A drone frame and a drone

Abstract

This utility model relates to the field of aircraft technology, and more particularly to a drone frame and a drone. It includes a fuselage and arms. The fuselage is composed of a first triangular bracket and a second triangular bracket connected by a quick-release connecting module, stacked vertically. Arm clamps are provided at each corner of the first and second triangular brackets, and the arms are inserted into the arm clamps. The connecting module includes one or more carbon fiber support plates. One or more connecting pipe fixing rings are detachably installed on the upper and / or lower surfaces of the carbon fiber support plates. The carbon fiber connecting pipes of the first and second triangular brackets are correspondingly inserted and fixed into the circular holes of the connecting pipe fixing rings. This allows for convenient and quick modular assembly of the drone frame, facilitating assembly and maintenance. Furthermore, the size of the triangular brackets can be adjusted according to requirements, enabling the production of drone frames of different sizes and significantly reducing production costs.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a drone frame and a drone. Background Technology

[0002] Currently, drones are widely used in aerial surveying, agricultural plant protection, logistics and distribution, security patrol, emergency rescue, infrastructure construction, and other operational scenarios. Their convenient take-off and landing without site restrictions and long flight time are the main reasons why users choose them. As industry demands continue to upgrade, drones with large payloads are playing an increasingly important role in industrial applications due to their ability to carry large equipment and transport heavy materials.

[0003] A drone's structure generally consists of a mechanical system, a power system, a flight control system, a remote control and receiving system, a communication and navigation system, and a mission payload. The frame is the main structural framework of the drone, supporting other components. To ensure structural strength, many drone frames are made of a single piece of metal or rigid plastic. While this ensures a certain load-bearing capacity, the high material density significantly increases the drone's weight, sometimes exceeding 40% of the maximum payload. This drastically reduces the effective payload space, increases energy consumption, and shortens flight time. Furthermore, some drones attempt to use engineering plastics to reduce weight, but when flying with heavy loads, the plastic material lacks sufficient mechanical strength to withstand prolonged stress. Under complex weather conditions or at high speeds, it is prone to deformation and breakage, leading to equipment damage or even crashes. In practical use, because the frame is a single piece, if any component is damaged, repairs are difficult due to the difficulty of disassembling and reassembling the structural parts, or the entire frame may be beyond repair. This hinders rapid assembly and maintenance of the drone frame, placing high demands on the user's disassembly and assembly skills. Utility Model Content

[0004] The purpose of this invention is to provide a lightweight, high-strength, easy-to-assemble and maintain, and low-cost drone frame and drone.

[0005] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0006] This utility model proposes a drone frame, including a fuselage and arms. The fuselage is composed of a first triangular bracket and a second triangular bracket stacked and connected by a quick-release connecting module. Each corner of the first and second triangular brackets is provided with an arm clamp, and the arm is inserted into the arm clamp. The quick-release connecting module includes one or more carbon fiber support plates. One or more connecting pipe fixing rings are detachably installed on the upper and / or lower surfaces of the carbon fiber support plates. The carbon fiber connecting pipes of the first and second triangular brackets are inserted and fixed into the circular holes of the connecting pipe fixing rings one by one.

[0007] As a further embodiment of this utility model, the connecting pipe fixing ring includes a pair of half rings, and the two ends of each half ring are locked and fixed by fasteners so that the carbon fiber connecting pipe is clamped in the circular hole of the connecting pipe fixing ring.

[0008] In a further embodiment of this utility model, the top of the semi-ring is provided with a threaded hole, and the carbon fiber support plate is provided with a plurality of through holes along the edge of the end face that are adapted to the threaded hole. The connecting pipe fixing ring is locked to the threaded hole by bolts passing through the corresponding through holes of the carbon fiber support plate.

[0009] In a further embodiment of this utility model, the first triangular support consists of three first arm fixing modules and three first carbon fiber connecting pipes. The three first carbon fiber connecting pipes form a first triangular support. The connecting ends of two adjacent first carbon fiber connecting pipes are connected through the first arm fixing modules. The arm clamp is mounted on the first arm fixing modules.

