An integrated boom for heavy-lift drones

Abstract

The utility model discloses a kind of integrated type supporting arm for heavy load unmanned plane, belong to unmanned plane technical field, the integrated type supporting arm includes supporting arm piece, the end of supporting arm piece is connected with fuselage assembly, the end of supporting arm piece away from fuselage assembly is connected with electric push system, electric push system can provide the thrust required for unmanned plane to hover and fly, installation slot is opened in supporting arm piece, fixed part is equipped in the installation slot of supporting arm piece, fixed part is used to install and fix electric governor, fixed part and electric governor do not protrude from supporting arm piece, to reduce wind resistance while electric governor radiates heat, maintenance opening is opened in supporting arm piece, to maintain electric governor when maintenance opening is opened.The utility model inlay electric governor and fixed part in supporting arm piece, and ensure flush with supporting arm piece outer wall, to significantly reduce the air resistance when unmanned plane flies, to improve flight efficiency, increase endurance range and effective load.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) technology, and in particular relates to an integrated support arm for heavy-duty UAVs. Background Technology

[0002] With the rapid development of drone technology, its application in logistics transportation, emergency rescue, agricultural plant protection and other fields is becoming increasingly widespread, which puts forward higher requirements for the payload capacity and flight performance of drones. Heavy-load drones need to carry a large amount of payload, so the power and heat dissipation requirements of their power system (usually including motors, ESCs, propellers, etc.) are also significantly increased.

[0003] In traditional drone designs, the electronic speed controller (ESC) is typically mounted externally on the fuselage or boom. While this layout facilitates installation and heat dissipation, it also presents significant problems: First, the protruding ESC and its cables significantly increase the drone's aerodynamic drag, affecting flight efficiency and endurance. Second, externally mounted ESCs are highly susceptible to impacts, scratches, or rain damage in complex operating environments, reducing reliability. Furthermore, the messy external wiring not only affects aesthetics but also increases maintenance complexity.

[0004] To address these issues, some existing technologies have incorporated electronic speed controllers (ESCs) into the boom arm to reduce wind resistance and protect electronic equipment. However, these designs are often imperfect. For example, simple internal integration may lead to poor heat dissipation due to a loose connection between the ESC and the boom structure. The significant heat generated by the ESC during operation cannot be dissipated in time, severely impacting its operational stability and lifespan. Furthermore, internal ESCs greatly complicate routine inspections, troubleshooting, and replacement maintenance, often requiring the disassembly of numerous components to access the ESC, resulting in low maintenance efficiency.

[0005] Therefore, there is an urgent need to design an integrated outrigger for heavy-duty drones to solve the problems mentioned above. Utility Model Content

[0006] The purpose of this invention is to provide an integrated support arm for heavy-duty drones, which has the advantages of perfectly solving the heat dissipation and convenient maintenance requirements without sacrificing aerodynamic performance, thus solving the problems mentioned in the background art.

[0007] To achieve the above objectives, the specific technical solution of this utility model for an integrated support arm for heavy-duty unmanned aerial vehicles is as follows: An integrated support arm for a heavy-duty UAV includes an arm component. One end of the arm component is connected to the fuselage assembly, and the end of the arm component away from the fuselage assembly is connected to an electric propulsion system. The electric propulsion system provides the thrust required for hovering and flight of the UAV. The arm component has an ESC mounting opening, and a fixing member is provided inside the ESC mounting opening for mounting and fixing the ESC. The fixing member and the ESC do not protrude beyond the arm component to reduce wind resistance while allowing the ESC to dissipate heat. The arm component has a maintenance opening with an arm cover. The arm cover can open and close the maintenance opening to maintain the ESC when the maintenance opening is open.

[0008] Furthermore, the fasteners and electric controllers are flush with the outrigger components.

[0009] Furthermore, the fastener includes a fixed bracket and a reinforcing frame. The fixed bracket has an installation port adapted to the power regulator, and both ends of the fixed bracket are fixedly connected to the reinforcing frame.

