Arm fixing assembly and multi-rotor unmanned aerial vehicle

Abstract

The invention provides an arm fixing assembly and a multi-rotor unmanned aerial vehicle. The arm fixing assembly comprises a single-layer fixing part and a plurality of layers of fixing parts. The single-layer fixing piece comprises a first connecting rod sleeve and a first machine arm mounting part which are uniformly distributed in a first height space, the first connecting rod sleeve is used for being connected with a connecting rod in the first height space to form a first polygonal frame, and the first machine arm mounting part is used for mounting a machine arm of the first polygonal frame; the multiple layers of fixing pieces comprise second connecting rod sleeves distributed in the second height space and second arm mounting parts distributed in the first height space, and the second connecting rod sleeves are used for being connected with connecting rods distributed in the second height space to form a second polygonal frame; and the second arm mounting part is used for mounting the arms of the second polygonal frame and enabling the arms of the fuselage to be located on the same horizontal plane, so that the unmanned aerial vehicle is convenient to assemble, and the production efficiency is improved.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to an arm fixing assembly and a multi-rotor UAV. 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. Summary of the Invention

[0008] The purpose of this invention is to provide an arm fixing assembly applicable to the assembly of multi-rotor drone fuselages, in order to solve at least one of the above-mentioned technical problems.

[0009] To achieve the above objectives, the present invention provides the following technical solution: This invention provides an arm fixing assembly for use in the fuselage of a multi-rotor unmanned aerial vehicle (UAV) and for mounting and fixing the arm. The assembly includes a single-layer fixing component and multiple layers of fixing components. The single-layer fixing component includes a first connecting rod sleeve and a first arm mounting portion, both distributed in a first height space. The first connecting rod sleeve is used to connect with connecting rods in the first height space to form a first polygonal frame, and the first arm mounting portion is used to mount the arm of the first polygonal frame. The multiple layers of fixing components include a second connecting rod sleeve distributed in a second height space and a second arm mounting portion distributed in the first height space. The second height space has a different height than the first height space. The second connecting rod sleeve is used to connect with connecting rods distributed in the second height space to form a second polygonal frame, and the second arm mounting portion is used to mount the arm of the second polygonal frame, ensuring that the centerline of the arm of the second polygonal frame is at the same horizontal plane as the centerline of the arm of the first polygonal frame.

[0010] In one embodiment, the first connecting rod sleeve is provided in two sets, each set of first connecting rod sleeves is used to fix the end of a connecting rod, and the center lines of the two sets of first connecting rod sleeves are set at a first included angle; the first arm mounting part includes a first mounting sleeve, and the center line of the first mounting sleeve coincides with the angle bisector of the first included angle.

[0011] In one embodiment, the second connecting rod sleeve is provided in two sets, each set of the second connecting rod sleeve is used to fix the end of a connecting rod, the center lines of the two sets of the second connecting rod sleeve are set at a second included angle, the angle value of the second included angle is equal to that of the first included angle; the second arm fixing part includes a second mounting sleeve, the center line of the second mounting sleeve coincides with the angle bisector of the second included angle.

[0012] In one embodiment, the centerline of the second mounting sleeve is on the same horizontal plane as the centerline of the first mounting sleeve.

[0013] In one embodiment, the single-layer fastener includes a first upper mounting plate and a first lower mounting plate spaced apart, the first connecting rod sleeve and the first mounting sleeve are both disposed between the first upper mounting plate and the first lower mounting plate, and two sets of first connecting rod sleeves are distributed on both sides of the first mounting sleeve.

[0014] In one embodiment, each set of first connecting rod sleeves includes a pair of clamps, the pair of clamps including a first clamp and a second clamp arranged coaxially, the first clamp including a pair of half rings, each half ring having connecting lugs at both ends connected by threaded connectors; the second clamp including a clamp plate, one side of the clamp plate forming a break, and a pair of connecting lugs connected to both ends of the break.

[0015] In one embodiment, a reinforcing clamp is provided at one end of the first mounting sleeve located inside the machine body, and the reinforcing clamp is coaxially arranged with the first mounting sleeve.

[0016] In one embodiment, the plurality of fixing members includes a second upper mounting plate, a second lower mounting plate, and a partition plate. The second upper mounting plate, the partition plate, and the second lower mounting plate are spaced apart to form a first mounting cavity and a second mounting cavity. The first mounting cavity and the second mounting cavity are correspondingly disposed within a first height space and a second height space. The second mounting sleeve is disposed within the first mounting cavity, and its centerline coincides with the axis of symmetry of the first mounting cavity. The two sets of second connecting rod sleeves are disposed within the second mounting cavity at a second included angle with their centerlines, and the angle bisector of the second included angle is parallel to the centerline of the second mounting sleeve.

