A drone motor arm structure

Abstract

The utility model relates to an unmanned plane technical field especially relates to a kind of unmanned plane motor arm structure, including motor arm, the lift unit of unmanned plane is connected with aileron;The motor arm includes docking frame, right skin, left skin, docking band plate, fairing and motor seat, the right skin and left skin are glued together by docking band plate, cover and fit on motor seat and docking frame, form main force main body, the utility model is equipped with motor connecting frame in the up-down direction of front frame and rear frame, can install motor in up-down direction, while the electrically-controlled connection platform for installing electrically-controlled is designed in the left-right direction of front frame and rear frame, so that electrically-controlled can be installed in the vicinity of motor, facilitate the control of electrically-controlled to motor, reduce the probability that electrically-controlled and motor between connection wire harness are disturbed, so that the present application has the advantage that equipment arrangement is compact, while the present application also has the advantages of good maintainability, good heat dissipation, good safety and high stiffness.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a UAV motor arm structure. Background Technology

[0002] Vertical takeoff and landing (VTOL) drones do not require dedicated runways for takeoff and landing, making them flexible and widely applicable. They are increasingly used in logistics, reconnaissance, power line inspection, and rescue.

[0003] The motor arm connects to the lift unit of the drone, providing the power for the drone's vertical take-off and landing. It should have high strength and a good aerodynamic shape to ensure low drag when the drone is flying in fixed-wing mode. The lift unit of the drone is an important power system that requires regular maintenance. Therefore, the motor arm that connects to the lift unit needs to facilitate maintenance of the lift unit, detect defects in a timely manner, and reduce maintenance costs.

[0004] The Chinese utility model patent with application number 201920469905.1, entitled "An Arm Structure and a UAV", adopts an upper and lower end cover design to protect the UAV from dust and water when not in use. Its motor arm only connects the motor and propeller, and the distance between the ESC and the motor is far. The transmitted signal line is easily interfered with. It is a small multi-rotor UAV, and the shape of the motor arm has large aerodynamic drag, which is not suitable for use with load-bearing wing UAVs. Utility Model Content

[0005] The purpose of this utility model is to overcome the shortcomings of the prior art and provide a drone motor arm structure with the advantages of compact equipment layout, good maintainability, good heat dissipation, good safety and high rigidity.

[0006] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0007] A drone motor arm structure includes a motor arm that connects the drone's lift unit to its wings;

[0008] The motor arm includes a docking frame, a right skin, a left skin, a docking strip plate, a fairing, and a motor base. The right skin and the left skin are glued together by the docking strip plate and fitted onto the motor base and the docking frame to form the main load-bearing body. The fairing is detachably connected to the front of the motor base.

[0009] The motor mount consists of a cage-like structure composed of a front frame, a rear frame, and a motor connection frame. The motor connection frame is used to mount the motor, and the front and rear frames are used to mount the electronic speed controller (ESC).

[0010] Preferably, two docking plates are provided, and the tops and bottoms of the right and left skins are glued together by the docking plates. After the right and left skins are glued together by the docking plates, the whole structure is cylindrical.

[0011] Furthermore, one end of the docking frame is glued to the right skin, the left skin, and the docking strip plate, and the other end of the docking frame is glued to the wing of the UAV.

[0012] Furthermore, the overlapping positions of the motor mount with the left skin, right skin, and mating strip are connected with structural adhesive to maintain the motor mount as an integral structure with the left and right skins.

[0013] Furthermore, the right skin, left skin, and docking strip are all made of carbon fiber composite material, and the width of the docking strip is not less than 25mm.

[0014] Furthermore, both sides of the rear frame are provided with ESC cable passage grooves, and the rear frame is also provided with an ESC mounting platform for installing the ESC. The rear frame is integrally formed with a frame flange to increase the bonding area between the rear frame and the right skin, left skin and mating strip plate. The rear frame is provided with a rear cable passage hole for the wire harness to pass through.

[0015] Furthermore, the front frame is integrally formed with a fairing connection flange for detachable installation of the fairing, and the front frame is also provided with an ESC connection front platform for installing the ESC. The front frame is provided with a motor wire avoidance groove for avoiding motor wires, and the front frame is provided with a front wire passage hole for the wire harness to pass through.

[0016] Furthermore, each motor mount has two motor connection frames, each motor connection frame has a reinforcing rib, each motor connection frame has a motor connection hole for mounting the motor, and the reinforcing rib has a wire harness fixing hole for mounting the wire harness.

