Solar unmanned aerial vehicle double-sided power generation wing structure

Abstract

The utility model provides a solar unmanned aerial vehicle double-sided power generation wing structure, which belongs to the technical field of unmanned aerial vehicles, and comprises a wing, a double-sided solar cell module and a lower skin, the interior of the wing is of a hollow structure, the wing comprises a front edge, a main beam, a wing rib, a support cross bar and a rear edge, a bonding area of the double-sided solar cell module is arranged on the rear edge, and the double-sided solar cell module is fixedly mounted between the rear edge and the front edge; the plurality of groups of wing ribs are distributed at equal intervals, are fixedly connected with the main beam and are used for being matched with the main beam to ensure the structural strength of the wing and reduce the weight; the front edge and the rear edge are respectively arranged at the front end and the rear end of the wing rib and are fixedly connected with the wing rib; according to the utility model, the problem of low power generation efficiency of a single-surface solar cell can be solved, and the power generation efficiency is improved on an unmanned aerial vehicle on which solar cell modules with the same area are laid.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, and specifically relates to a solar-powered UAV with a dual-sided generator wing structure. Background Technology

[0002] In today's era of rapid technological advancement, unmanned aerial vehicle (UAV) technology has demonstrated enormous application potential in numerous fields, especially solar-powered UAVs. With their sustainable energy acquisition methods and unique flight performance, they are gradually emerging and gaining widespread attention and application in both military and civilian sectors, such as meteorological monitoring and communication platforms. In the field of meteorological monitoring, solar-powered UAVs can cruise over specific airspaces for extended periods, accurately collecting various meteorological data, such as changes in atmospheric temperature, humidity, air pressure, and wind speed and direction. This provides more detailed and real-time data support for weather forecasts, significantly improving the accuracy and timeliness of forecasts. In terms of communication platforms, solar-powered UAVs can serve as high-altitude relay stations, effectively expanding communication coverage and ensuring uninterrupted communication in remote areas or during special circumstances such as natural disasters. They play an irreplaceable role in both military command and control and civilian emergency communication support.

[0003] Because solar-powered drones have limited payload capacity, traditional single-sided photovoltaic panels have low power generation efficiency for the same area, making it difficult to meet the energy requirements for drone flight, mission execution, and equipment operation. At the same time, increasing the area of ​​solar cells to improve power generation efficiency will inevitably bring a heavy load, further reducing the effective payload space that drones can use to carry mission equipment or energy storage devices. Therefore, a lightweight and more efficient solar-powered drone wing structure is needed. Utility Model Content

[0004] In view of this, the present invention provides a double-sided generator wing structure for solar-powered drones, which can solve the problem of low power generation efficiency of single-sided solar cells and improve power generation efficiency on drones with solar cell modules of the same area.

[0005] This utility model is implemented as follows:

[0006] This utility model provides a solar-powered unmanned aerial vehicle (UAV) dual-sided generator wing structure, which includes a wing, dual-sided solar cell modules and a lower skin. The interior of the wing is a hollow structure. The wing includes a leading edge, a main beam, wing ribs, supporting crossbars and a trailing edge. The trailing edge is provided with an adhesive area for the dual-sided solar cell modules. The dual-sided solar cell modules are fixedly installed between the trailing edge and the leading edge.

[0007] The technical effects of the dual-sided generator wing structure for a solar-powered drone provided by this utility model are as follows: By designing a hollow structure for the wing through the main beam and wing ribs, and by setting up dual-sided solar cell modules, dual-sided power generation can be achieved by combining the curved surface of the wing. Power generation is further improved by utilizing reflected light from clouds and other sources through the bottom surface and the lower skin.

[0008] Based on the above technical solution, the solar-powered unmanned aerial vehicle (UAV) double-sided generator wing structure of this utility model can be further improved as follows:

[0009] The wing ribs are in multiple sets, evenly spaced and fixedly connected to the main beam, which work together with the main beam to ensure the structural strength of the wing and reduce its weight.

[0010] The beneficial effects of adopting the above-mentioned improvement scheme are: by setting ribs to construct a hollow structure, the internal weight of the wing is reduced.

[0011] Furthermore, the leading edge and the trailing edge are respectively disposed at the front and rear ends of the rib and are fixedly connected to the rib.

