Central wing structure of unmanned aerial vehicle

Abstract

The utility model discloses a central wing structure of an unmanned aerial vehicle, which comprises a framework, a skin is supported and connected outside the framework, GNSS antenna platforms are arranged at two ends of the skin, fastener mounting platforms are arranged on two sides of each GNSS antenna platform, and a covering cap is arranged in the middle of the skin. The front tubular beam, the front plate beam and the two main force transmission structures are arranged at the position of the central wing on the main beam, when one part loses efficacy, the other part can still bear the limiting load, and safety is high. The central wing and the outer wing are connected through the front tubular beam and the rear tubular beam, the outer diameters of the two tubular beams of the outer wing are the same as the inner diameters of the front tubular beam and the rear tubular beam of the central wing, the outer wing is directly inserted between the front tubular beam and the rear tubular beam and then locked through the lock catch on the skin, and connection is convenient.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, and particularly relates to a central wing structure of an unmanned aerial vehicle. Background Art

[0002] An unmanned aerial vehicle is an unpiloted aircraft controlled by a radio remote control device and a self-contained program control device, and has the characteristics of small volume, low cost and convenient use. The combination of unmanned aerial vehicles and industrial applications is the real demand for unmanned aerial vehicles. Their applications in fields such as aerial photography, agriculture, plant protection, micro selfies, express delivery, disaster relief, wildlife observation, monitoring of infectious diseases, mapping, news reporting, power line inspection, disaster relief, film shooting, creating romance, etc. have greatly expanded the uses of unmanned aerial vehicles themselves.

[0003] The main function of the wing of an unmanned aerial vehicle is to generate lift to support the unmanned aerial vehicle to fly in the air. The design and structure of the wing will vary according to the type and use of the unmanned aerial vehicle. Ailerons and flaps are usually installed on the wing. The ailerons are used to control the rolling motion of the unmanned aerial vehicle, while the flaps are used to increase the lift during takeoff and landing. The wing may also be equipped with components such as engines, landing gears and fuel tanks. There may be a fuel tank installed inside some wings, and the lower surface may be used for hanging additional equipment such as auxiliary fuel tanks and weapons. In addition, under specific designs, the wing of an unmanned aerial vehicle can also be equipped with a power device, such as a propeller or a jet engine, to generate thrust to help the unmanned aerial vehicle overcome the earth's gravity and achieve flight in the air.

[0004] The wing structure is mainly composed of spanwise beams, chordwise ribs and upper and lower skins. The skins can be divided into leading edge, trailing edge and wing box skins according to the forming method, and are mainly composed of composite material structures, metal structures, etc. As the part of the wing middle area that bears the greatest force, the central wing is connected to the fuselage at the lower part and to the outer wing at the outer side. The forces of the whole aircraft converge in the central wing area, and the force is complex. Special attention should be paid during design. However, the connections of many existing central wings are complex, inconvenient to disassemble, and have poor load-bearing capacity. Content of the Utility Model

[0005] The purpose of the utility model is to provide a central wing structure of an unmanned aerial vehicle to solve the problems mentioned in the background art. To achieve the above purpose, the utility model provides the following technical solution: A central wing structure of an unmanned aerial vehicle, including a framework, a skin is supported and connected to the outside of the framework, GNSS antenna platforms are arranged at both ends of the skin, fastener installation platforms are arranged on both sides of the GNSS antenna platforms, and an access panel is arranged in the middle of the skin.

[0006] Preferably, the skeleton includes a front tube beam, a front plate beam is installed on the front tube beam, a rear plate beam is provided on the rear side of the front tube beam, ribs are installed between the front plate beam and the rear plate beam, both ends of the rear plate beam are connected to the rear tube beam, a GNSS antenna mounting plate is installed between the rear tube beam and the front tube beam, a central fixing platform is installed between the middle of the front plate beam and the rear plate beam, the central fixing platform and the GNSS antenna mounting plate are connected to ribs on both sides, and connected to connecting seats at both ends.

[0007] Preferably, the skin is a carbon fiber composite foam sandwich structure.

[0008] Preferably, the connecting seat includes a supporting block, a metal sleeve is installed inside the supporting block, and the supporting block connects the ribs and the central fixing platform.