[0017] Furthermore, the front and rear frames are fitted with abrasion-resistant sleeves to prevent wear on the wiring harness.

[0018] Furthermore, when the fairing and motor mount are assembled into an integral structure, a wire passage groove is left between the fairing and the motor mount, through which the motor wiring harness is passed into the motor arm. The interior of the fairing is provided with a reinforcing structure.

[0019] The beneficial effects of this utility model are:

[0020] This utility model has motor connection frames installed in the vertical direction of the front and rear frames, which can install motors in both the vertical and vertical directions. At the same time, ESC connection platforms are designed in the left and right directions of the front and rear frames for installing ESCs. This allows the ESCs to be installed near the motors, which facilitates the control of the motors by the ESCs and reduces the probability of interference between the wiring harness between the ESCs and the motors. As a result, this application has the advantage of compact equipment layout.

[0021] The fairing of the motor arm is connected to the front frame by fasteners and is a detachable structure. After the fairing is removed, the internal wiring harness can be fixed and maintained through the front wiring hole of the front frame. The motor and ESC are exposed on the outer surface of the motor arm and can be maintained directly without disassembling other structural components, thus giving this application the advantage of good maintainability.

[0022] The motor and ESC are exposed on the outer surface of the motor arm. During vertical takeoff and landing, the propeller wind is used for heat dissipation. During level flight, the airflow from the forward flight of the drone can dissipate heat, resulting in good heat dissipation performance.

[0023] The motor mount consists of a cage-like structure composed of a front frame, a rear frame, and a motor connection frame. It has high strength and rigidity, and maintains structural stability and integrity when bearing the load of the lifting unit. It can effectively withstand the torque, tension, and other loads of the UAV's vertical take-off and landing, and has high strength and good safety. Attached Figure Description

[0024] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1 This is a diagram showing the position of a drone motor arm structure according to the present invention on a drone;

[0026] Figure 2 This is an isometric view of a drone motor arm structure according to the present invention;

[0027] Figure 3 This is an exploded view of the structure of a drone motor arm according to the present invention;

[0028] Figure 4 This is an exploded view of the motor base of this utility model;

[0029] Figure 5 This is an isometric view of the motor connection frame of this utility model;

[0030] Figure 6 This is an isometric view of the front frame of this utility model;

[0031] Figure 7 This is an isometric view of the rear frame of this utility model;

[0032] Figure 8 This is a horizontal sectional view of the motor arm structure of this utility model at the rear frame position;

[0033] Figure 9 This is an internal view of the fairing of this utility model.

[0034] The markings in the diagram are as follows: 1. Motor arm; 11. Docking frame; 12. Right skin; 13. Left skin; 14. Docking strip plate; 15. Fairing; 151. Reinforcing structure; 16. Motor mount; 161. Rear frame; 1611. ESC cable tray; 1612. ESC mounting platform; 1613. Frame flange; 1614. Rear cable hole; 162. Front frame; 1621. Fairing connection flange; 1622. ESC connection front platform; 1623. Motor cable clearance groove; 1624. Front cable hole; 163. Motor connection frame; 1631. Reinforcing rib; 1632. Motor connection hole; 1633. Wiring harness fixing hole; 164. Anti-wear sleeve; 2. UAV; 3. Cable tray. Detailed Implementation

[0035] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0036] It should be understood that, when used in this specification and the appended claims, the terms "comprising" and "including" indicate the presence of the described features, integrals, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components and / or collections thereof.

[0037] It should also be understood that the terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the scope of the invention. As used in this specification and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise.

[0038] It should also be further understood that the term "and / or" as used in this specification and the appended claims refers to any combination of one or more of the associated listed items and all possible combinations, and includes such combinations.

[0039] Example 1

[0040] Please see Figure 1-9 As shown, a drone motor arm structure includes a motor arm 1, which connects the lift unit and wing of the drone 2.

[0041] like Figure 1 As shown, motor arms 1 are arranged between the lift unit and the wing of the UAV 2, in four locations with identical structures. This example uses one location as an example for illustration. The motor arms 1 of the UAV 2 are connected to the lift units at the top and bottom respectively. Each motor arm 1 is connected to two sets of lift units. Compared to connecting one set of lift units to a single motor arm 1, this saves half the number of motor arms 1, making it lighter. At the same time, it reduces the aerodynamic interference of the motor arms 1 to the wing by half, effectively reducing drag during forward flight. The motor arms 1 connect the lift unit and the wing, transferring the lift generated by the lift unit and the torque of the motor to the wing, ensuring the function of the lift unit and realizing the vertical take-off and landing function of the UAV 2.