[0010] In a further embodiment of this utility model, the first arm fixing module includes at least two first carbon fiber mounting plates arranged in parallel and spaced vertically. A first carbon fiber connecting pipe fixing ring is provided between each pair of vertically opposite first carbon fiber mounting plates to provide support and form a hollow channel. The connecting ends of two adjacent first carbon fiber connecting pipes are inserted into one layer of the hollow channel, and the connecting ends of the first carbon fiber connecting pipes are fixed within the hollow channel by the first carbon fiber connecting pipe fixing ring. The arm clamp is located between two vertically opposite first carbon fiber mounting plates. In the first arm fixing module, the connecting ends of the first carbon fiber connecting pipes and the arm clamp are located within the same or different layers of the hollow channel.

[0011] In a further embodiment of this utility model, the second triangular support consists of three second arm fixing modules and three second carbon fiber connecting pipes. The three second carbon fiber connecting pipes form a second triangular support, and the connecting ends of two adjacent second carbon fiber connecting pipes are connected through the second arm fixing modules. The arm clamp is mounted on the second arm fixing modules.

[0012] In a further embodiment of this utility model, the second arm fixing module includes at least two second carbon fiber mounting plates arranged in parallel and spaced vertically. A second carbon fiber connecting pipe fixing ring is provided between each pair of vertically opposite second carbon fiber mounting plates to provide support and form a hollow channel. The connecting ends of two adjacent second carbon fiber connecting pipes are inserted into one layer of the hollow channel, and the connecting ends of the second carbon fiber connecting pipes are fixed within the hollow channel by the second carbon fiber connecting pipe fixing ring. The arm clamp is located between two vertically opposite second carbon fiber mounting plates. In the second arm fixing module, the connecting ends of the second carbon fiber connecting pipes and the arm clamp are located within the same or different layers of the hollow channel.

[0013] In a further embodiment of this utility model, both the first carbon fiber connecting pipe and the second carbon fiber connecting pipe are cut from the same one-piece molded carbon fiber pipe to a predetermined length; the carbon fiber support plate, the first carbon fiber mounting plate, and the second carbon fiber mounting plate of the quick-release connecting module are all cut from the same one-piece molded carbon fiber sheet to a predetermined shape.

[0014] As a further embodiment of this utility model, the arm is made of carbon fiber tubes of predetermined lengths cut from identical carbon fiber tubes formed in one piece; the connecting tube fixing ring is made of elastic material.

[0015] This utility model also proposes a drone, which adopts the drone frame described above.

[0016] The beneficial effects of this utility model are as follows: The drone frame provided by this utility model is formed by the carbon fiber connecting tubes of the first and second triangular brackets of the drone frame being stacked and fixedly connected by quick-release connecting modules. The carbon fiber connecting tubes have the outstanding characteristics of being lightweight and high-strength, and have better thermal stability and corrosion resistance. This allows for convenient and quick modular assembly of the drone frame, which facilitates the assembly and maintenance of the drone frame. Furthermore, the size of the triangular brackets can be adjusted according to requirements, thereby enabling the production of drone frames of different sizes and greatly reducing production costs. Attached Figure Description

[0017] Figure 1 This is an exploded view of the drone frame according to an embodiment of this utility model.

[0018] Figure 2 This is a schematic diagram of the fuselage of the unmanned aerial vehicle (UAV) according to an embodiment of this utility model.

[0019] Figure 3 This is an exploded view of the fuselage of the drone according to an embodiment of this utility model.

[0020] Figure 4 This is a schematic diagram of the quick-release connection module according to an embodiment of the present invention. Figure 1 .

[0021] Figure 5 This is a schematic diagram of the quick-release connection module according to an embodiment of the present invention. Figure 2 .

[0022] Figure 6 This is a schematic diagram of the structure of the connecting pipe fixing ring according to an embodiment of the present utility model.

