High-strength composite material photovoltaic fuselage skeleton of unmanned aerial vehicle

Abstract

The utility model provides a high-strength composite material unmanned aerial vehicle photovoltaic fuselage skeleton, which relates to the technical field of unmanned aerial vehicles, and comprises an upper plate skeleton, a lower plate skeleton arranged at the bottom of the upper plate skeleton, a side skeleton arranged between the upper plate skeleton and the lower plate skeleton, a connecting seat arranged on the side surface of the side skeleton, and a wing skeleton arranged at the port of the connecting seat, supporting rods are arranged at the bottom of the lower plate framework, supporting pads are arranged at the bottoms of the supporting rods, photovoltaic panels are arranged at the top of the upper plate framework and the top of the lower plate framework, and adjusting assemblies are arranged at the two ends of the upper plate framework and the two ends of the lower plate framework. The positioning sliding rods are adjusted through the needed structure, the reinforcing rods penetrate through the mounting plates to be fixed to the wing framework, the diagonal draw bars adjust and change the positions of the mounting plates through the second sliding grooves, the overall structure and the mounting position are adjusted at any time through the adjusting assemblies, and the aircraft can be matched with a fuselage frame and is convenient to adjust and mount.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a high-strength composite material UAV photovoltaic fuselage frame. Background Technology

[0002] According to Chinese Patent Publication No. CN108438216A, a drone frame and a drone are disclosed, relating to the technical field of drones. The drone frame includes a fuselage frame and multiple arms. Each arm includes a first end and a second end. The first end is used to fix a propeller mechanism, and the second end is movably connected to the circumferential side of the fuselage frame, allowing the distance between the second end and the fuselage frame to be adjustable. By moving the arm, the second end of the arm can be brought closer to the fuselage frame.

[0003] The aforementioned comparative documents and existing technologies have the following technical problems: The existing drone fuselage frame structure is the main component of current drone technology and the main internal auxiliary support component. However, the fuselage frame is mostly an integrated structure, and its frame is mostly made of lightweight materials such as carbon fiber and titanium alloy. These materials achieve a balance between high strength and low weight through composite processes, which directly affects the flight performance and safety of the drone. However, the integrated structure is too monotonous and directly determines the structure of the drone. Utility Model Content

[0004] The purpose of this invention is to address the shortcomings of existing technologies by proposing a high-strength composite material photovoltaic fuselage frame for unmanned aerial vehicles.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: a high-strength composite material photovoltaic fuselage frame for a drone, comprising an upper plate frame, a lower plate frame at the bottom of the upper plate frame, a side frame between the upper plate frame and the lower plate frame, a connecting seat on the side of the side frame, a wing frame at the port of the connecting seat, a support rod at the bottom of the lower plate frame, and a support pad at the bottom of the support rod.

[0006] Preferably, photovoltaic panels are provided on the top of both the upper and lower frame frames, and adjustment components are provided at both ends of both the upper and lower frame frames.

[0007] Preferably, the adjusting component includes a positioning slide rod, the positioning slide rod has a connecting rod inside, the connecting rod has hexagonal nuts at both ends, the bottom of the positioning slide rod has a first sliding groove, and the top of the first sliding groove has a positioning groove.

[0008] Preferably, the connecting rod passes through the positioning slide rod in the upper plate frame and the lower plate frame, and the top of the upper plate frame and the top of the lower plate frame are provided with positioning grooves, and the top of the lower plate frame is provided with a first sliding groove.

[0009] Preferably, a reinforcing rod is provided on the inner side of the positioning slide rod, the reinforcing rod passes through the wing frame, and a mounting plate is provided between the reinforcing rod and the wing frame. The mounting plate and the reinforcing rod, as well as the mounting plate and the wing frame, are connected by snap-fit.

[0010] Preferably, the support rod has a second sliding groove on its outer side, a diagonal tie rod on one side of the second sliding groove, and fixing screws on the outer sides of both ends of the diagonal tie rod. The fixing screws pass through the diagonal tie rod and the interior of the second sliding groove, and the interior of the second sliding groove has threads that cooperate with the fixing screws.

[0011] Preferably, CIGS thin-film solar cells are provided on the outer side of the wing frame, the outer side of the upper plate frame, the outer side of the lower plate frame, and the inner and outer sides of the side frame.

[0012] Beneficial effects

[0013] This invention employs an upper frame, a lower frame, side frames, and a wing frame. The fuselage frame is composed of multiple frame modules and connected to them by support rods and diagonal braces to achieve high rigidity and lightweight. The modular frame structure facilitates assembly and disassembly, and multiple independent mounting positions can be reserved as needed to support quick replacement of batteries, sensors, or photovoltaic modules, thereby improving maintenance efficiency.