[0010] Furthermore, the reinforcing frame is set along the longitudinal direction of the support arm, and the shape of the reinforcing frame is the same as the shape of the longitudinal section of the support arm.

[0011] Furthermore, the fixed bracket includes a fixed part and an extension part, the fixed part and the extension part are fixedly connected, the mounting port is opened in the fixed part and the extension part, the extension part is adapted to the ESC mounting port, and when the extension part extends beyond the ESC mounting opening, the extension part is flush with the outer wall of the support arm.

[0012] Furthermore, the fixing part is larger than the ESC mounting opening, and when the extension part extends beyond the ESC mounting opening, the fixing part fits against the inner wall of the support arm.

[0013] Furthermore, an installation groove is provided inside the outrigger component, and the fixing component is limited within the outrigger component through the installation groove.

[0014] Furthermore, the outrigger assembly includes two outrigger skins, which together form the outrigger assembly. Mounting slots are provided on both outrigger skins, and maintenance openings are provided on either outrigger skin.

[0015] Furthermore, a connecting joint is fixedly connected to the outrigger assembly, and the outrigger assembly is connected to the outrigger joint of the fuselage assembly through the connecting joint.

[0016] Furthermore, a motor mounting base is connected to the end of the outrigger assembly away from the fuselage assembly, and the electric propulsion system is mounted on the motor mounting base.

[0017] This utility model has the following advantages: by embedding the ESC and fixing parts inside the support arm and ensuring that they are flush with the outer wall of the support arm, the air resistance during the flight of the UAV is significantly reduced, thereby improving flight efficiency, increasing range and payload. Moreover, when the ESC needs to be inspected, adjusted or replaced, there is no need to disassemble the entire support arm or damage the main structure. The operation can be carried out directly by simply opening the support arm cover. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the overall structure of the heavy-duty multi-rotor UAV of this utility model. Figure 2 This is a structural schematic diagram of the top and middle engine compartments of this utility model; Figure 3 This is a schematic diagram of the bottom engine compartment of this utility model; Figure 4 This is a schematic diagram of the structure of the cabin skin of this utility model; Figure 5 This is a schematic diagram of the structure of the first equipment cover, flight control maintenance cover, nose cover and air intake grille of this utility model; Figure 6 This is a schematic diagram of the structure of the second device opening cover and the opening cover of this utility model; Figure 7 This is a schematic diagram of the connecting skin structure of this utility model; Figure 8 This is a schematic diagram of the hanging system of this utility model; Figure 9 This is a schematic diagram of the structure inside the top cabin of this utility model; Figure 10 This is a structural schematic diagram of the top partition and reinforcing member of this utility model; Figure 11 This is a structural schematic diagram of the fuselage frame, partition, and top partition of this utility model; Figure 12 This is a schematic diagram of the structure inside the middle cabin of this utility model; Figure 13 This is a structural schematic diagram of the longitudinal beam and landing gear assembly of this utility model; Figure 14 This is a schematic diagram of the support arm assembly of this utility model; Figure 15 This is a schematic diagram of the structure of the support arm, connecting joint, and motor mounting base of this utility model; Figure 16 This is an exploded structural diagram of the support arm and fixing component of this utility model; Figure 17 This is a schematic diagram of the structure of the fastener of this utility model; Explanation of markings in the diagram: 1. Fuselage assembly; 11. Top cabin; 111. Top bulkhead; 1111. Straight section; 1112. Sloping section; 112. Reinforcing member; 1121. First reinforcing section; 1122. Second reinforcing section; 113. Boom joint; 114. Emergency power supply; 115. Airborne data link; 116. Flight management computer; 117. Aircraft pylon joint; 12. Mid-cabin; 121. Fuselage frame; 1211. Longitudinal beam; 1212. Mid-cabin bulkhead; 122. Floor; 124. High-voltage control box; 125. Fuse box; 126. Slide rail; 127. Battery; 13. Bottom cabin; 14. Bulkhead; 15. Cabin covering 1. Skin; 151. Left Skin; 152. Right Skin; 153. Nose Skin; 154. First Equipment Port Cover; 155. Flight Control Maintenance Port Cover; 156. Nose Port Cover; 157. Second Equipment Port Cover; 158. Opening Cover; 159. Air Intake Grille; 16. Connecting Skin; 2. Motor Support Arm Assembly; 21. Support Arm Component; 22. Connecting Joint; 23. Motor Mounting Mount; 24. Mounting Slot; 25. Electronic Controller; 26. Fixing Component; 261. Fixing Bracket; 2611. Fixing Part; 2612. Extension Part; 262. Reinforcing Frame; 263. Electronic Controller Mounting Port; 27. Motor; 28. Twin-bladed Propeller; 29. ​​Support Arm Port Cover; 3. Landing Gear Assembly. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0020] Those skilled in the art will understand that although some embodiments herein include certain features included in other embodiments but not others, combinations of features from different embodiments are intended to be within the scope of this invention and form different embodiments. For example, in the claims, any of the claimed embodiments can be used in any combination.

