Flight platform and unmanned aerial vehicle

Abstract

The utility model provides a kind of flight platform and unmanned aerial vehicle, flight platform includes fuselage and six machine arms, the fuselage is hexagonal, the machine arm is connected in the corner end of fuselage, one mounting sleeve is equipped in the six corner ends of fuselage, the machine arm one-to-one corresponding detachably inserted in the mounting sleeve, the machine arm and mounting sleeve are carbon fiber tube, the center line of each mounting sleeve is coplanar arrangement.Through setting mounting sleeve in the corner end of fuselage, setting mounting sleeve and machine arm as carbon fiber material, can carry out modular assembly, reduce the weight of unmanned aerial vehicle, also facilitate the assembly of rack, in addition, the shape and size of carbon fiber frame can be adjusted according to needs, to realize the production of unmanned aerial vehicle of different shapes and different sizes, without developing different size mould, greatly reduce production cost.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and more specifically, to a flight platform and an unmanned aerial vehicle. Background Technology

[0002] In recent years, drone technology has developed rapidly worldwide and has been widely used in many fields such as aerial surveying and mapping, agricultural plant protection, logistics and distribution, security inspection, emergency rescue, and infrastructure construction. As application scenarios continue to expand and deepen, the market has placed more stringent demands on drone performance, prompting drones to continue evolving towards greater efficiency, intelligence, and reliability.

[0003] As industry demands continue to upgrade, heavy-duty drones, with their ability to carry large equipment and transport heavy materials, are playing an increasingly important role in industrial applications.

[0004] In the construction sector, the planning and construction of large-scale infrastructure projects such as bridges, railways, tunnels, buildings, and facilities require drones equipped with heavy equipment such as lidar and high-precision mapping cameras for terrain modeling, construction progress monitoring, and structural inspection. In construction sites with rugged terrain and inconvenient transportation, drones can be used for transportation and inspection, and can also carry building materials. The application of drones can solve the problems of low efficiency and specific requirements of traditional transportation methods in terms of construction environment and transportation. They can also replace helicopters in addressing the high costs and landing space requirements of these tasks. For example, in the construction of cross-sea bridges, high-payload drones can carry inspection equipment weighing several kilograms to conduct close-range inspections of key structural parts of the bridge, promptly identifying potential hazards. In the field of emergency rescue, when natural disasters occur, such drones can deliver emergency supplies such as food, medicine, and life jackets to remote disaster areas or inaccessible regions, with a single payload reaching several kilograms or even higher, providing strong support for rescue efforts. In the logistics and transportation sector, some companies are exploring the use of high-payload drones to achieve cross-regional, long-distance cargo transportation to solve the delivery problems of traditional logistics in remote or inaccessible areas.

[0005] To meet heavy payload requirements, traditional drones often use high-strength aluminum alloys, titanium alloys, and other metallic materials for their fuselages. While this ensures a certain load-bearing capacity, the high density of these materials 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. However, when flying with heavy loads, the mechanical strength of plastics is insufficient to withstand prolonged stress. Under complex weather conditions or at high speeds, this can easily lead to fuselage deformation, breakage, and even equipment damage or crashes.

[0006] In terms of structural design, current heavy-duty drones often improve load-bearing capacity by adding supporting components and reinforcing the frame. However, this design often lacks a balanced optimization between lightweight and high strength. Numerous additional supporting structures and reinforced components not only increase the weight of the fuselage but also increase structural complexity, reducing assembly efficiency and maintenance convenience. Furthermore, the complex structure leads to an unreasonable center of gravity distribution, making the drone prone to swaying and vibration during flight, affecting flight stability and controllability. For example, some heavy-duty drones used for logistics transportation have excessively reinforced their fuselage frames to carry heavier loads, resulting in an overall weight exceeding expectations. This requires more power to maintain balance during flight and frequently leads to malfunctions such as loose parts and wear.

[0007] To further expand the application boundaries of heavy-payload UAVs and improve their operational efficiency in construction, rescue, logistics, and other fields, it is urgent to overcome existing technological bottlenecks. Solving problems such as insufficient airframe weight, inadequate mechanical strength, and poor flight stability can significantly improve the payload, range, and reliability of heavy-payload UAVs, enabling them to better adapt to complex environments and diverse mission requirements. Utility Model Content

[0008] The purpose of this invention is to provide a flight platform and an unmanned aerial vehicle (UAV) using the flight platform, thereby solving the problems of heavy fuselage and low mechanical strength caused by the materials used in existing UAV flight platforms.

