Wing structure of unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle wing structure which comprises a wing body, the wing body is installed on a motor arm through a fastener, the wing body comprises a wing skin, the wing skin is provided with an aileron skin at the aileron position, and a gap is formed between the aileron skin and the wing skin. The wing skin and the aileron skin are mounted on the wing framework. The structure is good in aerodynamic performance, the wing skin is of a foam sandwich structure, the thickness is large, the rigidity is good, the wing skin cannot deform due to aerodynamic force of the surface of the wing in the flying process, and the aerodynamic performance of the wing is effectively kept.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a wing structure of a UAV. Background Art

[0002] A drone is an unmanned aerial vehicle controlled by a radio remote control device and a self-contained program control device. It is characterized by small size, low cost and easy use. Drone + industry application is the real demand for drones; its application in aerial photography, agriculture, plant protection, micro selfies, express transportation, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, creating romance and other fields has greatly expanded the use of drones themselves.

[0003] Composite-wing drones, also known as vertical take-off and landing fixed-wing drones, are a significant innovation in aeronautical engineering. Their design culminates in a clever integration of the efficient cruising characteristics of fixed-wing aircraft with the vertical take-off and landing, hovering flexibility of rotary-wing drones. The fixed-wing structure primarily provides lift, enabling the drone to fly long distances and at high speeds in level flight with minimal energy consumption. This fixed-wing design enables the drone to maintain a stable attitude in the air, facilitating long-range missions and high-altitude operations. The rotor system typically utilizes a multi-rotor design (such as a quadrotor or hexacopter) to enable vertical take-off and landing, as well as hovering. The rotor provides the necessary lift and attitude control during takeoff, landing, and low-speed flight, eliminating the need for long runways or catapults for traditional fixed-wing drones. The wing structure primarily consists of span-wise beams, chord-wise ribs, and upper and lower skins, which connect to other structures. The wing structure also serves as the rotor system's support structure, connecting the motor arms and meeting the drone's load and flight requirements. Many existing drone wing structures use fixed-wing wing structures. For example, the Chinese utility model patent application number 201721365279.9, "A fixed-wing drone outer wing structure," cannot be used on vertical take-off and landing composite-wing drones. It lacks a connection method with structures such as motor arms, does not fully utilize the space inside the wing, and does not install related equipment. Utility Model Content

[0004] The present invention aims to provide a drone wing structure to solve the problems mentioned in the background art. To achieve the above-mentioned object, the present invention provides the following technical solution: a drone wing structure, comprising a wing body, the wing body being mounted on a motor arm via fasteners, the wing body comprising a wing skin, the wing skin being provided with an aileron skin at the position of the aileron, a gap being provided between the aileron skin and the wing skin, and the wing skin and the aileron skin being mounted on a wing frame.

[0005] Preferably, the wing frame includes a beam, which is distributed in the span direction, and organic ribs are installed on the beam along the chord direction, and the wing ribs are connected to support the wing skin. A connecting block is installed in the middle of the beam, and the connecting block is connected to the wing skin. An aileron frame is installed on the beam, and the aileron skin is installed on the aileron frame. The aileron frame is connected to the servo, and the servo is installed on the servo mounting plate, and the servo mounting plate is installed on the wing skin.

[0006] Preferably, the beam is provided with a plate beam and a round tube beam, the round tube beam is installed at the inner end of the plate beam, and the wing ribs, connecting blocks and aileron frames are installed on the plate beam.

[0007] Preferably, the motor arm includes a motor arm skin, a wire passing hole is opened in the middle of the motor arm skin, motor arm connecting joints are provided on both sides of the wire passing hole, the motor arm connecting joints are fixed inside the motor arm skin, power unit mounting assemblies are installed at both ends of the motor arm skin, a power unit is installed on the power unit mounting assembly, and a frame is installed inside the motor arm skin.

[0008] Preferably, the frame is a ring-shaped structure with a hole inside.

[0009] Preferably, the power unit includes a motor and an electric regulator, and the electric regulator is connected to the motor via a power harness.

[0010] Preferably, the power unit mounting assembly includes an electric adjustment mounting plate, two parallel support plates are installed on the electric adjustment mounting plate, a motor mounting plate is installed above the two support plates, a motor is installed on the motor mounting plate, the electric adjustment is installed on the electric adjustment mounting plate, and the electric adjustment mounting plate is installed on the motor arm.