[0021] The following is a reference to the appendix. Figure 1 To be continued Figure 17 This invention describes an integrated support arm for heavy-duty unmanned aerial vehicles (UAVs).

[0022] The heavy-duty multi-rotor UAV includes fuselage assembly 1, motor arm assembly 2, and landing gear assembly 3.

[0023] The fuselage assembly system includes a nacelle skin 15, which has a partition 14 inside. The partition 14 divides the nacelle skin 15 into a top nacelle 11 and a middle nacelle 12. The nacelle skin 15 covers the top nacelle 11 and the middle nacelle 12. The nacelle skin 15 includes a left skin 151 and a right skin 152. The left skin 151 and the right skin 152 are separated by the fuselage symmetry plane. The left skin 151 is designed with a recess, and the right skin 152 rests on the recess of the left skin 151. The two are then fixed by a glued connection.

[0024] By using a recessed lap joint and adhesive riveting connection process for the left skin 151 and right skin 152, not only is the flatness of the skin joint ensured, which is beneficial to the aerodynamic shape, but the combination of the advantages of adhesive bonding and riveting also significantly improves the overall sealing, structural rigidity and connection reliability of the fuselage.

[0025] The fuselage assembly system also includes a bottom cabin 13, a top cabin 11, a middle cabin 12 and a bottom cabin 13 arranged sequentially from the top to the bottom of the UAV.

[0026] The modular three-section design of the fuselage assembly system realizes the physical separation and modularization of functions. The top section focuses on flight control, the middle section focuses on energy supply, and the bottom section focuses on mission payload. This design allows each module to be designed, tested, maintained and upgraded independently, which greatly improves R&D efficiency and maintenance convenience.

[0027] The top cabin 11 is equipped with a support assembly, which contains a flight management computer 116. The support assembly is connected to a boom joint 113, and the support assembly is connected to the motor boom assembly 2 through the boom joint 113.

[0028] The support assembly includes a top frame 111, which serves as the equipment installation space. The flight management computer 116 is located within the top frame 111. A reinforcing member 112 is provided within the top frame 111. An arm joint 113 is fixedly connected to the top frame 111. Specifically, the top frame 111 is octagonal and includes four straight sections 1111 and four inclined sections 1112. Both ends of each straight section 1111 are connected to the adjacent inclined section 1112, and both ends of each inclined section 1112 are connected to the adjacent straight section 1111. The arm joint 113 is connected to the inclined section 1112.