[0042] like Figure 2 As shown, the motor arm 1 includes a docking frame 11, a right skin 12, a left skin 13, a docking strip 14, a fairing 15, and a motor base 16. The right skin 12 and the left skin 13 are glued together by the docking strip 14 and fit onto the motor base 16 and the docking frame 1 to form the main load-bearing body. The fairing 15 is detachably connected to the front of the motor base 16.

[0043] like Figure 4 As shown, the motor mount 16 is a cage-like structure consisting of a front frame 162, a rear frame 161, and a motor connecting frame 163. The motor connecting frame 163 is used to mount the motor, while the front frame 162 and the rear frame 161 are used to mount the ESC.

[0044] like Figure 3 As shown, there are two mating plates 14. The tops of the right skin 12 and the left skin 13, as well as the bottoms of the right skin 12 and the left skin 13, are bonded together by the mating plates 14. After the right skin 12 and the left skin 13 are bonded together by the mating plates 14, the whole structure is cylindrical.

[0045] The inner top of the right skin 12 and the left skin 13 that are close to each other is glued to the top of the mating plate 14 located at the top. The inner bottom of the right skin 12 and the left skin 13 that are close to each other is glued to the bottom of the mating plate 14 located at the bottom. Under the action of the two mating plates 14, the right skin 12 and the left skin 13 can be glued together as a whole, and the whole is in the form of a cylindrical structure.

[0046] The right skin 12 and the left skin 13 are bonded together by a butt joint plate 14, which can maintain the aerodynamic shape of the motor arm 1. The right skin 12 and the left skin 13 divide the shape of the motor arm 1 into two parts, so that there will be no undercut during manufacturing and molding, which facilitates demolding.

[0047] The right skin 12, left skin 13 and mating strip 14 are all made of carbon fiber composite material, with a layup sequence of [(±45) / (0 / 90) / (0 / 90) / (±45)]. The width of the mating strip 14 is not less than 25 mm, and preferably 30 mm in this example, so that the adhesive width between the right skin 12 and the left skin 13 is not less than 15 mm, which can ensure the adhesive strength.

[0048] The load of the motor arm 1 is transmitted through the cylindrical structure composed of the right skin 12, the left skin 13 and the docking plate 14. Therefore, the carbon fiber composite material used in the right skin 12, the left skin 13 and the docking plate 14 needs to be subjected to non-destructive testing to ensure that there are no defects such as delamination or voids inside the carbon fiber composite material.

[0049] The docking frame 11 is a machined aluminum alloy part, preferably made of 7075 aluminum alloy, and preferably heat treated in T7351 condition. One end of the docking frame 11 is connected to the left skin 13, the right skin 12, and the docking strip 14. At this time, the outer surface of one end of the docking frame 11 is in contact with the inner wall of the left skin 13 and the right skin 12. The other end of the docking frame 11 is connected to the wing to ensure the continuous force transmission of the motor arm structure.

[0050] The connection between the docking frame 11 and the left skin 13, right skin 12, docking strip 14, and wing is mainly by adhesive bonding, with pop rivets installed at certain intervals to prevent the adhesive layer from peeling off. Specifically, one end of the docking frame 11 is glued to the right skin 12, left skin 13, and docking strip 14, and the other end of the docking frame 11 is glued to the wing of the UAV 2.

[0051] like Figure 3 , Figure 4 and Figure 5 As shown, the motor mount 16 is a cage structure composed of a front frame 162, a rear frame 161, and a motor connection frame 163. It has high strength and rigidity, and maintains structural stability and integrity when bearing the load of the lifting unit. It can effectively withstand the torque, tension and other loads of the UAV 2 during vertical take-off and landing. It has high strength and good safety.

[0052] The front frame 162, the rear frame 161 and the motor connecting frame 163 are fixedly connected. The front frame 162, the rear frame 161 and the motor connecting frame 163 can be fixedly connected by gluing, welding, fasteners, etc. In this example, a hybrid connection method of gluing and fasteners is used to ensure the connection strength.

[0053] Each motor mount 16 has two motor connection frames 163. The two motor connection frames 163 are fixedly connected to the top and bottom of the front frame 162 and the rear frame 161, respectively. The two ends of each motor connection frame 163 are fixedly connected to the front frame 162 and the rear frame 161, so that the front frame 162 and the rear frame 161 can support the two motor connection frames 163.