[0023] Figure 7 This is a schematic diagram of the overall structure of the drone according to an embodiment of the present invention. Detailed Implementation

[0024] Exemplary embodiments of this application will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of this application are shown in the drawings, it should be understood that this application may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of this application and to fully convey the scope of this application to those skilled in the art.

[0025] It should be understood that the terminology used herein is for the purpose of describing particular exemplary embodiments only and is not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “described” as used herein may also include the plural forms. The terms “comprising,” “including,” “containing,” and “having” are inclusive and therefore indicate the presence of the stated features, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, elements, components, and / or combinations thereof. The method steps, processes, and operations described herein are not construed as requiring them to be performed in a particular order described or illustrated unless the order of performance is explicitly indicated. It should also be understood that additional or alternative steps may be used.

[0026] Although terms such as "first," "second," etc., may be used in this document to describe multiple elements, components, regions, layers, and / or segments, these elements, components, regions, layers, and / or segments should not be limited by these terms. These terms may be used only to distinguish one element, component, region, layer, or segment from another. Unless the context clearly indicates otherwise, terms such as "first," "second," and other numerical terms used herein do not imply order or sequence. Therefore, the elements, components, regions, layers, or segments discussed below may be referred to as second elements, components, regions, layers, or segments without departing from the teachings of the exemplary embodiments.

[0027] For ease of description, spatial relative terms may be used in the text to describe the relationship of one element or feature relative to another element or feature, as shown in the figure. These relative terms include, for example, "inside," "outside," "above," "below," "horizontal," etc. Such spatial relative terms are intended to include different orientations of the device in use or operation, other than those depicted in the figure. For example, if the device in the figure is flipped, an element described as "below other elements or features" or "below other elements or features" would subsequently be oriented as "above other elements or features" or "above other elements or features." Therefore, the example term "below" can include both above and below orientations. The device may be otherwise oriented (rotated 90 degrees or in other directions), and the spatial relative descriptors used in the text will be interpreted accordingly.

[0028] Please refer to Figure 1-7 As shown, this utility model proposes a drone frame 100, including a fuselage 10 and an arm 20. Both the fuselage 10 and the arm 20 are made of carbon fiber material. Carbon fiber material has the outstanding characteristics of being lightweight and high-strength, and has better thermal stability and corrosion resistance, thus achieving lightweighting while meeting the structural strength requirements.

[0029] The arms 20 extend radially outward from the edge of the fuselage 10, with all arms 20 located on the same plane and arranged symmetrically at the center. The arms are made of high-strength, lightweight carbon fiber tubing cut to predetermined lengths, resulting in high structural strength. One end of each arm 20 is securely connected to the fuselage 10 via an arm clamp 60, ensuring it will not loosen during flight. The arms 20 can be designed as foldable or detachable structures for easy connection to the fuselage 10, facilitating the storage and transportation of the drone. The length, shape, and distribution of the pure carbon fiber tubing arms 20 have a significant impact on the aerodynamic performance and maneuverability of the drone. Longer arms 20 increase the distance between motors, effectively reducing airflow interference from the propellers and improving flight efficiency. A reasonable arm 20 distribution angle helps the drone to perform more flexible turning, pitching, and other maneuvers during flight, ensuring flight stability and precise control. One end of each arm 20 is tightly connected to the fuselage 10, providing mounting support for the motor assembly 21 of the power system. The motor assembly 21 is mounted at the end of the arm 20. The arm 20 transmits the power generated by the motor assembly 21 to the frame 100, thereby driving the entire UAV in flight. The propeller 22 is mounted on the motor shaft of the motor assembly 21 and can be made of materials such as carbon fiber, with different numbers and shapes of blades. Its rotation generates lift and thrust. The size, shape, and angle of the blades are designed according to the type and requirements of the UAV, affecting power output and flight efficiency. The motor assembly 21 and propeller 22 can be designed using existing technologies.