[0029] By designing the top frame 111 as an octagon, a robust load-bearing core is formed. Its geometry can efficiently convert the loads from the support arms from multiple directions into compressive and tensile stresses within the frame, avoiding stress concentration and providing excellent bending and torsional stiffness. At the same time, the support arm joint 113 is directly fixed to the inclined section 1112 of the top frame 111, rather than to the skin, so that the huge load from the motor support arm assembly 2 is directly transferred to the strongest core structure of the fuselage. The force flow path is clear and efficient, completely avoiding local instability and fatigue problems caused by connection to the thin skin, and significantly improving safety and lifespan.

[0030] Specifically, the bottom end of the top bulkhead 111 is fixedly connected to the bottom surface of the top cabin 11, that is, the bottom end of the top bulkhead 111 is fixedly connected to the bulkhead 14, and the top end of the top bulkhead 111 is fixedly connected to the top surface of the top cabin 11.

[0031] The reinforcing member 112 includes a first reinforcing part 1121 and a second reinforcing part 1122. Both the first reinforcing part 1121 and the second reinforcing part 1122 are fixedly connected inside the top partition 111. The first reinforcing part 1121 is arranged longitudinally along the top partition 111, and the shape of the first reinforcing part 1121 is the same as the shape of the longitudinal section of the top partition 111. The second reinforcing part 1122 is arranged transversely along the top partition 111, and the shape of the second reinforcing part 1122 is the same as the shape of the transverse section of the top partition 111. The first reinforcing part 1121 and the second reinforcing part 1122 form a three-dimensional, grid-like reinforcing structure, which divides the internal space of the top partition 111 into multiple stable areas, greatly enhancing the longitudinal and transverse stability of the top partition 111, preventing it from deforming due to huge loads, and providing an extremely stable and vibration-resistant installation environment for the flight management computer 116.

[0032] There are eight outrigger connectors 113. The eight outrigger connectors 113 are divided into four groups according to the motor outrigger. Each group consists of two adjacent outrigger connectors 113. The four groups of outrigger connectors 113 are symmetrical to each other. The motor outrigger is connected to the fuselage using a fork-ear connection structure. The outrigger connector 113 is designed as a double-ear connector. The bottom surface of the outrigger connector 113 is fixedly connected to the partition plate 14. The top surface of the outrigger connector 113 is fixedly connected to the nacelle skin 15. The side of the outrigger connector 113 is fixedly connected to the inclined section 1112 of the top partition frame 111. An aluminum plate is provided between each group of outrigger connectors 113 for fixing the arm cable separation socket.

[0033] The outrigger joint 113 is fixed to the bulkhead 14, the nacelle skin 15, and the top bulkhead 111 on three sides, forming a multi-path load transfer, which further enhances the reliability and stability of the connection. Furthermore, the modularization and standardization of cable management through the use of aluminum plates avoids mutual interference or wear of cables during vibration, improves system reliability, and facilitates installation and maintenance.

[0034] A connecting skin 16 is provided at the connection between the motor arm assembly 2 and the arm joint 113. The connecting skin 16 has a flanged structure at both the arm end and the fuselage end, which is used to connect with the arm skin and the fuselage skin respectively. It is arranged symmetrically on the left and right, with a total of four groups. Each fairing skin is divided into upper and lower parts, both of which are carbon fiber laminate structures and are detachable to cover the connection between the motor arm assembly 2 and the arm joint 113. The connecting skin 16 not only ensures excellent aerodynamic shape and reduces flight drag, but also facilitates the maintenance of the internal connection structure. The flanged design and the connection with the skin ensure the firmness and smoothness of the fairing itself.

[0035] Each set of boom joints 113 is fixedly connected to a whole-machine lifting joint 117. The whole-machine lifting joint 117 extends beyond the cabin skin 15 and can be connected to the hook of the crane through the whole-machine lifting joint 117, so that the UAV can be lifted and transported. The lifting joint is integrated into the set of boom joints 113, which cleverly utilizes the strongest structure of the fuselage to bear the load when the entire UAV is lifted.

