Unmanned aerial vehicle solar wing for flexible perovskite solar cell

Abstract

The utility model discloses an unmanned aerial vehicle solar wing for a flexible perovskite solar cell. The unmanned aerial vehicle solar wing comprises a wing structural member and a plurality of skins adhered to the surface of the wing structural member, the skin comprises a carbon fiber grid bonded with the wing structural member, a polyimide film bonded on the carbon fiber grid and a flexible solar cell panel arranged on the polyimide film; a polyimide film is bonded on the outer side wall of the connecting bent plate, and a flexible solar cell panel is bonded on the polyimide film. According to the structural design, the flexible perovskite solar cell has good flexibility and can be bent, folded and even curled, so that the flexible perovskite solar cell can be attached to the surface of the carbon fiber grid and polyimide film skin more easily. Due to the flexibility, the installation convenience of the battery is improved, the aerodynamic performance of the unmanned aerial vehicle is optimized, and the high-curvature parts on the wings are effectively utilized to supply power to the unmanned aerial vehicle.

Description

Technical Field

[0001] The utility model belongs to the field of unmanned aerial vehicle manufacturing, and specifically relates to a solar wing for an unmanned aerial vehicle used for flexible perovskite solar cells. Background Art

[0002] Currently, for traditional fuel-consuming drones, engine power is affected by the thin air in the critical space. However, for drones equipped with solar cells, near-space has minimal impact. Furthermore, traditional solar drones mostly use single-crystal silicon solar cells, but their poor deformation resistance makes them difficult to adapt to high-curvature airfoils. This requires a high-aspect-ratio structural design to ensure sufficient deployment area, resulting in inefficient utilization of the wing's leading edge. This structural design is specifically designed for flexible perovskite solar cells with high deformation resistance, specifically for fixed-wing drone solar wing substrates. Flexible perovskite cells utilize organometallic halide perovskite materials, which are not only low-cost but also easy to manufacture and process. Compared to traditional silicon-based solar cells, perovskite materials offer significant advantages in raw material costs. Furthermore, perovskite solar cells are low-cost to produce. They are also lightweight and thin, making installation and use more convenient, allowing for easy attachment to various surfaces without significantly impacting the existing structure. Utility Model Content

[0003] To overcome the problem that the wings of existing solar drones cannot be effectively utilized due to the poor deformation resistance of the monocrystalline silicon solar cells they use, the present invention provides the following technical solutions:

[0004] A solar wing for a drone using flexible perovskite solar cells, comprising: a wing structure and a plurality of skins bonded to the surface of the wing structure;

[0005] The wing structure comprises a spar, a plurality of front ribs arranged on the front side of the spar, and a plurality of rear ribs arranged on the rear side of the spar; a flap is further arranged on the front side of the front rib, and a connecting curved plate is arranged on the rear side of the rear rib;

[0006] The skin comprises a carbon fiber grid bonded to the wing structure, a polyimide film bonded to the carbon fiber grid, and a flexible solar cell panel disposed on the polyimide film;

[0007] A polyimide film is adhered to the outer side wall of the connecting curved plate, and a flexible solar cell panel is adhered to the polyimide film.

[0008] Furthermore, the wing spar is a hollow profile, and the front ribs and the rear ribs are bonded to the surfaces of the front and rear long sides of the wing spar. The left side of the wing spar is a male end, and the right side is a female end. The male end and the female end are used for plug-in connection between the wing spars.

[0009] Furthermore, the front rib includes a wide end bonded to the wing spar and a narrow end bonded to the flap. The upper and lower end surfaces of the front rib are both curved surfaces, and the curvature radius of the upper end surface is smaller than the curvature radius of the lower end surface.

[0010] Furthermore, the rear rib includes a wide end bonded to the wing spar and a narrow end bonded to the connecting curved plate. The upper and lower end surfaces of the rear rib are also curved surfaces, and the curvature radius of the upper end surface is smaller than the curvature radius of the lower end surface.

[0011] Furthermore, the length of the front rib is greater than that of the rear rib, and the curvature radius of the upper end surface of the front rib is greater than the curvature radius of the upper end surface of the rear rib; the front rib and the rear rib are both hollow designs to reduce the weight of the entire wing.