[0030] The fuselage 10 is generally hexagonal in shape. It is composed of a first triangular support 30 and a second triangular support 40 stacked together via a quick-release connection module 50. The central part of the assembled fuselage 10 has a hollow structure for installing functional components. Each corner of the first triangular support 30 and the second triangular support 40 is equipped with an arm clamp 60, into which the arm 20 is inserted. The quick-release connection module 50 includes one or more carbon fiber support plates 51, which can be prepared by compression molding or pultrusion molding and then cut into predetermined shapes and sizes. The upper and / or lower surfaces of the carbon fiber support plates 51 are detachable. One or more connecting pipe fixing rings 52 are installed, and the connecting pipe fixing rings 52 are made of elastic material. The carbon fiber connecting pipes of the first triangular bracket 30 and the second triangular bracket 40 are inserted and fixed in the circular holes 521 of the connecting pipe fixing rings 52. Therefore, the carbon fiber connecting pipes of the first triangular bracket 30 and the second triangular bracket 40 of the UAV frame are connected by stacking and fixing through quick-release connecting modules. Modular production and assembly are possible, and the fuselage 10 does not need to be welded, which facilitates the assembly and maintenance of the fuselage 10. Moreover, the size of the triangular bracket can be adjusted according to the needs, thereby realizing the production of UAV frames of different sizes and greatly reducing production costs.

[0031] In one embodiment of this utility model, the connecting pipe fixing ring 52 includes a pair of half rings 53. The two ends of each half ring 53 are locked and fixed by fasteners 532, so that the carbon fiber connecting pipe is clamped in the circular hole 521 of the connecting pipe fixing ring. The top of the half ring 53 is provided with a threaded hole 531. The carbon fiber support plate 51 is provided with several through holes 511 that are adapted to the threaded holes 531 along the edge of the end face. The connecting pipe fixing ring 52 is locked to the threaded hole 531 by bolts passing through the corresponding through holes 511 of the carbon fiber support plate 51. The connecting pipe fixing ring 52 enables convenient and quick assembly and disassembly of the carbon fiber connecting pipes of the first triangular bracket 30 and the second triangular bracket 40 to be stacked and fixedly connected.

[0032] In one embodiment of this utility model, the first triangular support 30 consists of three first arm fixing modules 31 and three first carbon fiber connecting pipes 32. The three first carbon fiber connecting pipes 32 are connected end to end to form the first triangular support 30. Each corner of the first triangular support 30 corresponds to a first arm fixing module 31. The connecting ends of two adjacent first carbon fiber connecting pipes 32 are connected through the first arm fixing module 31. The arm clamp 60 is installed on the first arm fixing module 31.

[0033] In one embodiment of this utility model, the first arm fixing module 31 includes at least two first carbon fiber mounting plates 311 arranged in parallel and spaced vertically. A first carbon fiber connecting pipe fixing ring 312 is provided between each pair of vertically opposite first carbon fiber mounting plates 311 to provide fixed support and form a hollow channel. The connecting ends of two adjacent first carbon fiber connecting pipes 32 are inserted into one layer of the hollow channel, and the connecting ends of the first carbon fiber connecting pipes 32 are fixed in the hollow channel by the first carbon fiber connecting pipe fixing ring 312. The arm clamp 60 is disposed between the two vertically opposite first carbon fiber mounting plates 311. In the first arm fixing module 31, the connecting ends of the first carbon fiber connecting pipes 32 and the arm clamp 60 are disposed in the same or different layers of the hollow channel, thereby improving the structural strength of the fuselage 10.

[0034] In one embodiment of this utility model, the second triangular support 40 consists of three second arm fixing modules 41 and three second carbon fiber connecting pipes 42. The three second carbon fiber connecting pipes 42 form a second triangular support 40. The connecting ends of two adjacent second carbon fiber connecting pipes 42 are connected through the second arm fixing modules 41. The arm clamp 60 is installed on the second arm fixing modules 41.