[0036] The front end of the top nacelle 11 is provided with a nose skin 153. The lower end of the nose skin 153 is connected to the corresponding recessed area on the nacelle skin 15. The upper end of the nose skin 153 is connected to the motor support arm and the top bulkhead 111 respectively. Specifically, the fuselage skin is a carbon fiber laminate structure with a recess and an opening in the middle. A nose hatch 156 is connected to the opening of the nose skin 153. The nose hatch 156 can open and close the top nacelle 11.

[0037] The top cabin 11 is equipped with a flight control maintenance cover 155 and a first equipment cover 154. The flight control maintenance cover 155 and the first equipment cover 154 open and close the top cabin 11. The first equipment cover 154 is located at the tail end of the top cabin 11, and the flight control maintenance cover 155 is located directly above the top bulkhead 111 inside the top cabin 11. Through the modular design of the nose cover 156, the flight control maintenance cover 155, and the first equipment cover 154, it is very convenient to access and maintain key equipment such as the flight management computer 116, the airborne data link 115, and the emergency power supply 114 without extensive disassembly of the fuselage.

[0038] The top cabin 11 is equipped with an emergency power supply 114 and an airborne data link 115. In the event of a power system failure, the emergency power supply 114 supplies power to the flight management computer 116 to provide power for the UAV to make an emergency landing. The airborne data link 115 transmits UAV flight control commands, mission payload commands, and link control commands in real time through an antenna. Specifically, the emergency power supply 114, the airborne data link 115, and the flight management computer 116 are all fixedly connected to the partition 14.

[0039] A top antenna is also provided above the top nacelle 11, which is fixed above the joint between the left skin 151 and the right skin 152 of the top nacelle 11.

[0040] The power supply system is installed in the middle cabin 12. The middle cabin 12 is fixedly connected to the top cabin 11. The middle cabin 12 is equipped with a hoisting system that can hoist cargo. Specifically, the middle cabin 12 is equipped with a fuselage frame 121, which supports the middle cabin 12. The fuselage frame 121 is connected to the bottom of the middle cabin 12. The hoisting system is fixedly connected to the fuselage frame 121. A floor 122 is provided on the fuselage frame 121, and the power supply system is located on the floor 122.

[0041] The fuselage frame 121 includes longitudinal beams 1211 and a central bulkhead 1212. There are two longitudinal beams 1211, which are located at both ends of the central cabin 12. The bottom ends of the two longitudinal beams 1211 are fixedly connected to the bottom surface of the central cabin 12. The two longitudinal beams 1211 are fixedly connected to the central bulkhead 1212. There are three central bulkheads 1212. The side ends of the central bulkheads 1212 are fixedly connected to the side walls of the central cabin 12, and the top ends of the central bulkheads 1212 are fixedly connected to the top surface of the central cabin 12. That is, the top ends of the central bulkheads 1212 are fixedly connected to the bulkhead 14. In other embodiments of this utility model, the number of central bulkheads 1212 can also be other, as long as they can support the central cabin 12.

[0042] The fuselage frame 121 provides a strong load-bearing foundation for the central cabin 12, which effectively distributes the load of the suspended cargo, the weight of the battery 127, and the impact force of the landing gear to the entire fuselage structure, avoiding local overload.

[0043] The fuselage frame 121 is fixedly connected to the top bulkhead 111 via the bulkhead 14. Thus, when the UAV is in flight, the huge lift generated by the motor and various loads during maneuvering are first transferred to the top bulkhead 111 through the boom joints 113. The bulkhead 14 acts as a crucial "force transfer station" or "structural bridge". The bulkhead 14 then evenly distributes the load to the entire fuselage frame 121 connected to it. In this way, the huge force that was originally concentrated on a few boom joints 113 is transferred and distributed to the robust frame of the entire central cabin 12.