[0009] To achieve the above objectives, this utility model provides the following technical solution: This utility model provides a flight platform, including a fuselage and multiple arms. The fuselage is hexagonal, and the arms are connected to the corners of the fuselage. Each of the six corners of the fuselage is provided with a mounting sleeve. The arms are detachably inserted into the mounting sleeves one by one. The arms and the mounting sleeves are all carbon fiber tubes, and the center lines of each mounting sleeve are coplanar.

[0010] In one embodiment, the fuselage is formed by splicing a first triangular frame and a second triangular frame with staggered corners, and each triangular frame is provided with a mounting sleeve at its corner.

[0011] In one embodiment, the first triangular frame includes multiple first connecting tubes connected end to end, and the second triangular frame includes multiple second connecting tubes connected end to end. The positions where the first connecting tubes and the second connecting tubes intersect are connected by a cross-fixing module made of carbon fiber material.

[0012] In one embodiment, the cross-fixing module includes an intermediate mounting plate and a first connecting pipe fixing ring and a second connecting pipe fixing ring disposed on the upper and lower sides of the intermediate mounting plate, respectively. The first connecting pipe fixing ring and the second connecting pipe fixing ring are used to fix the first connecting pipe and the second connecting pipe, and the included angle between the central axes of the first connecting pipe fixing ring and the second connecting pipe fixing ring is matched with the included angle between the first connecting pipe and the second connecting pipe.

[0013] In one embodiment, the arm is provided as an arm extension at the end away from the mounting sleeve, and the arm extension is perpendicular to the connecting pipe located on another frame and closest to it and connected by an orthogonal fixing module.

[0014] In one embodiment, the orthogonal fixing module includes a boom fixing ring and a connecting pipe fixing ring, which are used to fix the boom extension and the connecting pipe respectively, and their central axes are perpendicular to each other.

[0015] In one embodiment, the orthogonal fixing module further includes an intermediate fixing plate, and the arm fixing ring and the connecting pipe fixing ring are respectively disposed on the upper and lower sides of the intermediate fixing plate.

[0016] In one embodiment, the first triangular frame includes a first corner connector for bringing the ends of two adjacent first connecting pipes close to each other; the mounting sleeve includes a first mounting sleeve disposed on the first corner connector and its centerline coincides with the angle bisector of the first included angle defined by the two first connecting pipes.

[0017] In one embodiment, the first corner connector includes a first upper mounting plate, a first lower mounting plate, and two sets of first connecting pipe fixing sleeves disposed between the first upper mounting plate and the first lower mounting plate. Each set of first connecting pipe fixing sleeves includes a pair of pipe clamps for inserting and fixing the first connecting pipe, and the pair of pipe clamps are concentrically arranged. The pair of pipe clamps includes a first pipe clamp and a second pipe clamp disposed opposite to each other along the axis of the first connecting pipe. The first pipe clamp includes a pair of half rings, and each half ring has connecting lugs at both ends connected by threaded connectors. The second pipe clamp includes a clamp plate, one side of which forms a break, and a pair of connecting lugs are connected to both ends of the break.

[0018] In one embodiment, a reinforcing clamp is provided on the side of the first mounting sleeve away from the arm where the rotor is mounted, and the reinforcing clamp is concentrically arranged with the first mounting sleeve.

[0019] In one embodiment, the second triangular frame includes a second corner connector, which includes a second upper mounting plate, a second lower mounting plate, a partition, and two sets of second connecting pipe fixing sleeves. The second upper mounting plate, the partition, and the second lower mounting plate are spaced apart to form an upper mounting space and a lower mounting space. The mounting sleeve includes a second mounting sleeve, which is disposed in the upper mounting space and its centerline coincides with the axis of symmetry of the upper mounting space. The two sets of second connecting pipe fixing sleeves are installed in the lower installation space with their center lines forming a second angle, and the angle bisector of the second angle is parallel to the center line of the second mounting sleeve.

[0020] In one embodiment, each set of second connecting pipe fixing sleeves includes a pair of pipe clamps for inserting and fixing the second connecting pipe. The pair of pipe clamps are concentrically arranged along the axis of the connecting pipe, and the angle bisector of the second included angle formed by the center lines of the two pairs of pipe clamps is parallel to the center line of the second mounting sleeve.

