Unmanned aerial vehicle solar wing using flexible perovskite solar cell

Abstract

An unmanned aerial vehicle solar wing using a flexible perovskite solar cell, comprising: a wing structural member, and a plurality of skins bonded to the surface of the wing structural member. The skins each comprise a carbon fiber mesh bonded to the wing structural member, a polyimide thin film bonded to the carbon fiber mesh, and a flexible solar panel provided on the polyimide thin film; the polyimide thin film is bonded to the outer side wall of a connecting curved panel; and the flexible solar panel is bonded to the polyimide thin film.

Description

A drone solar wing for flexible perovskite solar cells Technical Field

[0001] This utility model belongs to the field of drone manufacturing, specifically relating to a drone solar wing for flexible perovskite solar cells. Background Technology

[0002] Currently, for traditional fuel-consuming drones, engine power is affected by the extremely thin air in the critical space. However, for drones with solar panels, the near-space environment has a minimal impact. Furthermore, traditional solar-powered drones often use monocrystalline silicon solar cells, which, due to their poor deformation resistance, are difficult to adapt to high-curvature airfoils. This necessitates a high aspect ratio structure design to obtain sufficient coverage area, resulting in inefficient utilization of the wing's leading edge area. This structural design targets flexible perovskite solar cells for fixed-wing drone solar wing substrates, offering higher deformation resistance. Flexible perovskite cells utilize organometal halide perovskite materials, which are not only inexpensive but also easy to manufacture and process. Compared to traditional silicon-based solar cells, perovskite materials offer significant advantages in raw material costs; secondly, perovskite solar cells have low production costs; and thirdly, their thinness and lightness make installation and use more convenient, allowing for easy attachment to various surfaces without placing excessive burden on existing structures.

[0003] Utility Model Content

[0004] To overcome the limitation of inefficient utilization of the area of ​​existing solar-powered drone wings due to the poor deformation resistance of the monocrystalline silicon solar cells used, this utility model provides the following technical solution:

[0005] A solar wing for a drone used with flexible perovskite solar cells includes: a wing structure and several skins bonded to the surface of the wing structure.

[0006] The wing structural component includes: a wing spars, a plurality of front ribs disposed on the front side of the wing spars, and a plurality of rear ribs disposed on the rear side of the wing spars; a flap is also disposed on the front side of the front ribs, and a connecting curved plate is disposed on the rear side of the rear ribs.

[0007] The skin includes a carbon fiber mesh bonded to the wing structure, a polyimide film bonded to the carbon fiber mesh, and a flexible solar panel disposed on the polyimide film.

[0008] A polyimide film is adhered to the outer wall of the connecting curved plate, and a flexible solar panel is adhered to the polyimide film.

[0009] Furthermore, the wing beam is a hollow profile, and the front rib and the rear rib are bonded to the surfaces of the long sides of the front and rear sides of the wing beam. The left side of the wing beam is the male end, and the right side is the female end. The male end and the female end are used for plug-in connection between the wing beams.

[0010] Furthermore, the front rib includes a wide end of the front rib bonded to the wing spar and a narrow end of the front rib bonded to the flap. Both the upper and lower end faces of the front rib are curved surfaces, and the radius of curvature of the upper end face is smaller than the radius of curvature of the lower end face.

[0011] Furthermore, the rear rib includes a wide end of the rear rib bonded to the wing beam and a narrow end of the rear rib bonded to the connecting curved plate. Both the upper and lower end faces of the rear rib are also curved surfaces, and the radius of curvature of the upper end face is smaller than the radius of curvature of the lower end face.

[0012] Furthermore, the length of the front rib is greater than the length of the rear rib, and the radius of curvature of the upper surface of the front rib is greater than the radius of curvature of the upper surface of the rear rib; both the front and rear ribs are hollowed out to reduce the weight of the overall wing.

[0013] Furthermore, the flap protrudes to form several insertion parts on one side near the front rib, and insertion slots are provided on the insertion parts corresponding to the narrow end of the front rib. The narrow end of the front rib and the insertion slots are matched and fixed by adhesive.

[0014] Furthermore, the inner wall of the connecting curved plate is bonded to the narrow end of the rear rib plate with an adhesive. The upper end face of the rear rib plate is provided with an upper support fixing groove, and the lower end face is provided with a lower support fixing groove. The upper support fixing groove and the lower support fixing groove are used to fix the support and ensure the overall stability of the wing structure.

[0015] Furthermore, the carbon fiber mesh can be divided into a first carbon fiber mesh bonded to the upper end face of the front rib, a second carbon fiber mesh bonded to the lower end face of the front rib, a third carbon fiber mesh bonded to the upper end face of the rear rib, and a fourth carbon fiber mesh bonded to the lower end face of the rear rib.

[0016] The front long side of the first carbon fiber mesh is bonded to the upper surface of the flap, and the rear long side is bonded to the upper surface of the spar.

