Unmanned aerial vehicle fuselage frame based on assembled photovoltaic array

Abstract

The utility model provides an unmanned aerial vehicle fuselage frame based on a split mounting type photovoltaic array, which relates to the technical field of unmanned aerial vehicle frames and comprises a fuselage, a photovoltaic panel is arranged at the top of the fuselage, connecting seats are arranged on two sides of the fuselage, arm modules are arranged at ports of the connecting seats, magnetic suction ends are arranged at two ends of the fuselage, and replacement parts are arranged at ports of the magnetic suction ends. A 3D printing honeycomb core is arranged in the machine body, a connecting frame is arranged at the bottom of the machine body, and the photovoltaic panel and the 3D printing honeycomb core are adopted, so that through existence of the photovoltaic panel, the weight of an external cable can be reduced by directly connecting the photovoltaic panel with a battery management system, the 3D printing honeycomb core is constructed in a frame, and the frame is covered with a carbon fiber truss grid; compared with a traditional solid frame, the weight of the structure is reduced, and the flexural rigidity is improved.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) frame technology, and in particular to a UAV fuselage frame based on a modular photovoltaic array. Background Technology

[0002] According to Chinese Patent No. CN215399354U, a solar-powered rotary-wing drone is disclosed to solve the technical problem of short flight time in current rotary-wing drones. The drone includes a fuselage with a frame and a built-in battery; a rotor mounted on the frame and powered by the battery; a mounting frame configured to house a louvered photovoltaic panel electrically connected to the battery, wherein the mounting frame is mounted on the frame and located above the fuselage; at least one memory configured to store at least one instruction; at least one processor configured to be electrically connected to the memory and the rotor; and a drive device electrically connected to the processor. The processor controls the operating state of the rotor and controls the drive device to switch the photovoltaic panel between a first state and a second state.

[0003] The aforementioned comparative documents and existing technologies have the following technical problems: The existing drone fuselage frame is the main component structure of the drone, and its frame determines the shape and structure of the drone. However, the assembly and use of the drone fuselage have not been well improved. The drone fuselage is mostly one piece, which restricts the subsequent assembly and expansion of the drone. Moreover, the fuselage can reduce its weight by optimizing its own layout. Utility Model Content

[0004] The purpose of this invention is to address the shortcomings of existing technologies by proposing a drone fuselage frame based on a modular photovoltaic array.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: a drone fuselage frame based on a modular photovoltaic array, including a fuselage, a photovoltaic panel on the top of the fuselage, connecting seats on both sides of the fuselage, an arm module at the port of the connecting seat, magnetic ends at both ends of the fuselage, and a replacement part at the port of the magnetic ends.

[0006] Preferably, the interior of the body is provided with a 3D printed honeycomb core, the bottom of the body is provided with a connecting frame, the inner side of the connecting frame is provided with an embedding groove, and the top of the connecting frame is provided with an elastic pad.

[0007] Preferably, the body has heat dissipation holes on both sides, an inner groove on the front of the body, a 3D printed honeycomb core inside the inner groove, and a carbon fiber truss mesh on the outside of the 3D printed honeycomb core.

[0008] Preferably, the bottom of the connector is provided with a positioning plug, the two sides of the body are provided with slots, the slots are connected to the positioning plug, the bottom of the connector is provided with a connecting groove, and the positioning plug and the connector are connected through the connecting groove.

[0009] Preferably, the arm module includes a folding rod, one end of which is provided with a connecting rod, and the other end of which is provided with a rotor seat. The rotor seat contains a rotor shaft, and the bottom of the rotor seat has a foot pad that is connected to the connecting seat by bolts. The other end of the folding rod is provided with a connecting groove, and the connecting rod is connected to the connecting groove. The rotor shaft is embedded inside the rotor seat.

[0010] Preferably, both ends of the machine body are provided with magnetic suction ends, the magnetic suction ends are provided with magnetic suction blocks inside, the surface of the magnetic suction ends is provided with slots, and the bottom of the replacement part is provided with buckles, which cooperate with the slots of the magnetic suction ends.