[0017] In one embodiment, each set of second connecting rod sleeves includes a pair of clamps for inserting and fixing the second connecting rod. The clamps include a first clamp and a second clamp arranged coaxially. The first clamp includes a pair of half rings, and each half ring has connecting lugs at both ends connected by threaded connectors. The second 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, both the single-layer fastener and the multiple-layer fastener are made of carbon fiber material.

[0019] As a second aspect, the present invention also provides a multi-rotor unmanned aerial vehicle (UAV), including a polygonal fuselage, a plurality of arms connected to each corner of the fuselage, a plurality of rotors connected to each arm, and the aforementioned arm fixing components; the polygonal fuselage includes a first polygonal frame and a second polygonal frame, the first polygonal frame and the second polygonal frame being spliced ​​together in a vertical direction with staggered corners, the first polygonal frame having the single-layer fixing component, and the second polygonal frame having the plurality of fixing components.

[0020] The beneficial effects of the technical solution provided by this invention are as follows: The arm fixing assembly of this invention uses a combination of single-layer fixing parts and multiple-layer fixing parts. The two types of fixing parts are used for the assembly of the fuselage frame at different heights, and the center lines of each arm are in the same horizontal plane, which allows the UAV to be stacked and modularly assembled, facilitating 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 UAVs of different shapes and sizes without the need to develop molds of different sizes, which greatly reduces the production cost. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments of the present invention will be briefly introduced below.

[0022] Figure 1 This is a schematic diagram of the structure of a multi-rotor unmanned aerial vehicle provided in one embodiment of the present invention; Figure 2 This is a schematic diagram of the structure of a first polygonal frame provided in one embodiment of the present invention; Figure 3 This is a schematic diagram of the structure of a single-layer fastener provided in one embodiment of the present invention; Figure 4 for Figure 3 A structural schematic diagram of the single-layer fastener from another perspective; Figure 5 This is a schematic diagram of the structure of a second polygonal frame provided in one embodiment of the present invention; Figure 6 This is a schematic diagram of the structure of a multi-layered fastener provided in one embodiment of the present invention. Detailed Implementation

[0023] Embodiments of the present invention will now be described in more detail with reference to the accompanying drawings. While some embodiments of the invention are shown in the drawings, it should be understood that the 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 invention. It should be understood that the accompanying drawings and embodiments are for illustrative purposes only and are not intended to limit the scope of protection of the invention.

[0024] It should be understood that the various steps described in the method embodiments of the present invention 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 the present invention is not limited in this respect.

[0025] 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.

[0026] It should be noted that the concepts of "first" and "second" mentioned in this invention are only used to distinguish between devices, modules or units, and are not intended to limit these devices, modules or units to necessarily be different devices, modules or units, nor are they intended to limit the order or interdependence of the functions performed by these devices, modules or units.

[0027] See Figures 1 to 6 The present invention provides an arm fixing component and a multi-rotor drone using the arm fixing component. The multi-rotor drone is characterized by modular assembly and light weight.

[0028] The multi-rotor UAV includes a polygonal fuselage 10, multiple arms 20, and multiple rotors corresponding to the number of arms 20. The polygonal fuselage 10 is evenly provided with multiple corner ends, the multiple arms 20 are distributed one-to-one at the corner ends of the polygonal fuselage 10, and the rotors are disposed one-to-one at the end of the arms 20 away from the fuselage.

[0029] The polygonal fuselage 10 is formed by splicing two polygonal frames together vertically. Taking a hexagonal UAV as an example, the fuselage is hexagonal, composed of two equilateral triangular frames stacked together with their corners offset (stacked and spliced ​​vertically). It can be understood that the two triangular frames are located in different height spaces. For ease of explanation, the upper space is defined as the first height space, the lower space as the second height space, the triangular frame located in the first height space is the first polygonal frame 11, and the triangular frame located in the second height space is the second polygonal frame 12.

[0030] The first polygonal frame 11 is formed by connecting three first connecting rods 112 and three single-layer fasteners 111. The three first connecting rods 112 are connected end to end by the single-layer fasteners 111 to form an equilateral triangular frame.

[0031] The single-layer fixing component 111 includes a first connecting rod sleeve 1114 and a first arm mounting part evenly distributed in the first height space. The first connecting rod sleeve 1114 is used to connect with the connecting rod (i.e. the first connecting rod 112) in the first height space to form a first polygonal frame 11. The first arm mounting part is used to install the arm 20 of the first polygonal frame 11.

[0032] In one embodiment, the first connecting rod sleeve 1114 is provided in two sets, each set of the first connecting rod sleeve 1114 is used to fix the end of a connecting rod, and the center lines of the two sets of the first connecting rod sleeve 1114 are set at a first included angle; the first arm mounting part includes a first mounting sleeve 1113, and the center line of the first mounting sleeve 1113 coincides with the angle bisector of the first included angle.