[0009] Preferably, the front tube beam and the rear tube beam are carbon fiber composite material round tubes, and the front plate beam, the rear plate beam and the ribs are all provided with weight-reducing holes.

[0010] The technical effects and advantages of the utility model are as follows: the structure is highly safe: the central wing is located at the main beam position, and the front tube beam and the front plate beam are arranged, which are two main force transmission structures. When one part fails, the other part can still bear the limited load, which is highly safe;

[0011] Easy connection: The center wing and outer wings are connected by the front and rear tubular beams. The outer diameters of the two tubular beams of the outer wing are the same as the inner diameters of the front and rear tubular beams of the center wing. They are directly inserted between the front and rear tubular beams and then locked with the locks on the skin, making the connection easy.

[0012] Easy to disassemble: The central wing is connected to the fuselage and motor arm in the form of a connecting seat. The fasteners are inserted into the metal sleeve of the connecting seat to connect with the fuselage and motor arm structure. Only 8 fasteners need to be removed to complete the connection with the motor arm and fuselage.

[0013] High load-bearing capacity: The central fixed platform is assembled from multiple plate parts, and it bears the bending moment, shear force and other loads transmitted to the middle part by the central wing. It has strong structural strength and high load-bearing capacity. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 An axonometric drawing of the utility model assembled with a drone;

[0015] Figure 2 This is an axonometric drawing of the present utility model;

[0016] Figure 3 It is an exploded view of the utility model;

[0017] Figure 4 It is an axonometric drawing of the skeleton of the utility model;

[0018] Figure 5 This is a partial view of the connecting seat and its surrounding structure of the present utility model;

[0019] Figure 6 This is a sectional view of the position of the connecting seat of the present utility model.

[0020] In the figure, 1. Central wing structure; 11. Skin; 111. GNSS antenna platform; 112. Access cover; 113. Fastener installation platform; 12. Skeleton; 121. Connecting seat; 1211. Metal sleeve; 1212. Support block; 122. Front tube beam; 123. Front plate beam; 124. Rear plate beam; 125. Rib; 126. Rear tube beam; 127. GNSS antenna mounting plate; 128. Central fixing platform; 2. UAV. Detailed implementation manners

[0021] In order to make the implementation means, creative features, achieved purposes and effects of the present utility model easy to understand, the present utility model will be further described below with reference to specific illustrations. In the description of the present utility model, it should be noted that unless otherwise clearly specified and limited, the terms "installation", "connection", and "coupling" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection or a mechanical connection, and it can also be an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, and the interiors of two components can be communicated.

[0022] Embodiment

[0023] As Figure 1 shown, the central wing structure 1 is located at the upper part of the UAV fuselage and in the middle of the wing, bearing the main loads of the whole machine, the aerodynamic loads during flight, the pulling force of the motor driving the propeller, the overload during landing, etc. All these are balanced at the position of the central wing structure 1, which is the component with the greatest stress and the most important component of the whole machine. When the UAV 2 is in use, the requirements for transportation and quick reinstallation need to be considered. Therefore, quick connection and disassembly are required between the central wing and the fuselage, between the central wing and the outer wing, and between the central wing and the motor arm.

[0024] As Figure 2 and Figure 3As shown in the figure, the central wing structure 1 includes a skin 11 and a framework 12. The skin 11 is installed outside the framework 12. The skin 11 is a carbon fiber composite foam sandwich structure, which improves the buckling resistance of the skin 11. At the position where the skin 11 is connected to the GNSS antenna, a GNSS antenna platform 111 is designed to ensure the mating of the bottom surface of the GNSS antenna and improve the firmness of the connection of the GNSS antenna. A hatch 112 is provided in the middle of the skin 11. The hatch 112 is a detachable structure. Equipment such as a flight control computer is installed inside the central wing. The hatch 112 provides a maintenance passage for maintaining the equipment inside the central wing. Fastener installation platforms 113 are provided on both sides of the GNSS antenna platform 111. The fastener installation platforms 113 are designed at the positions of the connection seats with the framework 12, so that the bottom surfaces of the fasteners connecting the central wing structure to the fuselage and the motor arms are flush with the skin 11, ensuring the reliability of the fastener connection.