[0011] Preferably, flanges are provided at both ends of the motor arm connection joint, a boss is provided in the middle of the motor arm connection joint, and a threaded hole is provided on the boss.

[0012] Preferably, the motor arm connecting joint is connected to the connecting block through a fastener, a motor arm skin and a wing skin are provided between the motor arm connecting joint and the connecting block, and the fastener passes through the motor arm skin and the wing skin.

[0013] Preferably, the fastener is a bolt.

[0014] The technical effects and advantages of the utility model are as follows: the structure has good aerodynamic performance: the wing skin adopts a foam sandwich structure, which is thicker and has good rigidity. During flight, it will not be deformed due to the aerodynamic force on the wing surface, effectively maintaining the aerodynamic performance of the wing;

[0015] Good heat dissipation effect: The ESC is placed under the motor, and the heat dissipation plate is exposed outside the motor arm structure, using the wind from the propeller for heat dissipation, which is effective;

[0016] Easy to disassemble: The motor arm is connected to the wing body by two bolts. When disassembling, you only need to unscrew the bolts, which is easy to disassemble;

[0017] Good stability: The motor arm skin is supported by the motor arm connection joint and the frame. When subjected to motor tension, the upper part of the motor arm skin will not buckle, and has good stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is an axonometric drawing of the present utility model;

[0019] Figure 2 It is an exploded view of the utility model;

[0020] Figure 3 This is an exploded view of the wing body of the utility model;

[0021] Figure 4 This is an axonometric view of the wing skeleton of the utility model;

[0022] Figure 5 This is an exploded view of the motor arm of the utility model;

[0023] Figure 6 This is an axonometric drawing of the power unit installation assembly and the power unit of the utility model installed together;

[0024] Figure 7 This is an axonometric view of the motor arm connection joint of the utility model;

[0025] Figure 8 This is a transverse cross-sectional view of the connection between the wing and the motor arm of the utility model;

[0026] Figure 9 This is an axonometric drawing of the utility model assembled with a drone.

[0027] In the figure, 1. Wing structure; 11. Wing body; 111. Wing frame; 1111. Beam; 1112. Connecting block; 1113. Wing rib; 1114. Servo mounting plate; 1115. Aileron frame; 112. Wing skin; 1121. Aileron skin; 12. Motor arm; 121. Power unit; 1211. Motor; 1212. ESC; 122. Power unit mounting assembly; 1221. Support plate; 1222. Motor mounting plate; 1223. ESC mounting plate; 123. Motor arm skin; 1231. Wire hole; 124. Motor arm connecting joint; 1241. Flanged edge; 1242. Boss; 125. Frame; 13. Bolt; 2. UAV. DETAILED DESCRIPTION

[0028] In order to make the technical means for realizing the present invention, the creative features, the purpose and the effect easily understood, the present invention is further explained below in conjunction with specific diagrams. In the description of the present invention, it should be noted that, unless otherwise clearly stipulated and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, an integral connection or a mechanical connection, or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be internal communication between two components.

[0029] Example

[0030] like Figure 9 As shown, the wing structure 1 is arranged on the outside of the UAV 2, and the outer motor arm and power unit are connected to the wing structure. When the UAV 2 takes off and lands vertically, they provide half of the pulling force. During level flight, the outer wing structure provides aerodynamic force. At the same time, the aileron on the wing structure 2 deflects to provide control force for the rolling of the UAV 2.

[0031] like Figure 1 , Figure 2 As shown, the wing structure 1 includes a wing body 11 and a motor arm 12. The wing body 11 is mounted on the motor arm 12 via fasteners. In this example, the fasteners are two bolts 13, which allow for easy disassembly of the wing body 11 and the motor arm 12. The motor arm 12 is arranged at the bottom of the wing body 11. The lift generated by the power unit measured by the motor arm 12 is transferred to the wing body 11 via the bolts 13. The lift is then transferred to the central wing through the wing body 11 for balancing.

