EVTOL aircraft wing skin structure

Abstract

The utility model discloses an eVTOL aircraft wing skin structure which comprises an upper skin, the lower portion of the upper skin is connected with a lower skin, and the front end and the rear end of the butt joint position of the upper skin, the lower skin and a motor arm appearance area are connected with a front splicing piece and a rear splicing piece respectively. According to the structure, the product quality is good, the appearance is complex, the wing appearance area is in lap joint, the motor arm appearance area is in butt joint forming at the combined part of the wing appearance and the motor arm appearance, the defects that the two areas are sunken and the combined part is prone to generating fiber bridging are avoided, and the product quality is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation equipment, and in particular to an eVTOL aircraft wing skin structure. Background Art

[0002] The development of eVTOL (Electric Vertical Takeoff and Landing) electric vertical takeoff and landing aircraft has attracted widespread attention from aerospace companies, the automotive industry, the transportation industry, and academia. Aircraft that rely on electric motors rather than internal combustion engines use electric propulsion systems instead of internal combustion engine power, thereby gaining many advantages and unique qualities. The most prominent advantages are energy saving and environmental protection, high efficiency and low energy consumption, while achieving near-zero emissions, very low noise and vibration levels, and good ride comfort. It is a truly friendly aircraft. In addition, it is safe and reliable (no explosion and fuel leakage), simple structure, easy operation and use, good maintainability / low cost, and good economy. There are also many advantages in design: the overall layout is flexible, the optimal layout and unconventional / innovative layout can be adopted; aircraft with extraordinary performance can be designed to meet special purpose needs, etc.

[0003] Compared with traditional fixed-wing aircraft, the wings of eVTOL aircraft are connected by motor arms, and the pulling force generated by the motor is also transmitted to the wings. In addition to bearing its own aerodynamic force, the wings also need to bear the pulling force generated by the propellers on the motor arms. The main function of aircraft wings is to provide lift. The main external loads borne by the wings include shear force, bending moment and torque. All three loads are generated by the weight of the wing itself and the aerodynamic force. The shape of the wing surface at the wing skin position maintains the lift characteristics of the aircraft during flight, while bearing the loads generated by aerodynamic force. The skin is one of the main load-bearing components. The skin is mainly made of carbon fiber composite materials to reduce the weight of the structure. However, the problem of bridging defects is prone to occur in carbon fiber composite materials at the intersection of the two areas of the skin. Utility Model Content

[0004] The purpose of the utility model is to provide an eVTOL aircraft wing skin structure to solve the problems mentioned in the background technology. To achieve the above purpose, the utility model provides the following technical solutions: an eVTOL aircraft wing skin structure, including an upper skin, a lower skin connected below the upper skin, and a front splicing piece and a rear splicing piece are respectively connected at the front and rear ends of the upper skin, the lower skin and the motor arm outer shape area.

[0005] Preferably, an overlapping edge is provided at one end of the front splicing piece, and the overlapping edge is located at a corner of the upper skin and the lower skin.

[0006] Preferably, a vertical edge is provided at one end of the rear splicing piece.

[0007] Preferably, the upper skin is provided with an overlapping depression at the leading edge of the wing, and the overlapping depression is glued to the lower skin.

[0008] The technical effects and advantages of the utility model: the product quality of the structure is good: in the part where the wing shape and the motor arm shape are combined, the shape is complex, the wing shape area is overlapped, and the motor arm shape area is butt-jointed to form, so as to avoid sinking of both areas and the fiber bridging defects that are easy to occur in the combined parts, thereby improving the quality of the product;

[0009] High degree of integration: The skin where the motor arm merges with the wing is designed as one piece. The upper and lower skins are integrated with the motor arm in a one-piece structure to achieve a structure in this area with a small number of parts and a high degree of integration.