[0021] As a second aspect, an unmanned aerial vehicle is also provided, which includes the aforementioned flight platform.

[0022] The beneficial effects of the technical solution provided by this utility model are as follows: The flight platform of this utility model, by setting the mounting sleeve at the corner of the fuselage and making the mounting sleeve and the arm of the aircraft carbon fiber, can be modularly assembled, which reduces the weight of the unmanned aerial vehicle and facilitates the assembly of the frame. In addition, the shape and size of the carbon fiber frame can be adjusted as needed, thereby realizing the production of unmanned aerial vehicles of different shapes and sizes without the need to develop molds of different sizes, which greatly reduces the production cost. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of this utility model, the accompanying drawings used in the description of the embodiments of this utility model will be briefly introduced below.

[0024] Figure 1 This is a schematic diagram of the structure of a flight platform provided in one embodiment of the present invention; Figure 2 This is a schematic diagram of the structure of a first triangular frame provided in one embodiment of the present invention; Figure 3 This is a schematic diagram of the structure of the first corner connector provided in one embodiment of the present utility model; Figure 4 for Figure 3 A structural schematic diagram of the first corner connector from another perspective; Figure 5 This is a schematic diagram of the structure of the second triangular frame provided in one embodiment of the present invention; Figure 6This is a schematic diagram of the structure of the second corner connector provided in one embodiment of the present invention; Figure 7 This is a schematic diagram of the structure of an orthogonal fixing module provided in one embodiment of the present invention; Figure 8 A schematic diagram of the structure of an orthogonal fixing module provided in another embodiment of this utility model; Figure 9 This is a schematic diagram of the cross-fixing module provided in one embodiment of the present invention. Detailed Implementation

[0025] Embodiments of the present invention will now be described in more detail with reference to the accompanying drawings. While some embodiments of the present invention are shown in the drawings, it should be understood that the present invention can be implemented in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided to provide a more thorough and complete understanding of the present invention. It should be understood that the accompanying drawings and embodiments of the present invention are for illustrative purposes only and are not intended to limit the scope of protection of the present invention.

[0026] It should be understood that the steps described in the method embodiments of this utility model may be performed in different orders and / or in parallel. Furthermore, the method embodiments may include additional steps and / or omit the steps shown. The scope of this utility model is not limited in this respect.

[0027] The term "comprising" and its variations as used herein are open-ended, meaning "including but not limited to". The term "connection" can refer to a direct connection or an indirect connection via intermediate components (elements). The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments". Definitions of other terms will be given in the following description.

[0028] It should be noted that the concepts of "first" and "second" mentioned in this utility model are only used to distinguish between devices, modules or units, and are not used to limit these devices, modules or units to necessarily be different devices, modules or units, nor are they used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0029] See Figures 1 to 9 This invention provides a flight platform 10, suitable for use with rotors and flight control modules to form an unmanned aerial vehicle. The flight platform 10 of this invention is made of carbon fiber material, which achieves lightweighting while meeting structural strength requirements.

[0030] The flight platform 10 includes a fuselage, arms 13, and landing gear 14. The fuselage is hexagonal, with the arms connected to the corners of the fuselage and the landing gear connected to the lower side of the fuselage. The fuselage is formed by splicing two carbon fiber frames along the vertical direction, both of which are triangular. Each corner of the carbon fiber frame has a mounting sleeve, and the centerlines of all the mounting sleeves are coplanar. The arms are inserted into the corresponding mounting sleeves. The carbon fiber frames are made of carbon fiber material and are assembled from carbon fiber tubes and carbon fiber plates. Optionally, the arms are detachably mounted to the mounting sleeves to accommodate arms of different lengths depending on the fuselage size.

[0031] In one embodiment, the two-layer carbon fiber frame includes a first triangular frame and a second triangular frame. The first triangular frame includes multiple first connecting tubes connected end to end, and the second triangular frame includes multiple second connecting tubes connected end to end. Both the first and second connecting tubes are carbon fiber tubes and are connected by a cross-fixing module at the intersection of the first and second connecting tubes. The cross-fixing module is made of carbon fiber material.

[0032] It should be noted that the two triangular frames constituting the first triangular frame 11 and the second triangular frame 12 are generally triangular, but not strictly triangular in the strict sense, and their corners are not pointed. Additionally, it is understood that the landing gear 14 is also made of carbon fiber material to reduce the weight of the flight platform 10 while ensuring structural strength.

