Compound wing electric unmanned aerial vehicle motor arm structure

Abstract

The utility model relates to an unmanned plane technical field especially relates to a kind of composite wing electric unmanned plane motor arm structure, including motor arm, the lift unit of unmanned plane is connected with wing by the motor arm;The motor arm includes connecting frame, right skin, left skin, fairing and motor seat, the right skin and left skin are bonded together by structural adhesive and connecting frame and motor seat, form main force main body, the connecting frame is connected with wing, the fairing is detachably connected in motor seat front part, when the fairing and motor seat are spliced into integral structure, the fairing is the end part appearance of motor arm structure, maintain fairing appearance while, can be used as maintenance port cover, the wire harness inside motor arm is maintained, the inside structure of motor seat is checked, the motor seat is used to install motor and electric governor;The utility model has the advantages of good maintenance, 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 composite-wing electric UAV motor arm structure. Background Technology

[0002] The compound-wing electric unmanned aerial vehicle (UAV) is an outstanding achievement of integrated innovation in the field of aviation technology. Through ingenious configuration design, it combines the core advantages of multi-rotor UAVs and fixed-wing UAVs, aiming to completely solve the fundamental contradiction that traditional UAVs cannot achieve both "convenience of vertical take-off and landing" and "long endurance and long range".

[0003] Its core working principle is a "three-stage" flight process: First, during the takeoff and landing phases, it fully utilizes the advantages of multi-rotor aircraft. With the help of multiple vertical motors and propellers specially set on the fuselage, it can take off and land vertically on the spot (VTOL) like a helicopter, completely eliminating its dependence on runways, catapults or recovery nets, and greatly expanding its deployment capabilities in complex and confined environments such as mountains, ships, and urban rooftops. Subsequently, after ascending to a safe altitude, the drone enters a crucial mode transition phase. The vertical motors gradually reduce power or change angles (such as tilting or folding), while the main propulsion motor at the tail starts working, providing forward thrust. Finally, the drone fully enters a highly efficient fixed-wing cruise mode. At this point, its flight principle is no different from that of a traditional aircraft, mainly relying on the streamlined fixed wings to generate lift. This aerodynamic lift efficiency is far higher than the method of "pulling" air through rotors, enabling the drone to fly at higher speeds (usually 2-3 times that of multi-rotor aircraft) and significantly reduce energy consumption, thus achieving amazing endurance. Its flight time and range are often several times that of multi-rotor aircraft with the same battery specifications.

[0004] The motor arm connects to the drone's lift system, providing the power for the drone's vertical takeoff and landing. It should have high strength and a good aerodynamic shape to ensure low drag when the drone is flying with a fixed wing. The drone's lift unit is an important power system that requires regular maintenance. Therefore, the motor arm connecting to the lift unit needs to facilitate maintenance of the lift unit, detect defects in a timely manner, and reduce maintenance costs. Utility Model Content

[0005] The purpose of this invention is to overcome the shortcomings of the prior art and provide a composite wing electric drone motor arm structure with advantages such as 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 composite-wing electric unmanned aerial vehicle (UAV) motor arm structure includes a motor arm that connects the UAV's lift unit and wing.

[0008] The motor arm includes a connecting frame, a right skin, a left skin, a fairing, and a motor base. The right skin and left skin are bonded to the connecting frame and the motor base with structural adhesive to form the main load-bearing body. The connecting frame is connected to the wing. The fairing is detachably connected to the front of the motor base. When the fairing and the motor base are assembled into an integral structure, the fairing is the end shape of the motor arm structure. While maintaining the rectified shape, it can also serve as a maintenance cover to maintain the wiring harness inside the motor arm and inspect the internal structure of the motor base.

[0009] The motor mount is used to install the motor and ESC.

[0010] Preferably, both the right skin and the left skin are provided with a "stepped" bonding surface to ensure the bonding strength, and the width of the "stepped" bonding surface is 30mm.

[0011] Furthermore, both the right and left skins are made of carbon fiber composite materials.

[0012] Furthermore, it also includes a support frame, which is connected to the left and right skins using structural adhesive.

[0013] Furthermore, after the right skin and left skin are glued together, the whole structure is cylindrical, and the cylindrical structure is provided with an opening for mounting the connecting frame and the motor base.

[0014] Furthermore, the connection frame is connected to the wing using a glue-riveting method.

[0015] 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.

[0016] Furthermore, it also includes a maintenance cover. After the right skin and left skin are glued together, the whole structure is cylindrical, and the cylindrical structure is provided with an opening for installing the maintenance cover.