[0017] The front long side of the second carbon fiber mesh is bonded to the lower surface of the flap, and the rear long side is bonded to the lower surface of the spar.

[0018] The front long side of the third carbon fiber mesh is bonded to the upper surface of the wing beam, and the rear long side is bonded to the front outer edge of the upper support fixing groove.

[0019] The front long side of the fourth carbon fiber mesh is bonded to the lower surface of the wing beam, and the rear long side is bonded to the front outer edge of the fixing groove of the lower support member.

[0020] Furthermore, the flexible solar panel is a perovskite solar panel.

[0021] 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, in particular, possess excellent flexibility, allowing them to be bent, folded, and even rolled, making them easier to bond to the carbon fiber mesh + polyimide film skin surface. This flexibility not only improves the ease of battery installation and helps optimize the aerodynamic performance of the drone, but also effectively utilizes the high curvature of the wing to power the drone. Attached Figure Description

[0022] Figure 1 is a schematic diagram of the overall structure of the solar wing of a drone for flexible perovskite solar cells according to this utility model.

[0023] Figure 2 is an exploded structural diagram of the wing structure of the solar wing of a drone for flexible perovskite solar cells according to this utility model.

[0024] Figure 3 is a cross-sectional schematic diagram of the skin in the solar wing of a drone for use with flexible perovskite solar cells, according to this utility model.

[0025] Figure 4 is an assembly diagram of the skin and wing structure of the solar wing of a UAV for flexible perovskite solar cells according to this utility model.

[0026] In the diagram: 1-wing structure, 2-skin; 11-flaps, 12-front rib, 13-spar, 14-rear rib, 15-connecting curved plate; 21-carbon fiber mesh, 22-polyimide film, 23-flexible solar panel; 131-male end, 132-female end, 122-wide end of front rib, 121-narrow end of front rib; 141-wide end of rear rib, 142-narrow end of rear rib, 111-plug-in part, 111a-plug-in groove; 143-upper support fixing groove, 144-lower support fixing groove, 211-first carbon fiber mesh; 212-second carbon fiber mesh, 213-third carbon fiber mesh, 214-fourth carbon fiber mesh. Detailed Implementation

[0027] The technical solution of this utility model will be clearly and completely described below with reference to the accompanying drawings and specific embodiments. It should be understood that the described embodiments are only used to illustrate this utility model and are not intended to limit the scope of this utility model.

[0028] A solar wing for a drone used for flexible perovskite solar cells, as shown in Figure 1, includes: a wing structure 1 and several skins 2 bonded to the surface of the wing structure 1.

[0029] As shown in Figure 2, the wing structure 1 includes: a wing sparb 13, a plurality of front ribs 12 disposed on the front side of the wing sparb 13, and a plurality of rear ribs 14 disposed on the rear side of the wing sparb 11; a flap 11 is also disposed on the front side of the front ribs 12, and a connecting curved plate 15 is disposed on the rear side of the rear ribs 14.

[0030] As shown in Figure 3, the skin 2 includes a carbon fiber mesh 21 bonded to the wing structure 1, a polyimide film 22 bonded to the carbon fiber mesh 21, and a flexible solar panel 23 disposed on the polyimide film 22.

[0031] A polyimide film 22 is adhered to the outer wall of the connecting curved plate 15, and a flexible solar panel 23 (not shown in the figure) is adhered to the polyimide film 22.

[0032] In some embodiments of this utility model, the flexible solar panel 23 is a perovskite solar panel.

[0033] In some embodiments of this utility model, referring back to Figure 2, the wing beam 11 is a hollow profile, the front rib plate 12 and the rear rib plate 14 are bonded to the surfaces of the long sides of the front and rear sides of the wing beam 13, the left side of the wing beam 13 is the male end 131 and the right side is the female end 132, the male end 131 and the female end 132 are used for the plug-in connection between the wing beams.

[0034] In some embodiments of this utility model, the front rib plate 12 includes a wide end 122 of the front rib plate bonded to the wing beam 13 and a narrow end 121 of the front rib plate bonded to the flap 11. The upper and lower end surfaces of the front rib plate 12 are both curved surfaces, and the radius of curvature of its upper end surface is smaller than the radius of curvature of its lower end surface.

[0035] In some embodiments of this utility model, the rear rib plate 14 includes a wide end 141 of the rear rib plate bonded to the wing beam 13 and a narrow end 142 of the rear rib plate bonded to the connecting curved plate 15. The upper and lower end faces of the rear rib plate 14 are also curved surfaces, and the radius of curvature of its upper end face is smaller than the radius of curvature of its lower end face.

[0036] In some embodiments of this utility model, the length of the front rib plate 12 is greater than the length of the rear rib plate 14, and the radius of curvature of the upper surface of the front rib plate 12 is greater than the radius of curvature of the upper surface of the rear rib plate 14.