[0033] In one embodiment, the first triangular frame 11 includes three first corner connectors 111 and three first connecting pipes 112. The three first connecting pipes 112 are connected end to end to form a first triangle. The first corner connectors 111 are connected to the two first connecting pipes 112 at the corners of the first triangle. The mounting sleeve includes a first mounting sleeve 1113, which is disposed on the first corner connectors 111. Preferably, the first corner connectors 111 have an axisymmetric structure, and the centerline of the first mounting sleeve coincides with the axis of symmetry of the first corner connector. The middle part of the flight platform 10 has a hollow structure with a large space, which can be used to install functional components such as power modules and carriers, meeting the needs of unmanned aerial vehicles.

[0034] In one embodiment, the first corner connector 111 includes two sets of first connecting pipe fixing sleeves 1114. Each set of first connecting pipe fixing sleeves 1114 includes a pair of pipe clamps for inserting and fixing the first connecting pipe 112. The pair of pipe clamps are concentrically arranged, and the first included angle formed by the center lines of the two pairs of pipe clamps is matched with the angle of the corner end of the first triangle. The first mounting sleeve 1113 is located between the two sets of first connecting pipe fixing sleeves 1114 and its center line coincides with the angle bisector of the first included angle.

[0035] In one embodiment, the pair of pipe clamps includes a first pipe clamp 1115 and a second pipe clamp 1116 arranged opposite to each other along the axis of the first connecting pipe 112. The first pipe clamp 1115 includes a pair of half rings, and each half ring has connecting lugs (not shown, the same below) connected to each other by threaded connectors at both ends. The second pipe clamp 1116 includes a clamp plate (not shown, the same below), one side of which forms a break (not shown, the same below), and a pair of connecting lugs are connected to both ends of the break.

[0036] In this embodiment, the break (not shown) is located on the side of the hoop away from the first mounting sleeve 1113 to facilitate the screwing of the threaded connector.

[0037] In the above embodiments, the connecting pipe and the first corner connector 111 are fixed by the pipe clamp and clamp plate structure, which facilitates the assembly and disassembly of the connecting pipe and the first corner connector 111.

[0038] In other embodiments, the clamp can be replaced with a sleeve to fix the connecting pipe. Optionally, when a more secure connection is required, glue can be filled between the connecting pipe and the sleeve.

[0039] Please combine Figure 4 In one embodiment, a reinforcing clamp 1117 is provided on the side of the first mounting sleeve 1113 away from the arm 13 for mounting the rotor, and the reinforcing clamp 1117 is concentrically arranged with the first mounting sleeve 1113.

[0040] In one embodiment, the first triangular frame 11 further includes a first upper mounting plate 1111 and a first lower mounting plate 1112, which are arranged parallel to each other vertically. The first connecting pipe fixing sleeve 1114, the first mounting sleeve 1113 and the reinforcing pipe clamp 1117 are all fixed between the first upper mounting plate 1111 and the first lower mounting plate 1112.

[0041] In this embodiment, the first upper mounting plate and the first lower mounting plate can position the relative positions of the first pipe clamp 1115 and the second pipe clamp 1116, and can also strengthen the pipe clamps.

[0042] In one embodiment, the second triangular frame 12 includes three second corner connectors 121 and three second connecting pipes 122. The three second connecting pipes 122 are connected end-to-end to form a second triangle. The second corner connectors 121 are connected to the two second connecting pipes 122 at the corners of the second triangle. The mounting sleeve includes a second mounting sleeve 1214, which is disposed on the second corner connectors 121. Preferably, the second corner connectors 121 have an axisymmetric structure, and the centerline of the second mounting sleeve coincides with the axis of symmetry of the second corner connector.

[0043] In one embodiment, the second corner connector 121 includes a second upper mounting plate 1211, a second lower mounting plate 1213, a partition 1212, and two sets of second connecting pipe fixing sleeves 1215. The second upper mounting plate, the partition, and the second lower mounting plate are spaced apart to form an upper mounting space and a lower mounting space. The second mounting sleeve is disposed in the upper mounting space and its centerline coincides with the axis of symmetry of the upper mounting space. The two sets of second connecting pipe fixing sleeves are disposed in the lower mounting space with their centerlines forming a second included angle. The angle bisector of the second included angle is parallel to the centerline of the second mounting sleeve.