[0014] In this invention, an adjustment component and a diagonal tie rod are used. During the assembly of the fuselage frame, the position of the positioning slide rod in the first slide groove is adjusted according to the required structure. After the position is determined, the positioning grooves of the upper plate frame and the lower plate frame are connected to the connecting rod, and then locked with a hexagonal nut. The reinforcing rod passes through the mounting plate and the wing frame for fixation, and is then connected to the mounting plate through the diagonal tie rod. The position of the mounting plate can be adjusted and changed through the second slide groove. The overall structure and installation position can be adjusted at any time through the adjustment component. It can cooperate with the fuselage frame and is convenient for adjustment and installation.

[0015] In this invention, a photovoltaic panel and a CIGS thin-film solar cell are used. The CIGS thin-film solar cell can fit the complex curved surface of the drone to maximize the light-receiving area and achieve high conversion efficiency. Furthermore, by embedding a transparent conductive film under the composite material skin, both structural strength and light transmittance are taken into account, so that the photovoltaic panel and CIGS thin-film solar cell can achieve maximum conversion efficiency. Attached Figure Description

[0016] Figure 1This is an isometric view of the present invention;

[0017] Figure 2 This is a top view of the present invention;

[0018] Figure 3 This is a bottom view of the present invention;

[0019] Figure 4 This is a front view of the present invention;

[0020] Figure 5 This is a side view of the present invention;

[0021] Figure 6 This utility model Figure 1 A magnified view of A in the middle.

[0022] Legend:

[0023] 1. Upper frame; 2. Lower frame; 3. Photovoltaic panel; 4. Side frame; 5. Connecting seat; 6. Wing frame; 7. Reinforcing rod; 8. Mounting plate; 9. Adjustment assembly; 901. Positioning slide rod; 902. Connecting rod; 903. Hexagonal nut; 904. First slide groove; 905. Positioning groove; 10. Support rod; 1001. Second slide groove; 11. Diagonal tie rod; 1101. Fixing screw; 12. Support pad. Detailed Implementation

[0024] To make the technical means, creative features, and achieved objectives and effects of this utility model easier to understand, the present utility model is further described below with reference to specific embodiments and accompanying drawings. However, the following embodiments are merely preferred embodiments of this utility model and not all of them. Other embodiments obtained by those skilled in the art based on the embodiments described in the implementation plan without creative effort are all within the protection scope of this utility model.

[0025] The specific embodiments of this utility model are described below with reference to the accompanying drawings. Specific Implementation Example 1:

[0027] Reference Figure 1-6This utility model provides a high-strength composite material photovoltaic fuselage frame for a drone, including an upper frame 1, a lower frame 2 at the bottom of the upper frame 1, a side frame 4 between the upper frame 1 and the lower frame 2, a connecting seat 5 on the side of the side frame 4, a wing frame 6 at the port of the connecting seat 5, CIGS thin-film solar cells on the outer side of the wing frame 6, the outer side of the upper frame 1, the outer side of the lower frame 2, and the inner and outer sides of the side frame 4, photovoltaic panels 3 on the top of the upper frame 1 and the top of the lower frame 2, and adjustment components 9 at both ends of the upper frame 1 and the lower frame 2. The adjustment assembly 9 includes a positioning slide rod 901, with a connecting rod 902 inside the positioning slide rod 901. Hexagonal nuts 903 are located at both ends of the connecting rod 902. A first groove 904 is located at the bottom of the positioning slide rod 901, and a positioning groove 905 is located at the top of the first groove 904. The connecting rod 902 passes through the positioning slide rod 901 between the upper plate frame 1 and the lower plate frame 2. Positioning grooves 905 are located at the top of both the upper plate frame 1 and the lower plate frame 2. The first groove 904 is located at the top of the lower plate frame 2. A reinforcing rod 7 is located inside the positioning slide rod 901, passing through the wing frame 6. A connection is provided between the reinforcing rod 7 and the wing frame 6. Mounting plate 8 is connected to reinforcing rod 7 and wing frame 6 via snap-fit ​​connections. A support rod 10 is located at the bottom of the lower frame 2. A second sliding groove 1001 is located on the outer side of the support rod 10. A diagonal tie rod 11 is located on one side of the second sliding groove 1001. Fixing screws 1101 are located on the outer sides of both ends of the diagonal tie rod 11, passing through the diagonal tie rod 11 and the interior of the second sliding groove 1001. The interior of the second sliding groove 1001 is threaded, and the threads engage with the fixing screws 1101. A support pad 12 is located at the bottom of the support rod 10. An adjustment assembly 9 and the diagonal tie rod 11 are used. The fuselage frame... During assembly, the positioning slide rod 901 is adjusted to the position of the first slide groove 904 according to the required structure. After the position is determined, the positioning grooves 905 of the upper plate frame 1 and the lower plate frame 2 are connected to the connecting rod 902, and then locked with the hexagonal nut 903. The reinforcing rod 7 passes through the mounting plate 8 and the wing frame 6 for fixation, and is then connected to the mounting plate 8 through the diagonal tie rod 11. The position of the mounting plate 8 can be adjusted and changed through the second slide groove 1001. The overall structure and installation position can be adjusted at any time through the adjustment component 9. It can cooperate with the fuselage frame and is convenient for adjustment and installation. Specific Implementation Example 2:

[0029] Reference Figure 1 By combining AI algorithms to optimize photovoltaic power generation efficiency, it ensures that some power supply can still be maintained during cloudy and rainy weather. High thermal conductivity materials are embedded between the photovoltaic cells and the body to avoid performance degradation caused by hot spot effect. Furthermore, a closed protective plate design is adopted to protect the photovoltaic panel 3 from damage during transportation and in harsh environments.