[0032] like Figure 3 As shown, the wing body 11 includes a wing frame 111 and a wing skin 112. The wing skin 112 is divided into aileron skin 1121 at the position of the aileron. There is a certain gap between the aileron skin 1121 and the wing skin 112. When the aileron moves, the aileron skin will not interfere with the wing skin 112. The preferred gap size is 3-5mm. The wing skin 112 bears aerodynamic forces. The wing skin 112 and the aileron skin 1121 preferably adopt a carbon fiber composite foam sandwich structure, and the wing skin 112 and the aileron skin 1121 are installed on the wing frame 111. The wing frame 111 provides support for the wing skin 112 and transmits the main load of the wing structure.

[0033] like Figure 4As shown, the wing skeleton 111 includes a span-wise beam 1111, a chord-wise wing rib 1113, a connecting block 1112 connected to the motor arm 12, a servo mounting plate 1114 and an aileron skeleton 1115. The wing rib is installed on the beam, the wing rib 1113 is connected to and supports the wing skin 112, a connecting block 1112 is installed in the middle of the beam 1111, the connecting block 1112 is connected to the wing skin 112, an aileron skeleton 1115 is installed on the beam 1111, the aileron skin 1121 is installed on the aileron skeleton 1115, the aileron skeleton 1115 is connected to the servo, and the servo mounting plate 1114 is installed on the wing skin 112; the beam 1111 is made of carbon fiber composite material, and a round tube beam is used on the inner side to facilitate cooperation with the round tube beam of the central wing, and is inserted into the inside of the round tube beam of the central wing to complete the installation with the central wing. Plate beams are used on the outside to support the upper and lower parts of the wing skin, forming an integral structure with low cost. The wing ribs 1113 support the wing skin 112 to prevent the wing skin 112 from buckling when subjected to aerodynamic forces, and at the same time transmit the shear force of the aerodynamic forces of the wing skin 112 to the beam 1111. The connecting block 1112 is an aluminum alloy machined part, which is connected to the wing frame 111 and the wing skin 112. The internal circular hole is connected to the bolt 13 to transmit the force of the motor arm 12 to the connecting block. The servo mounting plate 1114 is installed on the wing skin 112, and the servo is installed on the servo mounting plate 1114 to control the aileron. The servo mounting plate 1114 bears the torque transmitted by the deflection of the aileron. The aileron frame 1115 supports the aileron skin 1121 and transmits the main load of the aileron.

[0034] like Figure 5As shown, the motor arm 12 includes a power unit 121, a power unit mounting assembly 122, a motor arm skin 123, a motor arm connecting joint 124, and a frame 125. A wire passing hole 1231 is opened in the middle of the motor arm skin 123, and motor arm connecting joints 124 are provided on both sides of the wire passing hole 1231. The motor arm connecting joint 124 is fixed to the inside of the motor arm skin 123. The power unit mounting assembly 122 is installed at both ends of the motor arm skin 123. The power unit 121 is installed on the power unit mounting assembly 122. The frame 125 is installed inside the motor arm skin 123. The motor arm skin 123 is a carbon fiber composite material laminate structure, which bears the main load of the motor arm 12. The frame 125 supports the motor arm skin 123 to prevent buckling. The frame 125 is a carbon fiber composite material annular flat plate structure. There are holes inside the frame 125 for the wiring harness to pass through. The motor arm connection joint 124, together with the wing connection block 1112, connects the motor arm 12 and the wing body together through bolts. The power unit 121 provides lift and is installed on both ends of the motor arm 12 through the power unit 121 mounting assembly, maintaining a certain distance from the wing body 11 to prevent the wing from being under the propeller and blocking the airflow of the propeller, thereby reducing the pulling force of the propeller. The power unit mounting assembly 122 installs the power unit 121 thereon, and then connects to the motor arm skin 123 to transfer the force to the skin of the motor arm 12. The motor arm skin 123 is located in a position where the wing is matched, and the designed wire hole 1231 facilitates the wiring harness to pass from the motor arm into the interior of the wing.

[0035] like Figure 6 As shown, power unit 121 includes a motor 1211 and an ESC 1212. Motor 1211 uses electricity to drive the propeller, generating thrust. ESC 1212 controls motor 1211's speed, thereby varying the thrust. ESC 1212 and motor 1211 are connected by a power harness to carry current. The power unit mounting assembly 122 includes a support plate 1221, a motor mounting plate 1222, and an electric adjustment mounting plate 1223. Two parallel support plates 1221 are installed on the electric adjustment mounting plate 1223. The motor mounting plate 1222 is installed above the two support plates 1221. The motor 1211 is installed on the motor mounting plate 1222. The electric adjustment 1212 is installed on the electric adjustment mounting plate 1223, and the electric adjustment mounting plate 1223 is installed on the motor arm 12. The support plate 1221 connects the motor mounting plate 1222 and the electric adjustment mounting plate 1223 together, and then the outer edge is connected to the motor arm skin 123 to form a box structure to bear the load of the motor 1211.