[0044] In one embodiment, each set of second connecting pipe fixing sleeves includes a pair of pipe clamps for inserting and fixing the second connecting pipe 122. The pair of pipe clamps are concentrically arranged along the axis of the connecting pipe, and the angle bisector of the second included angle formed by the center lines of the two pairs of pipe clamps is parallel to the center line of the second mounting sleeve.

[0045] Similarly, the second upper mounting plate, the second lower mounting plate, and the partition plate can position the relative positions of the first and second pipe clamps in the second connecting pipe fixing sleeve, and can also strengthen the pipe clamps.

[0046] In one embodiment, the arm 13 is provided as an arm extension at the end away from the mounting sleeve, the arm extension extending above another triangular frame and perpendicular to the nearest connecting tube of the other triangular frame.

[0047] Please combine Figure 7 The machine body also includes an orthogonal fixing module 15, which includes a middle mounting plate 150 and a machine arm fixing ring 151 and a connecting pipe fixing ring 152 respectively disposed on the upper and lower sides of the middle mounting plate 150. The machine arm fixing ring 151 and the connecting pipe fixing ring 152 are used to fix the machine arm extension and the connecting pipe respectively, and their central axes are perpendicular to each other.

[0048] In this embodiment, by setting an orthogonal fixing module 15 to connect the arm extension and the connecting pipe, the stability of the connection between the two triangular frames is further improved, thereby enhancing the structural strength of the flight platform 10.

[0049] Please combine Figure 8 In another embodiment, the arm extension extends to the front end of the connecting pipe closest to another triangular frame and is connected by another orthogonal fixing module 15'. This orthogonal fixing module does not have an intermediate mounting plate, and the center lines of its arm fixing ring 151' and connecting pipe fixing ring 152' are perpendicular to each other.

[0050] Please combine Figure 9 In one embodiment, the fuselage further includes a cross-fixing module 16, which includes a middle mounting plate 160 and a first connecting pipe fixing ring 161 and a second connecting pipe fixing ring 162 respectively disposed on the upper and lower sides of the middle mounting plate 160. A pair of first connecting pipe fixing rings 161 and second connecting pipe fixing rings 162 are provided, respectively for fixing the first connecting pipe 112 and the second connecting pipe 122, and the included angle between the central axes of the first connecting pipe fixing rings 161 and the second connecting pipe fixing rings 162 is matched with the included angle between the first connecting pipe 112 and the second connecting pipe 122. Thus, by setting the cross-fixing module 16 to connect the first connecting pipe 112 and the second connecting pipe 122, the connection of the two triangular frames is achieved, eliminating the need for welding fixation of the flight platform fuselage, improving assembly efficiency, and reducing production costs. Preferably, both the first connecting pipe fixing rings 161 and the second connecting pipe fixing rings 162 are constructed by connecting two semi-rings along the height direction using threaded connectors.

[0051] This invention relates to a flight platform formed by stacking two triangular frames vertically (i.e., splicing them together in the height direction). This modular design allows for easy production and assembly of the flight platform 10. Furthermore, the size of the triangular frames can be adjusted as needed to produce unmanned aerial vehicle (UAV) flight platforms 10 of different sizes, eliminating the need to develop molds of varying dimensions and significantly reducing production costs. The two triangular frames are secured by intersecting fixing modules, and the arms are installed to the triangular frames using mounting sleeves and fastened with orthogonal fixing modules. The entire flight platform requires no welding, simplifying the assembly process and saving costs.

[0052] As a second aspect, the present invention also provides an unmanned aerial vehicle, which includes the aforementioned flight platform 10, six rotors (not shown) and a flight control module (not shown). The six rotors are installed one-to-one on each of the arms 13, and the flight control module is installed on the fuselage and used to control the working state of the rotors.

[0053] The above description is merely a preferred embodiment of this utility model and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of this utility model 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 of the utility model in this utility model that have similar functions.

[0054] Although the subject matter has been described using language specific to structural features and / or methodological logic, it should be understood that the subject matter defined in the appended claims is not necessarily limited to the specific features or actions described above. Rather, the specific features and actions described above are merely illustrative examples of implementing the claims.

Claims

1. A flight platform comprising a fuselage and a plurality of arms, the fuselage being hexagonal, the arms being connected to the corners of the fuselage, characterized in that, Each of the six corners of the machine body is provided with a mounting sleeve, and the machine arms are detachably inserted into the mounting sleeves one by one. The machine arms and the mounting sleeves are all carbon fiber tubes, and the center lines of each mounting sleeve are arranged in the same plane.