[0044] Specifically, the floor 122 is installed on two longitudinal beams 1211. The floor 122 is also designed with a downward-facing flange structure around its perimeter. It is fixed to the left skin 151 and right skin 152 of the fuselage by adhesive riveting. The planar area of ​​the floor 122 is fixed to the longitudinal beams 1211 and the central partition 1212 by adhesive riveting.

[0045] The power system includes two sets of batteries 127 and a slide rail 126. The two sets of batteries 127 are connected in parallel to provide power. When one set of batteries 127 fails, the other set of batteries 127 continues to provide power to enable the drone to make an emergency landing. The batteries 127 are equipped with feet, which allow them to slide along the slide rail 126 for easy installation and removal. Specifically, the feet are made of polytetrafluoroethylene (PTFE) to reduce the friction between the batteries 127 and the slide rail 126. A PTFE abrasion-resistant plate is fixedly connected to the floor 122 to prevent wear and tear on the composite floor 122 when the batteries 127 are installed or removed.

[0046] The power system also includes a high-voltage control box 124 and a fuse box 125. A battery 127 supplies power to the high-voltage control box 124. The high-voltage control box 124 is electrically connected to the flight management computer 116. The battery 127 can supplement the emergency power supply 114 with power through the high-voltage control box 124. The emergency power supply 114 is activated when the high-voltage control box 124 and the fuse box 125 fail.

[0047] Two equipment ports are provided on the central engine compartment 12, forming a maintenance passage for entering the central engine compartment 12 to install and remove the battery 127. Air intake grilles 159 are installed on the equipment ports. The two air intake grilles 159 are arranged opposite each other to ventilate and dissipate heat from the power system. The air intake grilles 159 can open and close the central engine compartment 12. The equipment ports and air intake grilles 159 on both sides serve as natural ventilation ducts to effectively dissipate heat from the battery 127 system, which generates a lot of heat, and also form a convenient maintenance passage, making it easy for personnel to enter the compartment for operation and maintenance.

[0048] The middle cabin 12 is provided with a second equipment access cover 157 and an opening cover 158 at the bottom. The second equipment access cover 157 and the opening cover 158 can open and close the middle cabin 12. The landing gear assembly 3 can be installed or removed from the fuselage frame 121 by entering through the bottom of the middle cabin 12 through the opening cover 158.

[0049] The bottom cabin 13 can be loaded with cargo. The bottom cabin 13 and the middle cabin 12 are detachably connected. The drone has a hoisting state and a loading state. When the drone is in the hoisting state, the bottom cabin 13 is separated from the middle cabin 12, and the hoisting system can hoist cargo. When the drone is in the loading state, the bottom cabin 13 is connected to the middle cabin 12, and cargo can be loaded in the bottom cabin 13.

[0050] The detachable connection of the bottom cabin 13 enables the drone to quickly and flexibly switch between two modes: sling-mounted and loaded. This solves the core pain point of the traditional drone's single transport mode, allowing it to perfectly adapt to different mission requirements, such as internal cargo transport requiring low-drag long-distance flight and external sling-mounted operations requiring precise airdrop, significantly expanding application scenarios and mission efficiency.

[0051] The bottom cabin 13 includes a fairing skin, which has wave-transmitting requirements and is specifically a fiberglass foam sandwich structure. The fairing skin forms a placement area for placing cargo. Preferably, when the UAV is in a loaded state, the bottom cabin 13 is screwed to the middle cabin 12. In other embodiments of this utility model, the bottom cabin 13 and the middle cabin 12 can also be connected by other detachable connection methods.

[0052] The motor support arm assembly 2 includes four support arm components 21, which are symmetrically arranged. Each support arm component 21 is fixedly connected to a connecting joint 22, which can be connected to a support arm connector 113 to connect the motor support arm assembly 2 to the body assembly 1. Specifically, the connecting joint 22 is a single-ear connector. When the connecting joint 22 is connected to the support arm connector 113, the connecting joint 22 is inserted into the gap of the double-ear connector of the support arm connector 113, and the through hole on the connecting joint 22 coincides with the through hole on the support arm connector 113. Then, the connecting joint 22 and the support arm connector 113 are fixed by bolts passing through the coincident through holes.