[0011] Beneficial effects

[0012] In this invention, a photovoltaic panel and a 3D-printed honeycomb core are used. The presence of the photovoltaic panel allows for direct connection between the photovoltaic panel and the battery management system, reducing the weight of external cables. The 3D-printed honeycomb core is constructed inside the frame and covered with a carbon fiber truss mesh on the outside. This structure is lighter than a traditional solid frame and has improved bending stiffness.

[0013] In this invention, a magnetic end and an arm module are used. The magnetic end is connected by both magnetic attraction and buckle, allowing for easy replacement and disassembly. The arm module is positioned and connected by a connecting seat and a positioning block. The replacement parts and the arm module are assembled with the fuselage. This structure facilitates the disassembly and assembly of the drone. Attached Figure Description

[0014] Figure 1 This is an isometric view of the present invention;

[0015] Figure 2 This is a top view of the present invention;

[0016] Figure 3 This is a bottom view of the present invention;

[0017] Figure 4 This is a front view of the present invention;

[0018] Figure 5 This is a side view of the present invention;

[0019] Figure 6 This is a side sectional view of the present invention;

[0020] Figure 7 This is a top sectional view of the present invention.

[0021] Legend:

[0022] 1. Body; 101. Heat dissipation hole; 102. Inner groove; 2. Photovoltaic panel; 3. Connecting seat; 301. Positioning plug; 4. Arm module; 401. Folding rod; 402. Connecting rod; 403. Rotor seat; 404. Rotor shaft; 405. Foot pad; 5. Magnetic end; 6. Replacement parts; 7. 3D printed honeycomb core; 8. Connecting frame; 801. Embedding groove; 802. Elastic pad. Detailed Implementation

[0023] 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.

[0024] The specific embodiments of this utility model are described below with reference to the accompanying drawings. Specific Implementation Example 1:

[0026] Reference Figure 1-7This utility model provides a drone fuselage frame based on a modular photovoltaic array, including a fuselage 1, a photovoltaic panel 2 on the top of the fuselage 1, connecting seats 3 on both sides of the fuselage 1, a positioning block 301 at the bottom of the connecting seat 3, slots on both sides of the fuselage 1 connected to the positioning block 301, a connecting groove at the bottom of the connecting seat 3, and the positioning block 301 connected to the connecting seat 3 via the connecting groove. An arm module 4 is provided at the port of the connecting seat 3, and the arm module 4 includes a folding arm. The folding rod 401 has a connecting rod 402 at one end and a rotor seat 403 at the other end. A rotor shaft 404 is located inside the rotor seat 403, and a foot pad 405 is located at the bottom of the rotor seat 403. One end of the folding rod 401 is connected to the connecting seat 3 by bolts, and the other end of the folding rod 401 has a connecting groove. The connecting rod 402 is connected to the connecting groove. The rotor shaft 404 is embedded inside the rotor seat 403. Magnetic suction ends 5 are located at both ends of the fuselage 1. The machine body 1 has magnetic ends 5 on both sides, with magnetic blocks inside and slots on the surface. The bottom of the replacement part 6 has a buckle that engages with the slots of the magnetic ends 5. The port of the magnetic ends 5 has a replacement part 6. The machine body 1 has a 3D printed honeycomb core 7 inside. The machine body 1 has heat dissipation holes 101 on both sides. The front of the machine body 1 has an inner groove 102, with the 3D printed honeycomb core 7 inside. The outer side of the 3D printed honeycomb core 7 has a carbon fiber truss mesh. The bottom of the machine body 1 has a connecting frame 8, with an embedding groove 801 on the inner side. The top of the connecting frame 8 has an elastic pad 802. The machine body 1 uses a photovoltaic panel 2 and a 3D printed honeycomb core 7. The presence of the photovoltaic panel 2 allows for direct connection between the photovoltaic panel 2 and the battery management system, reducing the weight of external cables. The 3D printed honeycomb core 7 is built inside the frame and covered with a carbon fiber truss mesh on the outside. This structure is lighter than a traditional solid frame and has improved bending stiffness. Specific Implementation Example 2:

[0028] Reference Figure 1 Perovskite solar cells are directly deposited on the surface of carbon fiber skin to form a dual-function skin that generates electricity and supports loads. The surface area of ​​the drone is converted into power generation units, and the power generation per unit area is higher than that of external photovoltaic panels. Lithium-sulfur solid-state batteries are embedded inside the frame, and the carbon fiber layer also serves as an electrode carrier, which increases the energy storage density of the frame itself and reduces the weight compared to external batteries.