[0025] The framework 12 is the main load-bearing structure. The loads received by the central wing are borne and balanced by the framework 12. The framework 12 also serves as a support structure for the internal equipment, providing interfaces for equipment installation. The framework 12 and the skin 11 are connected by structural adhesive, which plays a role in supporting the skin 11 and at the same time transmits the aerodynamic force received by the skin 11 to the framework 12.

[0026] As Figure 4 and Figure 5 As shown in the figure, the framework 12 includes connection seats 121, front tube beams 122, front plate beams 123, rear plate beams 124, ribs 125, rear tube beams 126, GNSS antenna mounting plates 127, and central fixing platforms 128. A front plate beam 123 is installed on the front tube beam 122. A rear plate beam 124 is provided behind the front tube beam 122. A rib 125 is installed between the front plate beam 123 and the rear plate beam 124. The rear plate beam 124 is connected to the rear tube beams 126 at both ends. A GNSS antenna mounting plate 127 is installed between the rear tube beam 126 and the front tube beam 122. A central fixing platform 128 is installed between the middle parts of the front plate beam 123 and the rear plate beam 124. The central fixing platform 128 and the GNSS antenna mounting plate 127 are connected to the ribs 125 on both sides and to the connection seats 121 at both ends. The front tube beam 122 and the rear tube beam 126 are supported by carbon fiber composite round tubes and are connected to the tube beams of the outer wing at both ends. The front plate beam 123, the rear plate beam 124, the ribs 125, the GNSS antenna mounting plate 127, and the central fixing platform 128 are all flat plates made of carbon fiber composites assembled by splicing. Except for the important structures of the front plate beam 123 and the rear plate beam 124, weight reduction holes are designed on other plate-like parts to reduce the weight. The central fixing platform 128 houses system equipment such as a flight control computer, providing support for the system equipment and ensuring the firm installation of the equipment.

[0027] As Figure 6As shown, the connecting seat 121 is composed of an internal metal sleeve 1211 and an external support block 1212. The metal sleeve 1211 cooperates with the internal fastener to improve the wear resistance between them during each disassembly. The support block 1212 connects the rib 125 and the central fixing platform 128. The support block 1212 supports the metal sleeve 1211 to prevent the metal sleeve 1211 from skewing, resulting in a position change and inability to be connected to the fuselage and the motor arm. At the same time, the support block 1212 distributes the concentrated load on the metal sleeve 1211 to the surrounding plate-like parts of the carbon fiber composite material to complete the force transmission.

[0028] Finally, it should be noted that the above are only the preferred embodiments of the present invention and are not used to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A central wing structure of an unmanned aerial vehicle, comprising a skeleton, characterized in that: The outer support of the framework is connected with a skin. GNSS antenna platforms are arranged at both ends of the skin. Fastener installation platforms are arranged on both sides of the GNSS antenna platforms. An access panel is arranged in the middle of the skin.

2. The central wing structure of a drone according to claim 1, wherein: The framework includes a front tube beam. A front plate beam is installed on the front tube beam. A rear plate beam is arranged behind the front tube beam. Ribs are installed between the front plate beam and the rear plate beam. Rear tube beams are connected to both ends of the rear plate beam. A GNSS antenna mounting plate is installed between the rear tube beam and the front tube beam. A central fixing platform is installed between the middle parts of the front plate beam and the rear plate beam. Ribs are connected to both sides of the central fixing platform and the GNSS antenna mounting plate. Connecting seats are connected to both ends.

3. The central wing structure of a drone according to claim 1, characterized in that: The skin is a carbon fiber composite foam sandwich structure.

4. The central wing structure of an unmanned aerial vehicle according to claim 2, characterized in that: The connecting seat includes a support block. A metal sleeve is installed inside the support block. The support block is connected to the rib and the central fixing platform.

5. The central wing structure of an unmanned aerial vehicle according to claim 2, characterized in that: The front tube beam and the rear tube beam are carbon fiber composite round tubes. Lightening holes are provided on the front plate beam, the rear plate beam and the ribs.

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