[0054] Both motor connection frames 163 are used to install motors, so that each motor arm 1 can install two motors.

[0055] Each motor connection frame 163 is fixedly equipped with a reinforcing rib 1631 to improve out-of-plane stiffness. When subjected to motor tension, it maintains small deformation, thus minimizing the change in the angle of the tension line, which is beneficial for the control of the UAV 2 state during flight.

[0056] Each motor connection frame 163 has a motor connection hole 1632 for installing a motor. The motor connection hole 1632 is used to install the motor. Fasteners are screwed into the motor through the motor connection hole 1632 to fix the motor to the motor connection frame 163.

[0057] The reinforcing rib 1631 has a wire harness fixing hole 1633 for installing the wire harness. When the wire harness inside the motor arm 1 passes through the inside of the motor base 16, it is fixed to the wire harness fixing hole 1633 by the strip, keeping the wire harness in a fixed state and preventing the wire harness from contacting the structure when vibrating, thus avoiding wear.

[0058] The motor connection frame 163 is a machined aluminum alloy part, preferably made of 7075 aluminum alloy, and preferably heat treated with T7351.

[0059] like Figure 6 As shown, the front frame 162 has an integrally formed fairing connection flange 1621 for detachable installation of the fairing 15. The fairing 15 is connected to the fairing connection flange 1621 of the front frame 162 by a single-sided fastener, ensuring that the fairing 15 is detachable.

[0060] The front frame 162 has an ESC connection front platform 1622 on both the left and right sides for mounting the ESC. The ESC connection front platform 1622 is a partial planar structure that fits into the plane at the bottom of the ESC and is connected to the front frame 162 by fasteners.

[0061] The front frame 162 is provided with a motor wire avoidance groove 1623 for avoiding motor wires. The motor wire avoidance groove 1623 is a hollow structure, which provides a passage for motor wires when the upper and lower motors of the motor arm 1 are connected, so that the motor wires can enter the interior of the motor arm 1 through the motor wire avoidance groove 1623.

[0062] The front frame 162 has a front wire pass hole 1624 for the wire harness to pass through. The interior of the front frame 162 has a hollow structure, which is a square hole. This square hole is the front wire pass hole 1624. The wire harness inside the motor arm 1 passes through the front wire pass hole 1624, deflects up and down, and extends out of the outside of the motor arm 1 through the motor wire avoidance groove 1623 to connect with the upper and lower motors.

[0063] The front frame 162 is a machined aluminum alloy part, preferably made of 7075 aluminum alloy, and preferably heat treated with T7351.

[0064] like Figure 6 and 7 As shown, both the left and right sides of the rear frame 161 are provided with ESC mounting platforms 1612 for installing ESCs. The ESC mounting platform 1612 is a partial planar structure. It completes the installation of the ESC together with the ESC connection platform 1622 of the front frame 162. There are a total of 4 ESC connection holes on the ESC connection platform 1622 of the front frame 162. Two ESC connection holes are provided on the ESC connection platform 1622 and two ESC connection holes are provided on the ESC mounting platform 1612. Fasteners are screwed into the ESC through the ESC connection holes to fix the two ends of the ESC to the front frame 162 and the rear frame 161 respectively, so as to securely fix the ESC.

[0065] Both sides of the rear frame 161 are provided with ESC wire passage grooves 1611. After the ESC is installed, the ESC wire harness passes through the ESC wire passage grooves 1611 and enters the interior of the motor arm 1, thereby preventing the structure from blocking the passage of the wire harness.

[0066] The rear frame 161 has an integrally formed frame flange 1613 that increases the bonding area between the rear frame 161 and the right skin 12, left skin 13 and mating strip 14. The frame flange 1613 forms a certain bonding area and is bonded together with the left skin 13, right skin 12 and mating strip 14 to ensure a certain bonding width.

[0067] The rear frame 161 has a rear wire pass hole 1614 for the wire harness to pass through. The interior of the rear wire pass hole 1614 is used for the wire harness to pass through, so that the power wire harness of the motor can pass through the wire pass groove 3, the front wire pass hole 1624 of the front frame 162, the rear wire pass hole 1614 of the rear frame 161, the cavity formed by the left skin 13 and the right skin 12, and the docking frame 11 to reach the interior of the wing and connect with the battery pack inside the fuselage of the UAV 2.

[0068] The rear frame 161 is a machined aluminum alloy part, preferably made of 7075 aluminum alloy, and preferably heat treated in T7351 condition.