[0030] In summary:

[0031] 1. The use of upper frame 1, lower frame 2, side frame 4 and wing frame 6 achieves a modular frame structure that facilitates assembly and disassembly. Furthermore, multiple independent mounting positions can be reserved as needed to support quick replacement of batteries, sensors or photovoltaic modules, thereby improving maintenance efficiency.

[0032] 2. By using the adjustment component 9 and the diagonal tie rod 11, the positioning slide rod 901 can be adjusted according to the required structure during the assembly of the fuselage frame. The reinforcing rod 7 passes through the mounting plate 8 and the wing frame 6 for fixation. The position of the mounting plate 8 can be adjusted and changed through the second slide groove 1001. The overall structure and installation position can be adjusted at any time through the adjustment component 9. It can cooperate with the fuselage frame and is convenient for adjustment and installation.

[0033] 3. By using photovoltaic panel 3 and CIGS thin-film solar cells, the CIGS thin-film solar cells can be fitted to the complex curved surface of the UAV, maximizing the light-receiving area and achieving high conversion efficiency. Furthermore, by embedding a transparent conductive film under the composite material skin, both structural strength and light transmittance are taken into account, enabling photovoltaic panel 3 and CIGS thin-film solar cells to achieve maximum conversion efficiency.

[0034] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0035] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely preferred examples and are not intended to limit the utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed utility model. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. A high-strength composite material photovoltaic fuselage frame for a drone, comprising an upper plate frame (1), characterized in that: The bottom of the upper plate frame (1) is provided with a lower plate frame (2), and a side frame (4) is provided between the upper plate frame (1) and the lower plate frame (2). A connecting seat (5) is provided on the side of the side frame (4), and a wing frame (6) is provided at the port of the connecting seat (5). A support rod (10) is provided at the bottom of the lower plate frame (2), and a support pad (12) is provided at the bottom of the support rod (10).

2. The high-strength composite material photovoltaic fuselage frame for a drone according to claim 1, characterized in that: Photovoltaic panels (3) are provided on the top of the upper frame (1) and the top of the lower frame (2), and adjustment components (9) are provided at both ends of the upper frame (1) and both ends of the lower frame (2).

3. The high-strength composite material photovoltaic fuselage frame for a drone according to claim 2, characterized in that: The adjustment component (9) includes a positioning slide rod (901), a connecting rod (902) is provided inside the positioning slide rod (901), hexagonal nuts (903) are provided at both ends of the connecting rod (902), a first sliding groove (904) is provided at the bottom of the positioning slide rod (901), and a positioning groove (905) is provided at the top of the first sliding groove (904).

4. The high-strength composite material photovoltaic fuselage frame for a drone according to claim 3, characterized in that: The connecting rod (902) passes through the positioning slide rod (901) in the upper plate frame (1) and the lower plate frame (2). The top of the upper plate frame (1) and the top of the lower plate frame (2) are provided with positioning grooves (905), and the top of the lower plate frame (2) is provided with a first slide groove (904).

5. The high-strength composite material photovoltaic fuselage frame for a drone according to claim 4, characterized in that: The inner side of the positioning slide rod (901) is provided with a reinforcing rod (7), which passes through the wing frame (6). A mounting plate (8) is provided between the reinforcing rod (7) and the wing frame (6). The mounting plate (8) and the reinforcing rod (7) are connected by snap-fit.

6. The high-strength composite material photovoltaic fuselage frame for a drone according to claim 1, characterized in that: The support rod (10) has a second sliding groove (1001) on its outer side. A diagonal tie rod (11) is provided on one side of the second sliding groove (1001). Fixing screws (1101) are provided on the outer sides of both ends of the diagonal tie rod (11). The fixing screws (1101) pass through the diagonal tie rod (11) and the interior of the second sliding groove (1001). The interior of the second sliding groove (1001) is provided with threads, which cooperate with the fixing screws (1101).

7. The high-strength composite material photovoltaic fuselage frame for a drone according to claim 1, characterized in that: CIGS thin-film solar cells are provided on the outer side of the wing frame (6), the outer side of the upper plate frame (1), the outer side of the lower plate frame (2), and the inner and outer sides of the side frame (4).

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