UAV leading edge skin

Abstract

This utility model relates to a leading edge skin for an unmanned aerial vehicle (UAV), comprising a core material and inner and outer panels. The panels and the core material form a sandwich structure. A solar panel is connected to the upper surface of the outer panel of the core material. A recessed area is provided on the upper surface of the outer panel of the core material to accommodate the solar panel. A weight reduction structure is provided on the core material and / or at least one panel.

Description

Technical Field

[0001] This invention relates to the field of aviation technology, and more specifically to the leading edge skin of unmanned aerial vehicles (UAVs). Background Technology

[0002] See appendix Figure 1 Currently, most commonly used solar-powered drone structures use a single foam block (100) to fill the leading edge, resulting in significant weight. This requires machining to create the leading edge shape, leading to high costs. Furthermore, the exposed foam is susceptible to damage from impacts, affecting aerodynamic performance and reducing maintainability. After attaching a solar panel (200) to the upper edge, a step difference is created on the surface, increasing aerodynamic drag. This type of solar-powered drone technology has the following drawbacks.

[0003] 1. Significant Weight: To achieve high altitude and long endurance flight performance, controlling the structural weight of solar-powered drones is crucial. Currently, most commonly used solar-powered drone structures use a single piece of foam to fill the leading edge, resulting in significant weight.

[0004] 2. High cost: Filling with foam requires machining the leading edge shape, which is costly.

[0005] 3. Poor maintainability: The exposed foam padding is easily damaged by bumps and knocks. The damaged shape affects the aerodynamic performance of the drone, resulting in poor maintainability.

[0006] 4. Poor aerodynamic performance: After the solar panel is attached to the upper surface of the upper edge, a step difference will be generated on the surface, which will increase the aerodynamic drag. Summary of the Invention

[0007] To avoid the aforementioned technical defects in the background art, this utility model provides a drone, the wing structure of which is shown in the appendix. Figure 2 The wing includes a leading-edge skin, which comprises a core material and inner and outer panels. The panels and the core material form a sandwich structure. A solar panel is connected to the upper surface of the outer panel of the core material. A recessed area is provided on the upper surface of the outer panel of the core material to accommodate the solar panel. A weight-reduction structure is provided on the core material and / or at least one panel.

[0008] Furthermore, the depth of the sunken area is adapted to the solar panel, so that the aerodynamic shape of the skin is a smooth surface after the solar panel is installed.

[0009] Furthermore, the weight-reducing structure is a weight-reducing hole.

[0010] Furthermore, the panel has a connection structure for connecting with other structures of the drone.

[0011] Furthermore, the connecting structure is an ear piece.

[0012] Furthermore, the panel and core material are formed through a co-curing process.

[0013] Furthermore, the panel is made of carbon fiber material.

[0014] Furthermore, the core material is foam.

[0015] Furthermore, the core material is polyvinyl chloride.

[0016] This utility model also provides a drone, including the aforementioned drone leading edge skin.

[0017] The skin of this invention features a sandwich structure, resulting in high leading-edge stiffness and enhanced drop resistance for the drone. The foam is not exposed, making it less susceptible to damage from impacts and minimizing aerodynamic performance degradation. It also offers good maintainability. The use of lightweight materials and the inclusion of weight-reducing structures contribute to a lighter drone weight. The foam does not require machining to create the leading-edge shape, reducing costs. The recessed structure on the upper surface of the skin allows space for connections to solar panels and other structures, preventing a step difference on the leading-edge surface and ensuring no impact on aerodynamic performance. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the structure of a solar-powered drone in the background technology;

[0019] Figure 2 This is a schematic diagram of the wing structure of the solar-powered drone of this utility model;

[0020] Figure 3 This is a schematic diagram of the skin sandwich structure of this utility model;

[0021] Figure 4 This is a schematic diagram of the recessed structure and weight reduction structure of the outer skin panel of this utility model. Detailed Implementation

[0022] For ease of description, in the following text, the direction in which the leading edge of the aircraft faces the wind during flight is "front", the opposite direction is "rear", the vertically upward direction is "up", and the opposite direction is "down".

[0023] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0024] See appendix Figure 2This utility model provides a drone wing, including a leading edge skin 101, a solar panel 102, a rib 103, and a main beam 104.

[0025] See appendix Figure 3 The leading edge skin 101 of the UAV includes a sandwich structure composed of panels 1 and 3 and a core material 2. The sandwich structure of the leading edge skin 101 can be a solid or hollow sandwich structure, and optionally composed of two or more layers. In the hollow sandwich structure, panels 1 and 3 are specifically two layers, namely a first panel 1 disposed on the outside of the core material 2 and a second panel 3 disposed on the inside of the core material 2.

[0026] See appendix Figure 4 A recessed area 4 is provided on the upper surface of the panel 1 located outside the core material 2 to ensure that the aerodynamic shape of the skin is integrated, smooth, and complete after connecting the solar panel or other structures, reducing air resistance and minimizing aerodynamic losses. The recessed area for connecting the solar panel is located in a relatively flat area on the upper surface of the leading edge.

[0027] A connecting structure 5 is provided at the lower part of the panel 1 located on the outer side of the core material 2 to enable connection with other structures of the drone. This connecting structure 5 can be specifically selected as an ear piece 5 or other commonly used connecting structures for drones.

[0028] A weight-reducing structure 6 is provided on one or more panels 1 and 3, for example, it can be configured as a weight-reducing hole 6, to achieve weight reduction.

[0029] Panels 1 and 3 are made of lightweight materials, such as carbon fiber and lightweight metals, to reduce the weight of the drone.

[0030] Panels 1 and 3 are made of high-strength materials to avoid impact damage to aerodynamic performance.

[0031] The core material 2 is made of foam, plastic, or honeycomb material, such as high-toughness foam, which can improve structural toughness while reducing weight; or thermoplastic plastic; or polyvinyl chloride (PVC).

[0032] The core material 2 is provided with a lightening structure, such as a lightening hole 6.

[0033] Panels 1 and 3 and core material 2 are formed by an integral molding process, especially a co-curing process.

[0034] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A leading edge skin for an unmanned aerial vehicle (UAV), characterized in that, The core material (2) and two inner and outer panels (1, 3) are included. The panels (1, 3) and the core material (2) form a sandwich structure. The upper surface of the outer panel (1) of the core material (2) is connected to the solar panel. A recessed area (4) is provided on the upper surface of the outer panel (1) of the core material (2). The recessed area (4) is used to accommodate the solar panel. A weight reduction structure (6) is provided on the core material (2) and / or at least one panel (1, 3).

2. The UAV leading edge skin according to claim 1, characterized in that, The depth of the sunken area (4) is adapted to the solar panel, so that the aerodynamic shape of the skin is a smooth surface after the solar panel is installed.

3. The UAV leading edge skin according to claim 1, characterized in that, The weight-reducing structure (6) is a weight-reducing hole.

4. The leading edge skin of the unmanned aerial vehicle according to any one of claims 1-3, characterized in that, The panels (1, 3) and the core material (2) are formed by a co-curing process.

5. The leading edge skin of the unmanned aerial vehicle according to any one of claims 1-3, characterized in that, The panels (1, 3) are made of carbon fiber material.

6. The leading edge skin of the unmanned aerial vehicle according to any one of claims 1-3, characterized in that, The core material (2) is foam.

7. The leading edge skin of the unmanned aerial vehicle according to any one of claims 1-3, characterized in that, The core material (2) is polyvinyl chloride.

8. A drone, characterized in that, Includes the leading edge skin of the unmanned aerial vehicle as described in any one of claims 1-7.

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