2. The flight platform according to claim 1, characterized in that, The fuselage is formed by splicing together a first triangular frame and a second triangular frame with staggered corners, and each triangular frame is provided with a mounting sleeve at its corner.

3. The flight platform according to claim 2, characterized in that, The first triangular frame includes multiple first connecting tubes connected end to end, and the second triangular frame includes multiple second connecting tubes connected end to end. The positions where the first connecting tubes and the second connecting tubes intersect are connected by a cross-fixing module, which is made of carbon fiber material.

4. The flight platform according to claim 3, characterized in that, The cross-fixing module includes an intermediate mounting plate and a first connecting pipe fixing ring and a second connecting pipe fixing ring disposed on the upper and lower sides of the intermediate mounting plate, respectively. The first connecting pipe fixing ring and the second connecting pipe fixing ring are used to fix the first connecting pipe and the second connecting pipe, and the included angle between the central axes of the first connecting pipe fixing ring and the second connecting pipe fixing ring is matched with the included angle between the first connecting pipe and the second connecting pipe.

5. The flight platform according to claim 3, characterized in that, The arm extension is defined as the part of the arm that passes through the mounting sleeve at the end away from the end used to install the rotor. The arm extension is perpendicular to the connecting pipe located on another frame and the nearest one, and is connected to it by an orthogonal fixing module.

6. The flight platform according to claim 5, characterized in that, The orthogonal fixing module includes a boom fixing ring and a connecting pipe fixing ring, which are used to fix the boom extension and the connecting pipe respectively, and their central axes are perpendicular to each other.

7. The flight platform according to claim 6, characterized in that, The orthogonal fixing module also includes an intermediate fixing plate, and the arm fixing ring and the connecting pipe fixing ring are respectively located on the upper and lower sides of the intermediate fixing plate.

8. The flight platform according to claim 3, characterized in that, The first triangular frame includes a first corner connector, which is used to bring the ends of two adjacent first connecting pipes closer to each other; The mounting sleeve includes a first mounting sleeve, which is disposed on the first angle connector and its centerline coincides with the angle bisector of the first included angle defined by the two first connecting pipes.

9. The flight platform according to claim 8, characterized in that, The first corner connector includes a first upper mounting plate, a first lower mounting plate, and two sets of first connecting pipe fixing sleeves disposed between the first upper mounting plate and the first lower mounting plate. Each set of first connecting pipe fixing sleeves includes a pair of pipe clamps for inserting and fixing the first connecting pipe, and the pair of pipe clamps are concentrically arranged. The pair of pipe clamps includes a first pipe clamp and a second pipe clamp arranged opposite to each other along the axis of the first connecting pipe. The first pipe clamp includes a pair of half rings, and each half ring has connecting lugs at both ends connected by threaded connectors. The second pipe clamp includes a clamp plate, one side of which forms a break, and a pair of connecting lugs are connected to both ends of the break.

10. The flight platform according to claim 8, characterized in that, A reinforcing clamp is provided on the side of the first mounting sleeve away from the arm where the rotor is mounted, and the reinforcing clamp is concentrically arranged with the first mounting sleeve.

11. The flight platform according to claim 3, characterized in that, The second triangular frame includes a second corner connector, which includes a second upper mounting plate, a second lower mounting plate, a partition, and two sets of second connecting pipe fixing sleeves. The second upper mounting plate, the partition, and the second lower mounting plate are spaced apart to form an upper mounting space and a lower mounting space. The mounting sleeve includes a second mounting sleeve, which is disposed within the upper mounting space and whose centerline coincides with the axis of symmetry of the upper mounting space. The two sets of second connecting pipe fixing sleeves are installed in the lower installation space with their center lines forming a second angle, and the angle bisector of the second angle is parallel to the center line of the second mounting sleeve.

12. The flight platform according to claim 11, characterized in that, Each set of second connecting pipe fixing sleeves includes a pair of pipe clamps for inserting and fixing the second connecting pipe. The pair of pipe clamps are concentrically arranged along the axis of the connecting pipe, and the angle bisector of the second included angle formed by the center lines of the two pairs of pipe clamps is parallel to the center line of the second mounting sleeve.

13. An unmanned aerial vehicle, characterized in that, Includes the flight platform described in any one of claims 1 to 12.

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