[0017] Furthermore, the motor mount is made of 7075 aluminum alloy with a heat treatment state of T7351, which has high strength and rigidity. The motor mount is mainly responsible for bearing concentrated loads and distributing them to the right and left skins, so that the stress on the right and left skins is smaller and more uniform. When the motor mount bears the load of the lifting unit, it maintains structural stability and integrity.

[0018] Furthermore, the motor mount has a hollow internal structure, with motors installed on both the top and bottom, and electronic speed controllers (ESCs) installed on both the left and right sides. The wiring harnesses for the power supply motors and ESCs pass through the inside of the motor mount, and wear-resistant sleeves are installed inside the motor mount to prevent wear on the wiring harnesses.

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

[0020] The fairing of this utility model is the end shape of the motor arm structure. While maintaining the rectifier shape, it can also serve as a maintenance cover. After disassembling the fairing, the wiring harness inside the motor arm can be maintained and the internal structure of the motor mount can be inspected. At the same time, the motor and ESC are exposed on the outer surface of the motor arm, and maintenance can be carried out directly without disassembling other structural components. Thus, this utility model has the advantage of good maintainability.

[0021] By having the motor and ESC exposed on the outer surface of the motor arm, the device utilizes the wind from the propeller for heat dissipation during vertical takeoff and landing, and during level flight, it can dissipate heat through the airflow from the forward-flying drone, giving this invention the advantage of good heat dissipation performance.

[0022] The motor mount is a cage-like structure machined from a single aluminum alloy piece. It has high strength and rigidity, and can effectively withstand the torque, tension and other loads of the UAV's vertical take-off and landing. It has high strength and good safety, ensuring high rigidity of the motor mount, reducing deformation, and facilitating the flight control of the UAV. Attached Figure Description

[0023] 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.

[0024] Figure 1 This is an isometric view of the motor arm structure of a composite wing electric unmanned aerial vehicle according to this utility model;

[0025] Figure 2 This utility model Figure 1 Enlarged schematic diagram of the structure at point A;

[0026] Figure 3 This is a bottom view of the motor arm of this utility model;

[0027] Figure 4 This is a schematic diagram showing the right and left skins of this utility model after being glued together;

[0028] Figure 5 This is a schematic diagram of the internal structure of the motor arm of this utility model;

[0029] Figure 6 This is an isometric view of the motor mount of this utility model;

[0030] Figure 7 This is an isometric view of the connecting frame of this utility model;

[0031] Figure 8 This is an internal view of the fairing of this utility model.

[0032] The markings in the diagram are as follows: 1. Motor arm; 11. Connecting frame; 12. Right skin; 13. Left skin; 14. Fairing; 15. Motor mount; 16. Support frame; 17. Maintenance port cover; 141. Reinforcing structure. Detailed Implementation

[0033] 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.

[0034] 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.

[0035] 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.

[0036] 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.

[0037] Example 1

[0038] Please see Figure 1-8 As shown, a composite wing electric drone motor arm structure includes a motor arm 1, which connects the drone's lift unit and wing.

[0039] Two motor arms 1 are located between the lift unit and the wing of the UAV. They have the same structure and are symmetrically deployed with respect to the Y-plane of the fuselage. This example uses one of them as an example. The two ends of the motor arm 1 are connected to the lift unit, and four sets of lift units are connected to a single motor arm 1. Compared with the combined motor arm form, it saves half the number of motor arms. It is also lighter and reduces the aerodynamic interference of the motor arm 1 to the wing by half, effectively reducing drag during forward flight. The motor arm 1 connects the lift unit and the wing, and transfers the lift generated by the lift unit and the torque of the motor to the wing, realizing the vertical take-off and landing function of the UAV.

[0040] like Figure 1 As shown, the motor arm 1 includes a connecting frame 11, a right skin 12, a left skin 13, a fairing 14, and a motor base 15. The right skin 12 and the left skin 13 are bonded together with the connecting frame 11 and the motor base 15 by structural adhesive to form the main load-bearing body. The fairing 14 is detachably connected to the front of the motor base 15.

[0041] The left skin 13 and right skin 12 divide the shape of the motor arm 1 into two parts. Compared with one-piece molding or winding molding, this method is less expensive and easier to demold. Both the left skin 13 and the right skin 12 are made of carbon fiber composite material, with a layup sequence of [(±45) / (0 / 90) / (0 / 90) / (±45)]. To ensure a smooth transition of the aerodynamic surfaces of the motor arm and reduce air resistance, both the left and right skins are provided with "stepped" bonding surfaces, such as... Figure 2 As shown, the width of the "stepped" bonding surface is 30mm to ensure the bonding strength. After the right skin 12 and the left skin 13 are bonded, the discontinuity of their outer surfaces should be controlled within 5-8mm to ensure a smooth aerodynamic shape.