[0035] In one embodiment of this utility model, the second arm fixing module 41 includes at least two or more second carbon fiber mounting plates 411 arranged in parallel and spaced vertically. A second carbon fiber connecting pipe fixing ring 412 is provided between each pair of vertically opposite second carbon fiber mounting plates 411 to provide fixed support and form a hollow channel. The connecting ends of two adjacent second carbon fiber connecting pipes 42 are inserted into one layer of the hollow channel, and the connecting ends of the second carbon fiber connecting pipes 42 are fixed in the hollow channel by the second carbon fiber connecting pipe fixing ring 412. The arm clamp 60 is disposed between the two vertically opposite second carbon fiber mounting plates 411. In the second arm fixing module 41, the connecting ends of the second carbon fiber connecting pipes 42 and the arm clamp 60 are disposed in the same layer or different layers of the hollow channel.

[0036] In an embodiment of this utility model, the first carbon fiber connecting tube 32 and the second carbon fiber connecting tube 42 are both cut from the same one-time molded carbon fiber tube to a predetermined length; the carbon fiber support plate 51, the first carbon fiber mounting plate 311 and the second carbon fiber mounting plate 411 of the quick-release connecting module are all cut from the same one-time molded carbon fiber sheet to a predetermined shape.

[0037] In one embodiment of this utility model, the fuselage 10 further includes a landing gear 11, which is connected to the lower part of the fuselage 10 and is also made of carbon fiber material to reduce the weight of the fuselage 10 while ensuring structural strength. The fuselage 10 typically adopts a frame structure, mainly made of lightweight alloy or high-strength plastic, to ensure sufficient strength to support the weight of the drone while reducing its own weight. The fuselage 10 plays a crucial role in the takeoff and landing of the drone. First, it maintains a certain safe distance between the fuselage 10 and the ground, preventing the fuselage 10 from tilting due to instability when the drone takes off or lands close to the ground, thereby avoiding collision between the propeller and the ground and protecting the propeller and fuselage. Second, the landing gear 11 creates sufficient space between the propeller and the ground, effectively reducing airflow interference between the airflow and the ground during takeoff and landing, and improving the stability and safety of the takeoff and landing process. The landing gear 11 is installed at the bottom of the fuselage 10, usually symmetrically installed at the four corners of the bottom of the fuselage, to ensure that the UAV can be stably supported during take-off and landing and maintain the balance of the fuselage.

[0038] As an embodiment of this utility model, a drone is also proposed, which includes a flight platform. The flight platform is mainly composed of the aforementioned drone frame 100, power system, intelligent control system, and other core modules. Through scientific installation layout and close cooperation, each module can achieve heavy-load flight missions. The drone frame is the basic support structure of the drone, providing an installation platform for other systems. The power system and intelligent control system are installed on the drone frame. The drone constructed in this way has its fuselage structure, especially the drone frame, constructed from pure carbon fiber connecting pipes or pure carbon fiber support plates. The one-piece molded carbon fiber pipes and carbon fiber support plates are cut to predetermined dimensions and assembled with connecting pipe fixing rings or carbon fiber connecting pipe fixing rings. The entire fuselage is assembled from carbon fiber connecting pipe or carbon fiber support plate modules, which is lightweight and high-strength, with no welding or weld points. It can also be assembled by stacking and connecting multiple layers of triangular brackets to obtain various drones. Therefore, the drone fuselage has strong stability, high mechanical strength, better thermal stability and corrosion resistance, and is suitable for various loads, especially for various heavy-load application scenarios.

[0039] The above description is merely a preferred embodiment of the present invention and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of the invention is not limited to the specific combination of the above-described technical features, but also includes other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the inventive concept. For example, technical solutions formed by substituting the above-described features with (but not limited to) technical features with similar functions as those in the present invention.