[0012] The beneficial effects of adopting the above-mentioned improvement scheme are as follows: by setting the leading edge, the aerodynamic effect is guaranteed on the basis of ensuring strength and rigidity; by setting the trailing edge, the support strength is provided and the bonding area is provided for the bifacial solar cell module is provided.

[0013] Furthermore, the supporting crossbar is fixedly connected to multiple sets of wing ribs to maintain the shape of the bifacial solar cell module.

[0014] Furthermore, the bifacial solar cell module is a bifacial solar panel, the back end of which can generate electricity using light reflected from the ground, clouds, etc.

[0015] Furthermore, the lower skin is made of a transparent film with tensile strength, and the lower skin is fixedly connected to the bottom of the leading edge, the wing rib, and the trailing edge.

[0016] The beneficial effects of adopting the above-mentioned improvement scheme are: by setting a transparent lower skin, it is beneficial to reflect sunlight.

[0017] Furthermore, the lower substrate of the bifacial solar cell module adopts a light-transmitting PMI foam layer, which works in conjunction with the lower skin to reflect light intensity onto the back of the bifacial solar cell module, thereby improving the luminous efficiency of the bifacial solar cell module.

[0018] Furthermore, the ribs are provided with multiple sets of irregularly shaped through holes to facilitate cable routing.

[0019] Furthermore, the wing is fixedly connected to the fuselage structure via the main beam.

[0020] Furthermore, the wing rib is provided with a slot adapted to the main beam, and the wing rib is fixedly connected to the main beam through the slot.

[0021] Compared with existing technologies, the beneficial effects of the bifacial generator wing structure for solar-powered drones provided by this utility model are as follows: The wing is designed with a hollow structure through the main beam and wing ribs; bifacial solar cell modules can be integrated with the curved surface of the wing to achieve bifacial power generation; the bottom surface, in conjunction with the lower skin, utilizes reflected light from clouds to generate electricity, further improving power generation efficiency; the wing ribs are used to construct the hollow structure, reducing the internal weight of the wing; the leading edge ensures aerodynamic performance while maintaining strength and rigidity; the trailing edge provides support strength and an bonding area for the bifacial solar cell modules; the transparent lower skin allows for sunlight reflection, and the filling with a translucent PMI foam layer further improves the back-side luminous efficiency of the bifacial solar cell modules. Attached Figure Description

[0022] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments of this utility model will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of a double-sided generator wing structure for a solar-powered unmanned aerial vehicle (UAV).

[0024] Figure 2 This is a schematic diagram of the internal structure of a dual-sided generator wing for a solar-powered unmanned aerial vehicle.

[0025] Figure 3 This is a diagram illustrating the principle of sunlight illumination.

[0026] The attached diagram lists the components represented by each number as follows:

[0027] 10. Wing; 101. Leading edge; 102. Main spars; 103. Wing ribs; 104. Support crossbars; 105. Trailing edge; 11. Bifacial solar panel; 12. Lower skin; 13. Through-hole; 14. PMI foam layer. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings.

[0029] like Figure 1-3 The image shows an embodiment of a solar-powered drone dual-sided generator wing structure provided by this utility model. In this embodiment, it includes a wing 10, a dual-sided solar cell module 11, and a lower skin 12. The interior of the wing 10 has a hollow structure. The wing 10 includes a leading edge 101, a main beam 102, a wing rib 103, a support crossbar 104, and a trailing edge 105. The trailing edge 105 is provided with an adhesive area for the dual-sided solar cell module 11. The dual-sided solar cell module 11 is fixedly installed between the trailing edge 105 and the leading edge 101.

[0030] In the above technical solution, the wing ribs 103 are in multiple sets, distributed at equal intervals and fixedly connected to the main beam 102, which are used to cooperate with the main beam 102 to ensure the structural strength of the wing and reduce the weight.

[0031] Furthermore, in the above technical solution, the leading edge 101 and the trailing edge 105 are respectively disposed at the front and rear ends of the wing rib 103 and are fixedly connected to the wing rib 103.

[0032] Furthermore, in the above technical solution, the support bar 104 is fixedly connected to multiple sets of ribs 103 to maintain the shape of the bifacial solar cell module 11.