[0036] like Figure 7As shown, both ends of the motor arm connecting joint 124 are designed with flanges 1241 connected to the motor arm skin 123, and the motor arm connecting joint 124 is designed with a boss 1242 at the position where it is connected to the bolt 13 in the middle, and a threaded hole is designed inside to connect with the bolt 13. The boss 1242 is used to increase the length of the thread so that the number of threads that cooperate with the bolt 13 is greater, so that the connection is more reliable. The motor arm connecting joint 124 can be made of aluminum alloy, stainless steel, titanium alloy and other materials, and can be selected according to the number of disassembly requirements. If a large number of disassembly times are required, stainless steel or titanium alloy should be used.

[0037] like Figure 8 As shown, connecting block 1112 connects to wing frame 111 and wing skin 112. It is tall and rigid, and has a clear hole inside. Motor arm connector 124 connects to wing connecting block 1112, sandwiching motor arm skin 123 and wing skin 112. They are then connected using bolts 13, whose threads mate with the threads in the holes of motor arm connector 124. This allows for a single-sided connection, requiring bolt installation from the upper portion of the wing body 11.

[0038] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent replacements for some of the technical features therein. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A UAV wing structure, comprising a wing body, characterized in that: The wing body is mounted on the motor arm through fasteners. The wing body includes a wing skin. The wing skin is provided with an aileron skin at the position of the aileron. A gap is provided between the aileron skin and the wing skin. The wing skin and the aileron skin are mounted on the wing frame.

2. The UAV wing structure according to claim 1, characterized in that: The wing frame includes a beam, which is distributed in the span direction. Organic ribs are installed on the beam along the chord direction. The wing ribs are connected to and support the wing skin. A connecting block is installed in the middle of the beam, and the connecting block is connected to the wing skin. An aileron frame is installed on the beam, and the aileron skin is installed on the aileron frame. The aileron frame is connected to a servo, and the servo is installed on a servo mounting plate, and the servo mounting plate is installed on the wing skin.

3. The UAV wing structure according to claim 2, characterized in that: The beam is provided with a plate beam and a round tube beam, the round tube beam is installed on the inner end of the plate beam, and the wing rib, the connecting block and the aileron frame are installed on the plate beam.

4. The UAV wing structure according to claim 1, characterized in that: The motor arm includes a motor arm skin, a wire passing hole is opened in the middle of the motor arm skin, motor arm connecting joints are provided on both sides of the wire passing hole, the motor arm connecting joints are fixed inside the motor arm skin, power unit mounting assemblies are installed at both ends of the motor arm skin, a power unit is installed on the power unit mounting assembly, and a frame is installed inside the motor arm skin.

5. The UAV wing structure according to claim 4, characterized in that: The frame is a ring-shaped structure with a hole inside.

6. The UAV wing structure according to claim 4, characterized in that: The power unit includes a motor and an electric regulator, and the electric regulator is connected to the motor through a power harness.

7. The UAV wing structure according to claim 6, characterized in that: The power unit mounting assembly includes an electric adjustment mounting plate, on which two parallel support plates are mounted, a motor mounting plate is mounted above the two support plates, a motor is mounted on the motor mounting plate, the electric adjustment is mounted on the electric adjustment mounting plate, and the electric adjustment mounting plate is mounted on the motor arm.

8. The UAV wing structure according to claim 4, characterized in that: The motor arm connecting joint has flanges at both ends, a convex column is provided in the middle of the motor arm connecting joint, and a threaded hole is provided on the convex column.

9. The UAV wing structure according to claim 8, characterized in that: The motor arm connection joint is connected to the connection block through a fastener, a motor arm skin and a wing skin are provided between the motor arm connection joint and the connection block, and the fastener passes through the motor arm skin and the wing skin.

10. The UAV wing structure according to claim 1, characterized in that: The fastener is a bolt.

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