[0042] like Figure 5 As shown, it also includes a support frame 16, which is connected to the left skin 13 and the right skin 12 with structural adhesive. The support frame 16 is a machined aluminum alloy part, preferably made of 7075 aluminum alloy, and preferably heat treated with T7351. The support frame 16 is connected to the left skin 13 and the right skin 12 of the motor arm 1 respectively, and is then connected to the wing of the UAV with the connecting frame 11 to ensure the continuous force transmission of the motor arm structure.

[0043] The connecting frame 11 is connected to the wing, and the connection method is adhesive riveting. That is, the main mating surfaces are connected with structural adhesive, and pop rivets are installed at certain intervals to prevent the adhesive layer from peeling off. The adhesive riveting method between the connecting frame 11 and the wing can ensure that the connection between the connecting frame 11 and the left skin 13, right skin 12 and wing can effectively transmit the aerodynamic load of the lift system.

[0044] The rectifier 14 is connected to the motor mount 15 by fasteners and is a detachable structure. When the rectifier 14 and the motor mount 15 are assembled into an integral structure, a wire passage groove is left between the rectifier 14 and the motor mount 15. The motor wiring harness is passed through the wire passage groove into the motor arm 1, which can fix and maintain the internal wiring harness. When the rectifier 14 and the motor mount 15 are assembled into an integral structure, the rectifier 14 is the end shape of the motor arm structure. While maintaining the rectifier shape, it can also serve as a maintenance cover. After disassembling the rectifier 14, the wiring harness inside the motor arm 1 can be maintained and the internal structure of the motor mount 15 can be inspected. At the same time, the motor and ESC are exposed on the outer surface of the motor arm 1, and maintenance can be carried out directly without disassembling other structural components. Thus, this utility model has the advantage of good maintainability.

[0045] The fairing 14 is a 3D printed plastic part made of PA12. In order to improve the rigidity of the fairing 14 and maintain its shape, a longitudinal and transverse reinforcing structure 141 is designed inside. The reinforcing structure 141 is made of the same material as the fairing 14, 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.

[0046] The motor mount 15 is a cage structure machined from a single aluminum alloy. The material of the motor mount 15 is 7075 aluminum alloy, and the heat treatment state is T7351. It has high strength and rigidity. The motor mount 15 is mainly responsible for bearing concentrated loads and distributing the concentrated loads to the right skin 12 and the left skin 13, so that the stress on the right skin 12 and the left skin 13 is small and uniform. When the motor mount 15 bears the load of the lifting unit, it maintains the stability and integrity of the structure.

[0047] The motor mount 15 has motor mounting platforms on both the top and bottom sides, and ESC connection platforms on both the left and right sides. The motor mount 15 has a hollow internal structure. Lifting units (motor + blades) are installed on both the top and bottom of the motor mount 15. That is, the motor is installed on the motor mount 15, and the blades are installed on the motor output end. ESCs are installed on both the left and right sides of the motor mount 15. The wiring harnesses of the power supply motor and ESC pass through the inside of the motor mount 15. The inside of the motor mount 15 is equipped with anti-wear sleeves to prevent the wiring harness from wearing out. The anti-wear sleeves can prevent the wiring harness from wearing out and avoid short circuit accidents.

[0048] like Figure 4As shown, after the right skin 12 and the left skin 13 are glued together, they form a cylindrical structure. The cylindrical structure has openings for mounting the connecting frame 11 and the motor mount 15. That is, the upper and lower sides and the left and right sides of the cylindrical structure are open. After the motor mount 15 is glued to the right skin 12 and the left skin 13 with structural adhesive, the upper and lower sides and the left and right sides of the motor mount 15 are exposed. When the lift unit (motor + blade) is installed on the upper and lower sides of the motor mount 15, the motor and blade of the lift unit are exposed. When the ESC is installed on the left and right sides of the motor mount 15, the ESC is exposed. Since the motor and ESC are exposed on the outer surface of the motor arm 1, the propeller wind is used for heat dissipation during vertical take-off and landing, and the airflow of the UAV flying forward can be used for heat dissipation during level flight. This gives the present invention the advantage of good heat dissipation performance.

[0049] After the right skin 12 and the left skin 13 are glued together, they form a cylindrical structure. The cylindrical structure has an opening for easy maintenance. A maintenance cover 17 is installed at the opening by fasteners. The maintenance cover 17 is a 3D printed plastic part made of PA12. The wire harness inside the electrode arm 1 can be easily maintained by removing the maintenance cover.