[0040] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An unmanned aerial vehicle (UAV) rack, comprising: The system includes a fuselage and an arm. The fuselage is composed of a first triangular bracket and a second triangular bracket stacked and connected by a quick-release connecting module. Each corner of the first and second triangular brackets is provided with an arm clamp, and the arm is inserted into the arm clamp. The quick-release connecting module includes one or more carbon fiber support plates. One or more connecting pipe fixing rings are detachably installed on the upper and / or lower surfaces of the carbon fiber support plates. The carbon fiber connecting pipes of the first and second triangular brackets are inserted and fixed into the circular holes of the connecting pipe fixing rings in a one-to-one correspondence.

2. The drone airframe of claim 1, wherein: The connecting pipe fixing ring includes a pair of half rings, and the two ends of each half ring are locked and fixed by fasteners so that the carbon fiber connecting pipe is clamped in the circular hole of the connecting pipe fixing ring.

3. The drone airframe of claim 2, wherein: The top of the semi-ring is provided with a threaded hole, and the carbon fiber support plate is provided with several through holes along the edge of the end face that are adapted to the threaded hole. The connecting pipe fixing ring is locked to the threaded hole by bolts passing through the corresponding through holes of the carbon fiber support plate.

4. The UAV frame as described in claim 1, characterized in that: The first triangular support consists of three first arm fixing modules and three first carbon fiber connecting pipes. The three first carbon fiber connecting pipes form the first triangular support. The connecting ends of two adjacent first carbon fiber connecting pipes are connected through the first arm fixing modules. The arm clamp is set on the first arm fixing module.

5. The UAV frame as described in claim 4, characterized in that: The first arm fixing module includes at least two first carbon fiber mounting plates arranged parallel to each other in sequence. A first carbon fiber connecting pipe fixing ring is provided between each pair of vertically opposite first carbon fiber mounting plates to provide support and form a hollow channel. The connecting ends of two adjacent first carbon fiber connecting pipes are inserted into one layer of the hollow channel, and the connecting ends of the first carbon fiber connecting pipes are fixed in the hollow channel by the first carbon fiber connecting pipe fixing ring. The arm clamp is disposed between two vertically opposite first carbon fiber mounting plates. In the first arm fixing module, the connecting ends of the first carbon fiber connecting pipes and the arm clamp are disposed in the same layer or different layers of the hollow channel.

6. The UAV frame as described in claim 5, characterized in that: The second triangular support consists of three second arm fixing modules and three second carbon fiber connecting pipes. The three second carbon fiber connecting pipes form the second triangular support. The connecting ends of two adjacent second carbon fiber connecting pipes are connected through the second arm fixing modules. The arm clamp is set on the second arm fixing modules.

7. The UAV frame as described in claim 6, characterized in that: The second arm fixing module includes at least two second carbon fiber mounting plates arranged in parallel and spaced vertically. A second carbon fiber connecting pipe fixing ring is provided between each pair of vertically opposite second carbon fiber mounting plates to provide support and form a hollow channel. The connecting ends of two adjacent second carbon fiber connecting pipes are inserted into one layer of the hollow channel, and the connecting ends of the second carbon fiber connecting pipes are fixed in the hollow channel by the second carbon fiber connecting pipe fixing ring. The arm clamp is located between two vertically opposite second carbon fiber mounting plates. In the second arm fixing module, the connecting ends of the second carbon fiber connecting pipes and the arm clamp are located in the same or different layers of the hollow channel.

8. The UAV frame as described in claim 7, characterized in that: Both the first carbon fiber connecting tube and the second carbon fiber connecting tube are cut from the same one-piece molded carbon fiber tube to a predetermined length; the carbon fiber support plate, the first carbon fiber mounting plate and the second carbon fiber mounting plate of the quick-release connecting module are all cut from the same one-piece molded carbon fiber sheet to a predetermined shape.

9. The UAV frame as described in claim 1, characterized in that: The arm is made of carbon fiber tubes cut into predetermined lengths from a single molded carbon fiber tube; the connecting tube fixing ring is made of elastic material.

10. An unmanned aerial vehicle (UAV), characterized in that: The drone uses a drone frame as described in any one of claims 1-9.

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