[0012] Furthermore, a plurality of plug-in parts are formed on one side of the flap near the front rib, and a plug-in groove is provided on the plug-in part corresponding to the narrow end of the front rib. The narrow end of the front rib corresponds to the plug-in groove and is fixed by adhesive.

[0013] Furthermore, the inner side wall of the connecting curved plate is bonded to the narrow end of the rear rib by adhesive, the upper end surface of the rear rib is provided with an upper support member fixing groove, and the lower end surface is provided with a lower support member fixing groove, and the upper support member fixing groove and the lower support member fixing groove are used to fix the support member to ensure the overall stability of the wing structure.

[0014] Furthermore, the carbon fiber mesh can be divided into a first carbon fiber mesh bonded to the upper end surface of the front rib, a second carbon fiber mesh bonded to the lower end surface of the front rib, a third carbon fiber mesh bonded to the upper end surface of the rear rib, and a fourth carbon fiber mesh bonded to the lower end surface of the rear rib.

[0015] The front long side of the first carbon fiber grid is bonded to the upper surface of the flap, and the rear long side is bonded to the upper surface of the spar;

[0016] The front long side of the second carbon fiber grid is bonded to the lower surface of the flap, and the rear long side is bonded to the lower surface of the spar;

[0017] The front long side of the third carbon fiber grid is bonded to the upper surface of the spar, and the rear long side is bonded to the front outer edge of the fixing groove of the upper support member;

[0018] The front long side of the fourth carbon fiber grid is bonded to the lower surface of the spar, and the rear long side is bonded to the front outer edge of the fixing groove of the lower support member.

[0019] Furthermore, the flexible solar cell panel is a perovskite solar cell panel.

[0020] This structural design is suitable for bonding flexible perovskite solar cells, flexible silicon-based solar cells, and flexible gallium arsenide cells. Flexible perovskite solar cells offer excellent flexibility and can be bent, folded, and even curled, making them easier to bond to the carbon fiber mesh and polyimide film skin. This flexibility not only improves battery installation convenience and helps optimize the drone's aerodynamic performance, but also effectively utilizes the high curvature of the wing to power the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the overall structure of the solar wing of a drone using flexible perovskite solar cells in the utility model.

[0022] Figure 2 This is a schematic diagram of the explosion structure of the wing structural parts in the solar wing of a drone using flexible perovskite solar cells in the utility model.

[0023] Figure 3 This is a cross-sectional schematic diagram of the middle skin of the solar wing of a drone using flexible perovskite solar cells according to the present invention.

[0024] Figure 4 This is an assembly diagram of the middle skin and wing structure of the solar wing of a UAV using flexible perovskite solar cells according to the present invention.

[0025] In the picture:

[0026] 1-wing structure, 2-skin;

[0027] 11- flap, 12- front rib, 13- spar, 14- rear rib, 15- connecting curved plate;

[0028] 21-carbon fiber mesh, 22-polyimide film, 23-flexible solar panel;

[0029] 131-male end, 132-female end, 122-wide end of front rib, 121-narrow end of front rib;

[0030] 141- wide end of rear rib, 142- narrow end of rear rib, 111- plug-in portion, 111a- plug-in slot;

[0031] 143 - upper support member fixing groove, 144 - lower support member fixing groove, 211 - first carbon fiber grid;

[0032] 212 - second carbon fiber grid, 213 - third carbon fiber grid, 214 - fourth carbon fiber grid. DETAILED DESCRIPTION

[0033] The following is a clear and complete description of the technical solution of the present invention with reference to specific embodiments in conjunction with the accompanying drawings. It should be understood that the embodiments described are only used to illustrate the present invention and are not used to limit the scope of the present invention.