[0050] The fasteners mentioned in this embodiment include, but are not limited to, screws and bolts.

[0051] In summary, the rectifier 14 of this utility model is the end shape of the motor arm structure. While maintaining the rectifier shape, it can also serve as a maintenance cover. After disassembling the rectifier 14, the wiring harness inside the motor arm 1 can be maintained, and the internal structure of the motor base 15 can be inspected. At the same time, the motor and ESC are exposed on the outer surface of the motor arm 1, and maintenance can be carried out directly without disassembling other structural components. Thus, this utility model has the advantage of good maintainability.

[0052] With the motor and ESC exposed on the outer surface of the motor arm 1, the propeller wind is used for heat dissipation during vertical take-off and landing, and the airflow from the forward flight of the UAV is used for heat dissipation during level flight, giving this invention the advantage of good heat dissipation performance.

[0053] The motor mount 15 is a cage-like structure machined from a single aluminum alloy, which has high strength and rigidity. It can effectively withstand the torque, tension and other loads of the UAV's vertical take-off and landing. It has high strength and good safety, ensuring that the motor mount 15 has high rigidity, reducing deformation, and facilitating the flight control of the UAV.

[0054] 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 composite-wing electric unmanned aerial vehicle (UAV) motor arm structure, characterized in that, include: Motor arm (1), which connects the lift unit of the UAV to the wing; The motor arm (1) includes a connecting frame (11), a right skin (12), a left skin (13), a fairing (14), and a motor base (15). The right skin (12) and the left skin (13) are bonded together with the connecting frame (11) and the motor base (15) by structural adhesive to form the main load-bearing body. The connecting frame (11) is connected to the wing. The fairing (14) is detachably connected to the front of the motor base (15). When the fairing (14) and the motor base (15) are assembled into an integral structure, the fairing (14) is the end shape of the motor arm structure. While maintaining the rectified shape, it can also serve as a maintenance cover to maintain the wiring harness inside the motor arm (1) and to inspect the internal structure of the motor base (15). The motor mount (15) is used to mount the motor and ESC.

2. The composite wing electric drone motor arm structure according to claim 1, wherein, Both the right skin (12) and the left skin (13) are provided with a "stepped" bonding surface to ensure the bonding strength, and the width of the "stepped" bonding surface is 30mm.

3. The composite wing electric drone motor arm structure according to claim 1, wherein, Both the right skin (12) and the left skin (13) are made of carbon fiber composite material.

4. The composite-wing electric unmanned aerial vehicle (UAV) motor arm structure according to claim 1, characterized in that, It also includes a support frame (16), which is connected to the left skin (13) and the right skin (12) by structural adhesive.

5. The composite-wing electric unmanned aerial vehicle (UAV) motor arm structure according to claim 1, characterized in that, After the right skin (12) and the left skin (13) are glued together, they form a cylindrical structure, and the cylindrical structure is provided with an opening for mounting the connecting frame (11) and the motor base (15).

6. The composite-wing electric unmanned aerial vehicle (UAV) motor arm structure according to claim 1, characterized in that, The connection frame (11) is connected to the wing by adhesive riveting.

7. The composite wing electric drone motor arm structure according to claim 1, wherein, When the fairing (14) and the motor mount (15) are assembled into an integral structure, a wire pass-through groove is left between the fairing (14) and the motor mount (15) to pass the motor wire harness through the wire pass-through groove into the motor arm (1). The fairing (14) is provided with a reinforcing structure (141).

8. The composite wing electric drone motor arm structure according to claim 1, wherein, It also includes a maintenance cover (17). The right skin (12) and the left skin (13) are glued together to form a cylindrical structure, and the cylindrical structure is provided with an opening for installing the maintenance cover (17).

9. The composite wing electric drone motor arm structure according to claim 1, wherein, The motor mount (15) is made of 7075 aluminum alloy and has a heat treatment state of T7351. It has high strength and rigidity. The motor mount (15) mainly bears the concentrated load and distributes the concentrated load to the right skin (12) and the left skin (13), so that the stress on the right skin (12) and the left skin (13) is uniform. When the motor mount (15) bears the load of the lifting unit, it maintains structural stability and integrity.

10. The composite-wing electric unmanned aerial vehicle (UAV) motor arm structure according to claim 1, characterized in that, The motor mount (15) has a hollow interior. Motors are installed on both the top and bottom of the motor mount (15). Electric speed controllers are installed on both the left and right sides of the motor mount (15). The wiring harnesses of the motors and electric speed controllers pass through the interior of the motor mount (15). A wear-resistant sleeve for preventing wear of the wiring harnesses is installed inside the motor mount (15).

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