[0033] In one embodiment, the single-layer fastener 111 includes a first upper mounting plate 1111 and a first lower mounting plate 1112 spaced apart, the first connecting rod sleeve 1114 and the first mounting sleeve 1113 are both disposed between the first upper mounting plate 1111 and the first lower mounting plate 1112, and two sets of first connecting rod sleeves 1114 are distributed on both sides of the first mounting sleeve 1113.

[0034] In one embodiment, each set of first connecting rod sleeves 1114 includes a pair of clamps, the pair of clamps including a first clamp and a second clamp arranged coaxially, the first clamp including a pair of half rings 1115, each half ring having connecting lugs at both ends connected by threaded connectors; the second clamp including a clamp plate 1116, one side of the clamp plate forming a break, and a pair of connecting lugs connected to both ends of the break.

[0035] In one embodiment, a reinforcing clamp 1117 is provided at one end of the first mounting sleeve 1113 located inside the machine body, and the reinforcing clamp 1117 is coaxially arranged with the first mounting sleeve 1113.

[0036] The second polygonal frame 12 is formed by connecting three second connecting rods 122 and three multiple layers of fixing members 121. The three second connecting rods 122 are connected end to end through the multiple layers of fixing members 121, thereby forming an equilateral triangle frame.

[0037] The multiple-layer fixing member 121 includes a second connecting rod sleeve 1215 distributed in the second height space and a second arm mounting part distributed in the first height space. The second connecting rod sleeve 1215 is used to connect with the connecting rod (i.e., the second connecting rod 122) distributed in the second height space to form a second polygonal frame 12. The second arm mounting part is used to install the arm 20 of the second polygonal frame 12 and make the center line of the arm 20 of the second polygonal frame 12 and the center line of the arm 20 of the first polygonal frame 11 at the same horizontal plane.

[0038] In this embodiment, multiple layers of fasteners 121 and single-layer fasteners 111 are alternately distributed at the corners of the fuselage.

[0039] In one embodiment, the second connecting rod sleeve 1215 is provided in two sets, each set of the second connecting rod sleeve 1215 is used to fix the end of a connecting rod, and the center lines of the two sets of the second connecting rod sleeve 1215 are set at a second included angle, the angle value of the second included angle is equal to that of the first included angle; the second arm fixing part includes a second mounting sleeve 1214, the center line of the second mounting sleeve 1214 coincides with the angle bisector of the second included angle.

[0040] In one embodiment, the centerline of the second mounting sleeve 1214 is on the same horizontal plane as the centerline of the first mounting sleeve 1113.

[0041] In one embodiment, the plurality of fixing members 121 includes a second upper mounting plate 1211, a second lower mounting plate 1213, and a partition plate 1212. The second upper mounting plate 1211, the partition plate 1212, and the second lower mounting plate 1213 are spaced vertically to form a first mounting cavity and a second mounting cavity. The first mounting cavity and the second mounting cavity are correspondingly disposed within a first height space and a second height space. The second mounting sleeve 1214 is disposed in the first mounting cavity and its centerline coincides with the axis of symmetry of the first mounting cavity. The two sets of second connecting rod sleeves 1215 are disposed in the second mounting cavity with their centerlines forming a second included angle, and the angle bisector of the second included angle is parallel to the centerline of the second mounting sleeve 1214.

[0042] In one embodiment, each set of second connecting rod sleeves 1215 includes a pair of clamps for inserting and fixing the second connecting rod 122. The clamps include a first clamp and a second clamp arranged coaxially. The first clamp includes a pair of half rings, and each half ring has connecting lugs at both ends connected by threaded connectors. The second 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.

[0043] In this invention, by setting a semi-circular pipe clamp and a clamp plate to cooperate, the insertion and locking of the connecting rod is facilitated, thereby facilitating the assembly of the machine body and improving assembly efficiency.

[0044] In this invention, the fuselage is composed of multiple connecting rods and an arm fixing assembly. The connecting rods can be made of tubular material, resulting in a relatively lightweight fuselage. Furthermore, the single-layer fixing component 111, the multiple-layer fixing components 121, the first connecting rod 112, the second connecting rod 122, and the arm 20 are all made of carbon fiber material. This reduces the weight of the drone while maintaining its structural strength, thereby improving its endurance.

[0045] The beneficial effects of the technical solution provided by this invention are as follows: The arm fixing assembly of this invention uses a combination of single-layer fixing parts and multiple-layer fixing parts. The two types of fixing parts are used for the assembly of the fuselage frame at different heights, and the center lines of each arm are in the same horizontal plane, which allows the UAV to be stacked and modularly assembled, facilitating 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 UAVs of different shapes and sizes without the need to develop molds of different sizes, which greatly reduces the production cost.