[0037] In some embodiments of this utility model, the front rib plate 12 and the rear rib plate 14 are both hollowed out to reduce the weight of the overall wing.

[0038] In some embodiments of this utility model, the flap 11 protrudes on one side near the front rib to form several insertion portions 111. The insertion portions 111 are provided with insertion grooves 111a corresponding to the narrow end 121 of the front rib. The narrow end 121 of the front rib and the insertion grooves 111a are correspondingly matched and fixed by adhesive.

[0039] In some embodiments of this utility model, the inner sidewall of the connecting curved plate 15 is bonded to the narrow end 142 of the rear rib plate by an adhesive. The upper end face of the rear rib plate 14 is provided with an upper support fixing groove 143, and the lower end face is provided with a lower support fixing groove 144. The upper support fixing groove 143 and the lower support fixing groove 144 are used to fix the support (not shown in the figure) to ensure the overall stability of the wing structure.

[0040] In some embodiments of this utility model, the grid in the carbon fiber mesh 21 is a two-way square grid.

[0041] Preferably, the mesh in the carbon fiber mesh 21 is a three-dimensional triangular mesh.

[0042] In some embodiments of this utility model, in conjunction with Figures 2 and 4, the carbon fiber mesh 21 can be divided into a first carbon fiber mesh 211 bonded to the upper end face of the front rib 12, a second carbon fiber mesh 212 bonded to the lower end face of the front rib 12, a third carbon fiber mesh 213 bonded to the upper end face of the rear rib 14, and a fourth carbon fiber mesh 214 bonded to the lower end face of the rear rib 14.

[0043] The front long side of the first carbon fiber mesh 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;

[0044] The front long side of the second carbon fiber mesh 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.

[0045] The front long side of the third carbon fiber mesh 213 is bonded to the upper surface of the wing beam 13, and the rear long side is bonded to the front outer edge of the upper support fixing groove 143.

[0046] The front long side of the fourth carbon fiber mesh 214 is bonded to the lower surface of the wing beam 13, and the rear long side is bonded to the front outer edge of the lower support fixing groove 144.

[0047] In some embodiments of this utility model, the adhesive is structural adhesive J133.

[0048] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model in any way. Any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present utility model shall fall within the scope of the technical solution of the present utility model.

Claims

1. A drone solar wing for flexible perovskite solar cells, characterized in that, include: Wing structural components and several skins bonded to the surface of the wing structural components; The wing structural component includes: a wing spars, a plurality of front ribs disposed on the front side of the wing spars, and a plurality of rear ribs disposed on the rear side of the wing spars; a flap is also disposed on the front side of the front ribs, and a connecting curved plate is disposed on the rear side of the rear ribs. The skin includes a carbon fiber mesh bonded to the wing structure, a polyimide film bonded to the carbon fiber mesh, and a flexible solar panel disposed on the polyimide film. A polyimide film is adhered to the outer wall of the connecting curved plate, and a flexible solar panel is adhered to the polyimide film.

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

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

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

5. The drone solar wing for flexible perovskite solar cells according to claim 4, characterized in that, The length of the front rib is greater than the length of the rear rib, and the radius of curvature of the upper surface of the front rib is greater than the radius of curvature of the upper surface of the rear rib; both the front and rear ribs are hollowed out to reduce the weight of the overall wing. 6.The UAV solar wing for flexible perovskite solar cell according to claim 1, wherein, The flap has a protrusion on one side near the front rib to form several insertion parts. The insertion parts are provided with insertion grooves corresponding to the narrow end of the front rib. The narrow end of the front rib and the insertion grooves are matched and fixed by adhesive.

7. The drone solar wing for flexible perovskite solar cells of claim 4, wherein, The inner wall of the connecting curved plate is bonded to the narrow end of the rear rib plate with an adhesive. The upper end face of the rear rib plate is provided with an upper support fixing groove, and the lower end face is provided with a lower support fixing groove. The upper support fixing groove and the lower support fixing groove are used to fix the support and ensure the overall stability of the wing structure.

8. The drone solar wing for flexible perovskite solar cells of claim 1, wherein, The carbon fiber mesh can be divided into a first carbon fiber mesh bonded to the upper end face of the front rib, a second carbon fiber mesh bonded to the lower end face of the front rib, a third carbon fiber mesh bonded to the upper end face of the rear rib, and a fourth carbon fiber mesh bonded to the lower end face of the rear rib. The front long side of the first carbon fiber mesh 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 mesh 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 mesh is bonded to the upper surface of the wing beam, and the rear long side is bonded to the front outer edge of the upper support fixing groove. The front long side of the fourth carbon fiber mesh is bonded to the lower surface of the wing beam, and the rear long side is bonded to the front outer edge of the fixing groove of the lower support member. 9.The UAV solar wing for flexible perovskite solar cell according to claim 1, wherein, The flexible solar panel is a perovskite solar panel.

Images