[0029] In summary:

[0030] 1. By using photovoltaic panel 2 and 3D printed honeycomb core 7, the presence of photovoltaic panel 2 allows for direct connection between photovoltaic panel 2 and battery management system, reducing the weight of external cables. The 3D printed honeycomb core 7 is constructed inside the frame and covered with carbon fiber truss mesh on the outside. This structure is lighter than traditional solid frames and has improved bending stiffness.

[0031] 2. The use of magnetic end 5 and arm module 4 achieves a dual connection of magnetic attraction and buckle through magnetic end 5, which can be replaced and disassembled at any time. The arm module 4 is positioned and connected to the positioning plug 301 through the connecting seat 3. The replacement part 6 and the arm module 4 are assembled with the body 1. This structure facilitates the disassembly and assembly of the UAV.

[0032] 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.

[0033] 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. An unmanned aerial vehicle fuselage frame based on a modular photovoltaic array, comprising a fuselage (1), characterized in that: The top of the fuselage (1) is provided with a photovoltaic panel (2), both sides of the fuselage (1) are provided with a connecting seat (3), the port of the connecting seat (3) is provided with a machine arm module (4), both ends of the fuselage (1) are provided with a magnetic suction end (5), the port of the magnetic suction end (5) is provided with a replacement part (6).

2. The UAV fuselage frame based on the assembled photovoltaic array according to claim 1, characterized in that: The inside of the fuselage (1) is provided with a 3D printing honeycomb core (7), the bottom of the fuselage (1) is provided with a connecting frame (8), the inner side of the connecting frame (8) is provided with an embedded groove (801), the top of the connecting frame (8) is provided with an elastic gasket (802).

3. The assembled photovoltaic array based drone fuselage frame of claim 1, wherein: Both sides of the fuselage (1) are provided with heat dissipation holes (101), the front of the fuselage (1) is provided with an inner groove (102), the inside of the inner groove (102) is provided with a 3D printing honeycomb core (7), the outside of the 3D printing honeycomb core (7) is provided with a carbon fiber truss grid.

4. The assembled photovoltaic array based drone fuselage frame of claim 1, wherein: The bottom end of the connecting seat (3) is provided with a positioning plug (301), both sides of the fuselage (1) are provided with a notch, which is connected between the positioning plug (301), the bottom of the connecting seat (3) is provided with a connecting groove, the positioning plug (301) and the connecting seat (3) are connected through the connecting groove.

5. The assembled photovoltaic array based UAV fuselage frame of claim 1, wherein: The machine arm module (4) includes a folding rod (401), one end of the folding rod (401) is provided with a connecting rod (402), the other end of the connecting rod (402) is provided with a rotor seat (403), the inside of the rotor seat (403) is provided with a rotor shaft (404), the bottom of the rotor seat (403) is provided with a foot pad (405).

6. The frame of the UAV body based on the assembled photovoltaic array according to claim 5, characterized in that: One end of the folding rod (401) and the connecting seat (3) are connected through bolts, the other end of the folding rod (401) is provided with a connecting groove, the connecting rod (402) is connected with the connecting groove, and the rotor shaft (404) is embedded in the inside of the rotor seat (403).

7. The assembled photovoltaic array based drone fuselage frame of claim 3, wherein: Both sides of both ends of the fuselage (1) are provided with a magnetic suction end (5), the inside of the magnetic suction end (5) is provided with a magnetic suction block, the surface of the magnetic suction end (5) is provided with a clamping groove, the bottom of the replacement part (6) is provided with a buckle, and the buckle is matched with the clamping groove of the magnetic suction end (5).

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