[0034] A solar wing for a flexible perovskite solar cell drone, based on Figure 1 As shown, it comprises: a wing structure 1 and a plurality of skins 2 bonded to the surface of the wing structure 1;

[0035] according to Figure 2 As shown, the wing structure 1 includes: a spar 13, a plurality of front ribs 12 arranged on the front side of the spar 13, and a plurality of rear ribs 14 arranged on the rear side of the spar 11; the front side of the front rib 12 is further provided with a flap 11, and the rear side of the rear rib 14 is provided with a connecting curved plate 15;

[0036] according to Figure 3 As shown, the skin 2 includes a carbon fiber grid 21 bonded to the wing structure 1, a polyimide film 22 bonded to the carbon fiber grid 21, and a flexible solar cell panel 23 provided on the polyimide film 22;

[0037] A polyimide film 22 is bonded to the outer side wall of the connecting curved plate 15 , and a flexible solar cell panel 23 (not shown in the figure) is bonded to the polyimide film 22 .

[0038] In some embodiments of the present invention, the flexible solar cell panel 23 is a perovskite solar cell panel.

[0039] In some embodiments of the present invention, Figure 2 The spar 11 is a hollow profile, and the front ribs 12 and the rear ribs 14 are bonded to the surfaces of the front and rear long sides of the spar 13. The left side of the spar 13 is a male end 131, and the right side is a female end 132. The male end 131 and the female end 132 are used for plug-in connection between the spar.

[0040] In some embodiments of the present invention, the front rib 12 includes a front rib wide end 122 bonded to the wing spar 13 and a front rib narrow end 121 bonded to the flap 11. The upper and lower end surfaces of the front rib 12 are both curved surfaces, and the curvature radius of the upper end surface is smaller than the curvature radius of the lower end surface.

[0041] In some embodiments of the present invention, the rear rib 14 includes a rear rib wide end 141 bonded to the wing spar 13 and a rear rib narrow end 142 bonded to the connecting curved plate 15. The upper and lower end surfaces of the rear rib 14 are also curved surfaces, and the curvature radius of the upper end surface is smaller than the curvature radius of the lower end surface.

[0042] In some embodiments of the present invention, the length of the front rib 12 is greater than that of the rear rib 14 , and the curvature radius of the upper end surface of the front rib 12 is greater than the curvature radius of the upper end surface of the rear rib 14 .

[0043] In some embodiments of the present invention, the front ribs 12 and the rear ribs 14 are both hollowed out to reduce the weight of the entire wing.

[0044] In some embodiments of the present invention, the flap 11 is raised on one side near the front rib to form a plurality of plug-in portions 111, and a plug-in groove 111a is provided on the plug-in portion 111 corresponding to the narrow end 121 of the front rib. The narrow end 121 of the front rib corresponds to the plug-in groove 111a and is fixed by adhesive.

[0045] In some embodiments of the present invention, the inner side wall of the connecting curved plate 15 is bonded to the narrow end 142 of the rear rib by an adhesive, and the upper end surface of the rear rib 14 is provided with an upper support member fixing groove 143, and the lower end surface is provided with a lower support member fixing groove 144. The upper support member fixing groove 143 and the lower support member fixing groove 144 are used to fix the support member (not shown in the figure) to ensure the overall stability of the wing structure.

[0046] In some embodiments of the present invention, the grid in the carbon fiber grid 21 is in a bidirectional square grid shape.

[0047] Preferably, the grid in the carbon fiber grid 21 is in a three-dimensional triangular lattice shape.

[0048] In some embodiments of the present invention, Figure 2 and Figure 4 The carbon fiber mesh 21 can be divided into a first carbon fiber mesh 211 bonded to the upper end surface of the front rib 12, a second carbon fiber mesh 212 bonded to the lower end surface of the front rib 12, a third carbon fiber mesh 213 bonded to the upper end surface of the rear rib 14, and a fourth carbon fiber mesh 214 bonded to the lower end surface of the rear rib 14.

[0049] The front long side of the first carbon fiber grid 211 is bonded to the upper surface of the flap 11, and the rear long side is bonded to the upper surface of the spar 13;

[0050] The front long side of the second carbon fiber grid 212 is bonded to the lower surface of the flap 11, and the rear long side is bonded to the lower surface of the spar 13;

[0051] The front long side of the third carbon fiber grid 213 is bonded to the upper surface of the spar 13, and the rear long side is bonded to the front outer edge of the upper support member fixing groove 143;

[0052] The front long side of the fourth carbon fiber grid 214 is bonded to the lower surface of the spar 13 , and the rear long side is bonded to the front outer edge of the lower support member fixing groove 144 .