[0046] 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.

[0047] 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. An arm mounting assembly for use in the fuselage of a multi-rotor unmanned aerial vehicle (UAV) and for mounting and fixing the arm, characterized in that, include: Single-layer fasteners and multi-layer fasteners; The single-layer fixing component includes a first connecting rod sleeve and a first arm mounting part evenly distributed in the first height space. The first connecting rod sleeve is used to connect with the connecting rod in the first height space to form a first polygonal frame, and the first arm mounting part is used to install the arm of the first polygonal frame. The multiple-layer fixing components include a second connecting rod sleeve distributed in a second height space and a second arm mounting part distributed in a first height space. The second height space and the first height space have different heights. The second connecting rod sleeve is used to connect with the connecting rods distributed in the second height space to form a second polygonal frame. The second arm mounting part is used to install the arm of the second polygonal frame and make the center line of the arm of the second polygonal frame and the center line of the arm of the first polygonal frame at the same horizontal plane.

2. The arm fixing assembly according to claim 1, characterized in that, The first connecting rod sleeve is provided in two sets, each set of first connecting rod sleeves is used to fix the end of a connecting rod, and the center lines of the two sets of first connecting rod sleeves are set at a first included angle; The first arm mounting part includes a first mounting sleeve, the center line of which coincides with the angle bisector of the first included angle.

3. The arm fixing assembly according to claim 2, characterized in that, The second connecting rod sleeve is provided in two sets. Each set of the second connecting rod sleeve is used to fix the end of a connecting rod. The center lines of the two sets of the second connecting rod sleeve are set at a second included angle, and the angle value of the second included angle is equal to that of the first included angle. The second arm fixing part includes a second mounting sleeve, the center line of which coincides with the angle bisector of the second included angle; The centerline of the second mounting sleeve is on the same horizontal plane as the centerline of the first mounting sleeve.

4. The arm fixing assembly according to claim 3, characterized in that, The single-layer fastener includes a first upper mounting plate and a first lower mounting plate spaced apart. The first connecting rod sleeve and the first mounting sleeve are both located between the first upper mounting plate and the first lower mounting plate, and two sets of first connecting rod sleeves are distributed on both sides of the first mounting sleeve.

5. The arm fixing assembly according to claim 4, characterized in that, Each set of first connecting rod sleeves includes a pair of pipe clamps, the pair of pipe clamps including a first pipe clamp and a second pipe clamp arranged coaxially, the first pipe clamp including a pair of half rings, each half ring having connecting lugs at both ends connected by threaded connectors; the second pipe clamp including a clamp plate, one side of the clamp plate forming a break, and a pair of connecting lugs connected to both ends of the break.

6. The arm fixing assembly according to claim 4, characterized in that, The first mounting sleeve has a reinforcing pipe clamp at one end located inside the machine body, and the reinforcing pipe clamp is coaxially arranged with the first mounting sleeve.

7. The arm fixing assembly according to claim 3, characterized in that, The multiple-layer fastener includes a second upper mounting plate, a second lower mounting plate, and a partition. The second upper mounting plate, the partition, and the second lower mounting plate are spaced apart to form a first mounting cavity and a second mounting cavity. The first mounting cavity and the second mounting cavity are respectively disposed in a first height space and a second height space. The second mounting sleeve is disposed inside the first mounting cavity and its center line coincides with the axis of symmetry of the first mounting cavity; The two sets of second connecting rod sleeves are arranged in the second mounting cavity at a second included angle with their center lines, and the angle bisector of the second included angle is parallel to the center line of the second mounting sleeve.

8. The arm fixing assembly according to claim 7, characterized in that, Each set of second connecting rod sleeves includes a pair of clamps for inserting and fixing the second connecting rod. The clamps include a first clamp and a second clamp arranged coaxially. The first clamp includes a pair of half rings, and each half ring has connecting lugs at both ends connected by threaded connectors. The second 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.

9. The arm fixing assembly according to claim 1, characterized in that, Both the single-layer and multi-layer fasteners are made of carbon fiber.

10. A multi-rotor unmanned aerial vehicle (UAV), comprising a polygonal fuselage, multiple arms connected to each corner of the fuselage, and multiple rotors connected to each arm, characterized in that, It also includes the arm fixing assembly as described in any one of claims 1 to 9; The polygonal body includes a first polygonal frame and a second polygonal frame. The first polygonal frame and the second polygonal frame are spliced ​​together in the vertical direction with their corners staggered. The first polygonal frame has the single-layer fastener, and the second polygonal frame has the multiple layers of fasteners.

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