[0053] The connection between the motor support arm assembly 2 and the body assembly 1 adopts a fork-ear connection with a single-ear joint and a double-ear joint, and is fixed by high-strength bolts. This allows it to perfectly withstand the combined loads of tension, compression, and shear generated by the motor thrust, gravity, and motor inertia. Compared with a simple flange connection, the fork-ear connection can better disperse stress, avoid stress concentration, and significantly improve fatigue life.

[0054] The end of the support arm 21 away from the connecting joint 22 is connected to a motor mounting base 23. The electric propulsion system is installed on the motor mounting base 23. The electric propulsion system is the core power source of this heavy-duty multi-rotor UAV, providing the thrust required for hovering and flight. Specifically, the motor mounting base 23 has a support arm mounting interface, into which the support arm 21 can be inserted. The motor mounting base 23 has an electric propulsion mounting interface, into which the electric propulsion system can be installed.

[0055] The boom member 21 is provided with a mounting slot 24 for mounting an electronic speed controller 25. The electronic speed controller 25 receives speed commands from the flight management computer 116 and drives the electric propulsion system through a vector control algorithm to ensure the operation of the electric propulsion system. Specifically, each boom member 21 has two mounting slots 24, and the two mounting slots 24 are located on the same straight line to utilize the oncoming airflow during flight to form a chimney effect and achieve efficient heat dissipation.

[0056] The support arm 21 includes two support arm skins. The two support arm skins are joined together to form the support arm 21. The mounting groove 24 is opened on the two support arm skins. A maintenance opening is opened on either support arm skin. A support arm cover 29 is provided on the maintenance opening. The support arm cover 29 can open and close the maintenance opening to facilitate the maintenance of the power regulator 25.

[0057] By setting up maintenance openings, maintenance personnel do not need to disassemble the entire support arm. They can directly access the power regulator 25 by simply opening the support arm cover 29 to perform operations such as inspection, replacement, or plugging and unplugging cables, thus greatly increasing maintenance efficiency.

[0058] A fixing member 26 is provided in the mounting slot 24 of the boom 21 to facilitate the fixed installation of the ESC 25 and to enhance the structural environment of the mounting slot 24. The fixing member 26 includes a fixing bracket 261 and a reinforcing frame 262. The fixing bracket 261 has an ESC mounting port 263 adapted to the ESC 25. Both ends of the fixing bracket 261 are fixedly connected to the reinforcing frame 262. The reinforcing frame 262 is arranged longitudinally along the boom 21, and the shape of the reinforcing frame 262 is the same as the shape of the longitudinal section of the boom 21. The reinforcing frame 262 provides support for the installation of the ESC 25 and significantly improves the overall bending and torsional stiffness of the boom. When the heavy-load UAV is maneuvering, the root of the boom is subjected to huge stress. The reinforcing frame 262 can effectively prevent the boom from deforming and ensure aerodynamic efficiency and flight stability.

[0059] The fixed bracket 261 includes a fixed part 2611 and an extension part 2612. The fixed part 2611 and the extension part 2612 are fixedly connected. The ESC mounting port 263 is opened in the fixed part 2611 and the extension part 2612. The fixed part 2611 is larger than the mounting groove 24. The extension part 2612 is adapted to the mounting groove 24. When the extension part 2612 extends beyond the mounting groove 24, the extension part 2612 is flush with the outer wall of the support arm 21. At this time, the ESC 25 also does not protrude beyond the support arm 21, so as to facilitate heat dissipation and reduce wind resistance.

[0060] The electric propulsion system includes eight motors 27 and eight double-bladed propellers 28. Every two motors 27 and every two double-bladed propellers 28 form a group. Each group of motors 27 and double-bladed propellers 28 is connected to the support arm 21. Each motor 27 drives its corresponding double-bladed propeller 28.