[0069] like Figure 4 and 8As shown, anti-wear sleeves 164 for preventing wire harness wear are installed inside the front frame 162 and the rear frame 161. Specifically, the anti-wear sleeves 164 are made of rubber and are clipped around the front wire hole 1624 and the rear wire hole 1614. They are held in place by the elastic deformation of the soft rubber material. Under the action of the anti-wear sleeves 164, the wire harness wear can be prevented, thus avoiding short circuit accidents caused by wire harness wear.

[0070] like Figure 8 As shown, the frame flange 1613 of the rear frame 161 is glued to the left skin 13 and the right skin 12. The ESC cable pass trough 1611 is a hollow structure. After the ESC is connected, the wire harness is passed through the ESC cable pass trough 1611 to the inside of the motor arm 1. The anti-wear sleeve 164 is snapped into the edge of the rear cable pass hole 1614 inside the rear frame 161 to protect the wire harness.

[0071] like Figure 9 As shown, when the fairing 15 and the motor mount 16 are assembled into an integral structure, a wire pass-through groove 3 is left between the fairing 15 and the motor mount 16. The motor wiring harness is passed through the wire pass-through groove 3 and inserted into the motor arm 1. A reinforcing structure 151 is fixedly installed inside the fairing 15.

[0072] The fairing 15 is a 3D printed plastic part made of PA12. In order to improve the rigidity of the fairing 15 and maintain its shape, a longitudinal and transverse reinforcing structure 151 is designed inside. The reinforcing structure 151 is made of the same material as the fairing 15, which ensures that the printed surface does not deform and at the same time improves its rigidity so that it will not deform due to aerodynamic forces during flight.

[0073] like Figure 2 and Figure 3 As shown, the overlapping positions of the motor mount 16 with the left skin 13, right skin 12, and mating strip 14 are connected with structural adhesive to maintain the motor mount 16, left skin 13, and right skin 12 as an integral structure.

[0074] Specifically, the right skin 12 and the left skin 13 are glued together by the mating strip 14 and fitted onto the front frame 162, the rear frame 161, and the motor connection frame 163. The overlapping positions of the front frame 162, the rear frame 161, and the motor connection frame 163 with the left skin 13, the right skin 12, and the mating strip 14 are connected with structural adhesive. After being connected with structural adhesive, the two motor connection frames 163, the ESC connection front platform 1622, and the ESC installation rear platform 1612 are exposed, and the motor wire avoidance groove 1623 opened on the front frame 162 is also exposed. This facilitates the installation of the motor and the ESC, and makes the motor and the ESC exposed on the outer surface of the motor arm 1 after installation.

[0075] After the fairing 15 is connected to the fairing connection flange 1621 of the front frame 162, the motor wire clearance groove 1623 is also exposed and forms the wire passage groove 3.

[0076] The fasteners mentioned in this embodiment include, but are not limited to, screws and bolts.

[0077] In summary, this utility model has motor connection frames 163 installed in the vertical direction of the front frame 162 and the rear frame 161, which can install motors in both the vertical and vertical directions. At the same time, ESC connection platforms are designed in the horizontal direction of the front frame 162 and the rear frame 161 for installing ESCs. This allows the ESCs to be installed near the motors, which facilitates the control of the motors by the ESCs and reduces the probability of interference between the wiring harness between the ESCs and the motors. As a result, this application has the advantage of compact equipment layout.

[0078] The fairing 15 of the motor arm 1 is connected to the front frame 162 by fasteners and is a detachable structure. After the fairing 15 is removed, the internal wiring harness can be fixed and maintained through the front wire hole 1624 of the front frame 162. The motor and ESC are exposed on the outer surface of the motor arm 1. No other structural components need to be disassembled, and maintenance can be carried out directly, thus giving this application the advantage of good maintainability.

[0079] The motor and ESC are exposed on the outer surface of the motor arm 1. During vertical take-off and landing, the propeller wind is used for heat dissipation. During level flight, the airflow from the forward flight of the UAV 2 can dissipate heat, resulting in good heat dissipation performance.

[0080] The front frame 162 is designed with a motor wire avoidance groove 1623, which together with the fairing 15 forms the wire passage groove 3 of the motor arm 1. The wire passage groove 3 is used for the motor power line to pass through, so that the power line passes through the inside of the motor arm 1 and then connects to the external motor.

