and the thickness of the second panel 12 is 3 mm.
As shown in fig. 8, the lightweight core layer 13 is a honeycomb core layer. The honeycomb core layer has the function of improving the bending rigidity of the sandwich structure and enabling the material to be far away from the neutral axis of the cross section. The honeycomb core layer is selected from nomex honeycombs.
The utility model discloses light-duty wing of small-size unmanned aerial vehicle, wing include covering 1, spar 2 and rib 3, spar 2 includes front-axle beam 21, centre sill 22 and back-axle beam 23, the cross section of front-axle beam 21, centre sill 22 and back-axle beam 23 all is the I font, front-axle beam 21, centre sill 22 and back-axle beam 23 all include web 24 and be on a parallel with web 24 and be located the flange 25 at web 24 both ends, web 24 and flange 25 all have multilayer axisymmetric composite material to lay the layer, front-axle beam 21, centre sill 22 and back-axle beam 23 are variable cross section ladder roof beam, and along the wing axial direction, the cross sectional shape of spar 2 is the same, and the thickness of spar 2 diminishes gradually, the material of front-axle beam 21, centre sill 22 and back-axle beam 23 is carbon fiber and epoxy, covering 1 includes first panel 11, second panel 12 and the light sandwich layer 13 of cementing between two panels, first panel 11 is the wing top layer, the first panel 11 is carbon fiber cloth, the second panel 12 is a multilayer composite material layer, and the second panel 12 is made of carbon fibers and epoxy resin. The utility model discloses a wing spar and covering in the wing adopt combined material, and the wing spar is laid for variable cross-section roof beam and combined material axial symmetry simultaneously, and the intensity of wing increases, the deformation rate reduces, the stress distribution of wing is more even, has characteristics such as lightweight, high rigidity, improves unmanned aerial vehicle high specific strength, high specific modulus, the easy whole contour machining of unmanned aerial vehicle wing.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. It will be apparent to those skilled in the art that various changes, modifications, substitutions and alterations can be made in the embodiments without departing from the principles and spirit of the invention, and the scope of the invention is to be accorded the full scope of the claims.
Claims (6)
1. The utility model provides a light-duty wing of unmanned aerial vehicle which characterized in that: the wing comprises a skin, a wing beam and a wing rib, the wing beam comprises a front beam, a middle beam and a rear beam, the cross sections of the front beam, the middle beam and the rear beam are all in an I shape, the front beam, the middle beam and the rear beam respectively comprise a web plate and edge strips which are perpendicular to the web plate and are positioned at the two ends of the web plate, the web plate and the edge strip are respectively provided with a plurality of layers of axisymmetric composite material layers, the front beam, the middle beam and the rear beam are stepped beams with variable cross sections, the section shapes of the wing spars are the same along the axial direction of the wing, the thickness of the wing spars is gradually reduced, the front beam, the middle beam and the rear beam are made of carbon fiber and epoxy resin, the skin comprises a first panel, a second panel and a light core layer glued between the two panels, the first panel is a wing surface layer, the first panel is carbon fiber cloth, the second panel is a multilayer composite material laying layer, and the second panel is made of carbon fibers and epoxy resin.
2. A light-weight wing of a drone according to claim 1, characterized in that: the front beam, the middle beam and the rear beam are made of T700 carbon fibers and epoxy resin.
3. A light-weight wing of a drone according to claim 2, characterized in that: the thickness of the single-layer T700 carbon fiber and epoxy resin composite material is 0.15 mm.
4. A light-weight wing of a drone according to claim 1, characterized in that: the carbon fiber cloth is formed by crosswise weaving longitudinal fibers and transverse fibers.
5. A light-weight wing of a drone according to claim 1, characterized in that: the thickness ratio of the first panel to the second panel to the lightweight core layer is 1: 10: 12.
6. a light-weight wing of a drone according to claim 1, characterized in that: the light core layer is a honeycomb core layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920998693.6U CN210479007U (en) | 2019-06-29 | 2019-06-29 | Light wing of small unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920998693.6U CN210479007U (en) | 2019-06-29 | 2019-06-29 | Light wing of small unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN210479007U true CN210479007U (en) | 2020-05-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920998693.6U Expired - Fee Related CN210479007U (en) | 2019-06-29 | 2019-06-29 | Light wing of small unmanned aerial vehicle |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112009667A (en) * | 2020-07-31 | 2020-12-01 | 彩虹无人机科技有限公司 | Low-magnetism magnetic detection special wing |
| CN113602477A (en) * | 2021-07-26 | 2021-11-05 | 成都飞机工业（集团）有限责任公司 | Full-composite empennage structure and forming method thereof |
| CN114572379A (en) * | 2022-03-25 | 2022-06-03 | 重庆交通大学 | Wing spar of small and medium-sized light unmanned aerial vehicle, control method and application |
| WO2023026662A1 (en) * | 2021-08-23 | 2023-03-02 | 三菱重工業株式会社 | Skin member and blade structure |
-
2019
- 2019-06-29 CN CN201920998693.6U patent/CN210479007U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112009667A (en) * | 2020-07-31 | 2020-12-01 | 彩虹无人机科技有限公司 | Low-magnetism magnetic detection special wing |
| CN113602477A (en) * | 2021-07-26 | 2021-11-05 | 成都飞机工业（集团）有限责任公司 | Full-composite empennage structure and forming method thereof |
| WO2023026662A1 (en) * | 2021-08-23 | 2023-03-02 | 三菱重工業株式会社 | Skin member and blade structure |
| CN114572379A (en) * | 2022-03-25 | 2022-06-03 | 重庆交通大学 | Wing spar of small and medium-sized light unmanned aerial vehicle, control method and application |
| CN114572379B (en) * | 2022-03-25 | 2024-03-26 | 重庆交通大学 | Wing spar of small and medium-sized light unmanned aerial vehicle, control method and application |
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| GR01 | Patent grant | ||
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| 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: 20200508 Termination date: 20210629 |