[0053] In some embodiments of the present invention, the adhesive is structural adhesive J133.

[0054] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention are within the scope of the technical solution of the present invention.

Claims

1. A solar wing for a drone using flexible perovskite solar cells, characterized in that: include: A wing structure and a plurality of skins bonded to the surface of the wing structure; The wing structure comprises a spar, a plurality of front ribs arranged on the front side of the spar, and a plurality of rear ribs arranged on the rear side of the spar; a flap is further arranged on the front side of the front rib, and a connecting curved plate is arranged on the rear side of the rear rib; The skin comprises a carbon fiber grid bonded to the wing structure, a polyimide film bonded to the carbon fiber grid, and a flexible solar cell panel disposed on the polyimide film; A polyimide film is adhered to the outer side wall of the connecting curved plate, and a flexible solar cell panel is adhered to the polyimide film.

2. The solar wing for a flexible perovskite solar cell drone according to claim 1, characterized in that: The wing spar is a hollow profile, and the front ribs and the rear ribs are bonded to the surfaces of the front and rear long sides of the wing spar. The left side of the wing spar is a male end, and the right side is a female end. The male end and the female end are used for plug-in connection between the wing spars.

3. The solar wing for a flexible perovskite solar cell drone according to claim 2, characterized in that: The front rib includes a front rib wide end bonded to the wing spar and a front rib narrow end bonded to the flap. The upper and lower end surfaces of the front rib are both curved surfaces, and the curvature radius of the upper end surface is smaller than the curvature radius of the lower end surface.

4. The solar wing for a flexible perovskite solar cell drone according to claim 3, characterized in that: The rear rib includes a wide end bonded to the wing spar and a narrow end bonded to the connecting curved plate. The upper and lower end surfaces of the rear rib are also curved surfaces, and the curvature radius of the upper end surface is smaller than the curvature radius of the lower end surface.

5. The solar wing for a flexible perovskite solar cell drone according to claim 4, characterized in that: The length of the front rib is greater than that of the rear rib, and the curvature radius of the upper end surface of the front rib is greater than the curvature radius of the upper end surface of the rear rib; the front rib and the rear rib are both hollow designs to reduce the weight of the entire wing.

6. The solar wing for a flexible perovskite solar cell drone according to claim 1, characterized in that: The flap is protruded on one side of the front rib to form a plurality of plug-in parts, and the plug-in parts are provided with plug-in grooves corresponding to the narrow ends of the front ribs. The narrow ends of the front ribs are matched with the plug-in grooves and are fixed by adhesive.

7. The solar wing for a flexible perovskite solar cell drone according to claim 4, characterized in that: The inner side wall of the connecting curved plate is bonded to the narrow end of the rear rib by adhesive. The upper end surface of the rear rib is provided with an upper support member fixing groove, and the lower end surface is provided with a lower support member fixing groove. The upper support member fixing groove and the lower support member fixing groove are used to fix the support member to ensure the overall stability of the wing structure.

8. The solar wing for a flexible perovskite solar cell drone according to claim 7, characterized in that: The carbon fiber mesh may be divided into a first carbon fiber mesh bonded to the upper end surface of the front rib, a second carbon fiber mesh bonded to the lower end surface of the front rib, a third carbon fiber mesh bonded to the upper end surface of the rear rib, and a fourth carbon fiber mesh bonded to the lower end surface of the rear rib. The front long side of the first carbon fiber grid is bonded to the upper surface of the flap, and the rear long side is bonded to the upper surface of the spar; The front long side of the second carbon fiber grid is bonded to the lower surface of the flap, and the rear long side is bonded to the lower surface of the spar; The front long side of the third carbon fiber grid is bonded to the upper surface of the spar, and the rear long side is bonded to the front outer edge of the fixing groove of the upper support member; The front long side of the fourth carbon fiber grid is bonded to the lower surface of the spar, and the rear long side is bonded to the front outer edge of the fixing groove of the lower support member.

9. The solar wing for a flexible perovskite solar cell drone according to claim 1, characterized in that: The flexible solar cell panel is a perovskite solar cell panel.

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