[0081] The motor mount 16 is a cage structure consisting of a front frame 162, a rear frame 161, and a motor connecting frame 163. It has high strength and rigidity, and maintains structural stability and integrity when bearing the load of the lifting unit. It can effectively withstand the torque, tension and other loads of the UAV 2 during vertical take-off and landing. It has high strength and good safety. The reinforcing ribs 1631 of the motor connecting frame 163 improve local rigidity, prevent deformation under motor torque and tension, and reduce vibration coupling when the motor rotates.

[0082] The rear frame 161 is designed with an ESC cable tray 1611, which is a cavity structure through which the power supply ESC cable harness passes.

[0083] Anti-wear sleeves 164 are connected to the edges of the wire passage holes inside the front frame 162 and the rear frame 161 to prevent the wire harness from being worn and to avoid short circuits.

[0084] Example 2

[0085] The difference from Embodiment 1 is that the front frame 162, rear frame 161, and motor connection frame 163 that make up the motor base 16 are designed as a single metal 3D printed part. This eliminates the connection between parts and creates a single structure, which can effectively reduce the structural weight.

[0086] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in this utility model, and these modifications or substitutions should all be covered within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the scope of the claims.

Claims

1. A drone motor arm structure, characterized in that, include: Motor arm (1), which connects the lift unit and the wing of the UAV (2); The motor arm (1) includes a docking frame (11), a right skin (12), a left skin (13), a docking strip (14), a fairing (15), and a motor base (16). The right skin (12) and the left skin (13) are glued together by the docking strip (14) and fitted onto the motor base (16) and the docking frame (11) to form the main load-bearing body. The fairing (15) is detachably connected to the front of the motor base (16). The motor mount (16) is a cage structure consisting of a front frame (162), a rear frame (161), and a motor connecting frame (163). The motor connecting frame (163) is used to install the motor, and the front frame (162) and the rear frame (161) are used to install the ESC.

2. The UAV motor arm structure according to claim 1, characterized in that, Two docking plates (14) are provided. The tops of the right skin (12) and the left skin (13) and the bottoms of the right skin (12) and the left skin (13) are glued together by the docking plates (14). After the right skin (12) and the left skin (13) are glued together by the docking plates (14), the whole structure is cylindrical.

3. The UAV motor arm structure according to claim 1, characterized in that, One end of the docking frame (11) is glued to the right skin (12), the left skin (13) and the docking strip (14), and the other end of the docking frame (11) is glued to the wing of the UAV (2).

4. The UAV motor arm structure according to claim 1, characterized in that, The overlapping positions of the motor base (16) with the left skin (13), right skin (12) and docking plate (14) are connected with structural adhesive to keep the motor base (16) and the left skin (13) and right skin (12) as an integral structure.

5. The UAV motor arm structure according to claim 1, characterized in that, The right skin (12), left skin (13) and docking strip (14) are all made of carbon fiber composite material, and the width of the docking strip (14) is not less than 25 mm.

6. The UAV motor arm structure according to claim 1, characterized in that, Both sides of the rear frame (161) are provided with ESC cable passage grooves (1611). The rear frame (161) is also provided with an ESC mounting platform (1612) for installing ESCs. The rear frame (161) is integrally formed with a frame flange (1613) to increase the bonding area between the rear frame (161) and the right skin (12), left skin (13) and mating strip plate (14). The rear frame (161) is provided with a rear cable passage hole (1614) for the wire harness to pass through.

7. The UAV motor arm structure according to claim 1, characterized in that, The front frame (162) has an integrally formed fairing connection flange (1621) for detachable installation of fairing (15). The front frame (162) is also provided with an ESC connection front platform (1622) for installing ESC. The front frame (162) has a motor wire avoidance groove (1623) for avoiding motor wires. The front frame (162) has a front wire passage hole (1624) for wire harness passage.

8. The UAV motor arm structure according to claim 1, characterized in that, Each motor mount (16) has two motor connection frames (163), each motor connection frame (163) has a reinforcing rib (1631), each motor connection frame (163) has a motor connection hole (1632) for mounting the motor, and the reinforcing rib (1631) has a wire harness fixing hole (1633) for mounting the wire harness.

9. The UAV motor arm structure according to claim 1, characterized in that, The front frame (162) and rear frame (161) are equipped with abrasion sleeves (164) to prevent wire harness wear.

10. The UAV motor arm structure according to claim 1, characterized in that, When the fairing (15) and the motor mount (16) are assembled into an integral structure, a wire pass-through groove (3) is left between the fairing (15) and the motor mount (16) to pass the motor wire harness through the wire pass-through groove (3) into the motor arm (1). The fairing (15) is provided with a reinforcing structure (151).

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