[0033] Furthermore, in the above technical solution, the bifacial solar cell module 11 is a bifacial solar panel, and its back end can generate electricity using light reflected from the ground, clouds, etc.

[0034] Furthermore, in the above technical solution, the lower skin 12 is made of a transparent film with tensile strength, and the lower skin 12 is fixedly connected to the bottom of the leading edge 101, the wing rib 103 and the trailing edge 105.

[0035] The lower skin 12 can be made of PC or PET materials.

[0036] Furthermore, in the above technical solution, the lower substrate of the bifacial solar cell module 11 adopts a light-transmitting PMI foam layer 14, which is used in conjunction with the lower skin 12 to allow the reflected light intensity to irradiate the back of the bifacial solar cell module 11, thereby improving the luminous efficiency of the bifacial solar cell module 11.

[0037] Furthermore, in the above technical solution, multiple sets of irregularly shaped through holes 13 are provided on the rib 103 to facilitate wiring.

[0038] Furthermore, in the above technical solution, the wing 10 is fixedly connected to the fuselage structure via the main beam 102.

[0039] Furthermore, in the above technical solution, the wing rib 103 is provided with a slot adapted to the main beam 102, and the wing rib 103 is fixedly connected to the main beam 102 through the slot.

[0040] Specifically, the principle of this invention is as follows: it mainly consists of a wing, a bifacial solar cell module, and a lower skin. The wing structure adopts a hollow design, allowing the bifacial solar cell module to generate electricity from both sides. The lower substrate of the bifacial solar cell module uses PMI foam with good light transmittance. The bifacial solar cell module is bonded to the edge of the wing structure with epoxy adhesive. The lower skin is made of a transparent and tensile-resistant film, which facilitates sunlight reflection and transmission, thereby improving the back-side power generation efficiency of the bifacial solar cell module.

Claims

1. A solar-powered drone dual-sided power generator wing structure, characterized in that, The aircraft includes a wing (10), a bifacial solar cell module (11), and a lower skin (12). The interior of the wing (10) is a hollow structure. The wing (10) includes a leading edge (101), a main beam (102), a wing rib (103), a support crossbar (104), and a trailing edge (105). The trailing edge (105) is provided with an adhesive area for the bifacial solar cell module (11). The bifacial solar cell module (11) is fixedly installed between the trailing edge (105) and the leading edge (101).

2. The dual-sided solar-powered UAV wing structure of claim 1, wherein, The wing ribs (103) are in multiple sets, evenly spaced and fixedly connected to the main beam (102), used to cooperate with the main beam (102) to ensure the structural strength of the wing and reduce weight.

3. The dual-sided solar-powered UAV wing structure of claim 2, wherein, The leading edge (101) and the trailing edge (105) are respectively disposed at the front and rear ends of the wing rib (103) and are fixedly connected to the wing rib (103).

4. The dual-sided solar-powered UAV wing structure of claim 3, wherein, The support bar (104) is fixedly connected to multiple sets of the ribs (103) to maintain the shape of the bifacial solar cell module (11).

5. The dual-sided solar-powered UAV wing structure of claim 4, wherein, The bifacial solar cell module (11) is a bifacial solar panel, and its back end can generate electricity using light reflected from the ground and clouds.

6. The dual-sided solar-powered UAV wing structure of claim 5, wherein, The lower skin (12) is made of a transparent film with tensile strength, and the lower skin (12) is fixedly connected to the bottom of the leading edge (101), the wing rib (103) and the trailing edge (105).

7. The dual-sided solar-powered UAV wing structure of claim 6, wherein, The lower substrate of the bifacial solar cell module (11) is made of a light-transmitting PMI foam layer (14), which works in conjunction with the lower skin (12) to reflect light onto the back of the bifacial solar cell module (11) and improve the luminous efficiency of the bifacial solar cell module (11).

8. The dual-sided solar-powered UAV wing structure of claim 7, wherein, The rib (103) has multiple sets of irregularly shaped through holes (13) for easy wiring.

9. The dual-sided solar-powered UAV wing structure of claim 8, wherein, The wing (10) is fixedly connected to the fuselage structure via the main beam (102).

10. The dual-sided solar-powered UAV wing structure of claim 9, wherein, The wing rib (103) is provided with a slot adapted to the main beam (102), and the wing rib (103) is fixedly connected to the main beam (102) through the slot.

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