[0061] The landing gear assembly 3 is fixedly connected to the fuselage frame 121. Specifically, the landing gear assembly 3 includes a landing gear crossbeam, which is fixedly connected to the longitudinal beam 1211 of the fuselage frame 121. Both ends of the landing gear crossbeam are fixedly connected to connecting joints 22. The landing gear crossbeam is connected to the landing gear bracket through the connecting joints 22. The landing gear bracket and the landing gear crossbeam are detachable.

[0062] Preferably, a limiting flange is added to the inner side of the docking between the landing gear crossbeam and the longitudinal beam 1211 of the fuselage frame 121 to control the landing gear crossbeam from shifting.

[0063] Obviously, the above embodiments of this utility model are merely examples for clearly illustrating the present utility model, and are not intended to limit the implementation of the present utility model. Those skilled in the art can make other variations or modifications based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this utility model should be included within the protection scope of the claims of this utility model.

Claims

1. An integrated support arm for heavy-duty unmanned aerial vehicles, characterized in that, The device includes an arm assembly, one end of which is connected to the fuselage assembly, and the other end of which is connected to the electric propulsion system. The electric propulsion system provides the thrust required for hovering and flight of the UAV. The arm assembly has a mounting slot, and a fixing component is installed in the mounting slot. The fixing component is used to install and fix the ESC (Electronic Speed ​​Controller). The fixing component and the ESC do not protrude beyond the arm assembly to reduce wind resistance while allowing the ESC to dissipate heat. The arm assembly has a maintenance opening, and a cover is provided on the maintenance opening. The cover can open and close the maintenance opening to maintain the ESC.

2. The integrated support arm for heavy-duty UAVs according to claim 1, characterized in that, The fasteners and electric controller are flush with the support arm.

3. The integrated support arm for heavy-duty UAVs according to claim 1, characterized in that, The fastener includes a fixed bracket and a reinforcing frame. The fixed bracket has an ESC mounting port that is compatible with the ESC. Both ends of the fixed bracket are fixedly connected to the reinforcing frame.

4. The integrated support arm for heavy-duty UAVs according to claim 3, characterized in that, The reinforcing frame is set along the longitudinal direction of the support arm, and the shape of the reinforcing frame is the same as the shape of the longitudinal section of the support arm.

5. The integrated support arm for heavy-duty UAVs according to claim 3, characterized in that, The fixed bracket includes a fixed part and an extension part, which are fixedly connected. An electric adjustment mounting port is opened on the fixed part and the extension part. The extension part is adapted to the mounting groove. When the extension part extends beyond the mounting groove, the extension part is flush with the outer wall of the support arm.

6. The integrated support arm for heavy-duty UAVs according to claim 5, characterized in that, The fixing part is larger than the mounting groove, and when the extension part extends beyond the ESC mounting opening, the fixing part fits against the inner wall of the support arm.

7. The integrated support arm for heavy-duty UAVs according to claim 1, characterized in that, The outrigger assembly includes two outrigger skins, which are joined together to form the outrigger assembly. Mounting slots are provided on both outrigger skins, and maintenance openings are provided on either outrigger skin.

8. The integrated support arm for heavy-duty UAVs according to claim 7, characterized in that, The two mounting slots on each outrigger are on the same straight line.

9. The integrated support arm for heavy-duty unmanned aerial vehicles according to claim 1, characterized in that, A connecting joint is fixedly connected to the outrigger assembly, and the outrigger assembly is connected to the outrigger joint of the fuselage assembly through the connecting joint.

10. The integrated support arm for heavy-duty UAVs according to claim 1, characterized in that, The end of the outrigger assembly furthest from the fuselage assembly is connected to a motor mounting base, and the electric propulsion system is mounted on the motor mounting base.

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