[0010] Low cost: The fusion area of ​​the wing and the motor arm is integrally formed to avoid separate parts, reduce the number of molds and assembly work, and reduce costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 It is an axonometric drawing of the utility model;

[0012] Figure 2 It is an exploded view of the utility model;

[0013] Figure 3 It is an axonometric view of the front splicing piece of the utility model;

[0014] Figure 4 It is an axonometric view of the rear splicing part of the utility model;

[0015] Figure 5 It is a cross-sectional view of the leading edge of the wing skin structure of the utility model;

[0016] Figure 6 It is a cross-sectional view of the wing skin structure of the utility model at the position of the front splicing piece;

[0017] Figure 7 This is an axonometric view of the utility model in the position of an eVTOL aircraft.

[0018] In the figure, 1. wing skin structure; 11. upper skin; 111. overlap depression; 12. lower skin; 13. front splicing piece; 131. overlap edge; 14. rear splicing piece; 141. vertical edge; 2. eVTOL aircraft. DETAILED DESCRIPTION

[0019] In order to make the technical means for realizing the utility model, creative features, objectives and effects easy to understand, the utility model is further explained below in conjunction with specific diagrams. In the description of the utility model, 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.

[0020] Example

[0021] like Figure 7 As shown, it is an axonometric view of the wing skin structure 1 at the position of the eVTOL aircraft 2. The wing skin structure 1 serves as the outer surface part of the wing (left and right wings, this example only describes the left side, and the right and left sides are symmetrical parts). The wing shape and the motor arm shape are designed into a structure to maintain the aerodynamic shape of the wing, withstand the aerodynamic force on the wing, and withstand the load transmitted from the motor arm.

[0022] like Figure 1 and Figure 2 As shown, the wing skin structure 1 includes an upper skin 11, a lower skin 12, a front splicing piece 13, and a rear splicing piece 14. The lower skin 12 is connected to the upper skin 11 below, and the front splicing piece 13 and the rear splicing piece 14 are installed at the front and rear ends of the upper skin 11, the lower skin 12 and the motor arm shape area. In order to ensure the molding of the wing skin structure 1, it is necessary to divide the wing skin structure 1 into blocks. This example adopts an upper and lower block method, which is divided at the leading edge and the trailing edge. At the same time, the area fused with the motor arm is separated along the leading edge and the trailing edge seam line to ensure the feasibility of molding. The leading edge of the wing shape area adopts an overlapping connection method, that is, the upper skin 11 and the lower skin 12 have an overlapping area, which is bonded with structural adhesive. The motor arm shape area is butt-jointed, and the upper skin 11 and the lower skin 12 have a seam there, and the skins are not connected to each other, so the front splicing piece 13 and the rear splicing piece 14 are designed to connect the upper skin 11 and the lower skin 12. The upper skin 11 and the lower skin 12 are made of carbon fiber composite materials to reduce the weight of the structure and have strong molding ability. The motor arm area and the wing shape area are integrated into a one-piece structure.

[0023] like Figure 3As shown, the front splicing piece 13 splices the upper skin 11 and the lower skin 12 in the motor arm shape area. In order to improve the connection strength, a lap edge 131 is designed at one end of the front splicing piece 13 for connection at the corner position of the upper skin 11 and the lower skin 12, connecting the upper skin 11 and the lower skin 12 at the leading edge of the wing. The front splicing piece 13 is made of carbon fiber composite material and is bonded to the upper skin 11 and the lower skin 12 with structural adhesive.

[0024] like Figure 4 As shown, the function of the rear splicing piece 14 is similar to that of the front splicing piece 13. A vertical edge 141 is designed at one end of the rear splicing piece 14 to strengthen the corner area of ​​the rear edge area and improve the connection strength. Due to the shape limitation, the rear splicing piece 14 is machined from aluminum alloy, the preferred material is 7075, and the preferred heat treatment state is T7351. The rear splicing piece 14 is bonded to the upper skin 11 and the lower skin 12 using structural adhesive.

[0025] like Figure 5 As shown, at the leading edge of the wing, the upper skin 11 is designed with an overlapping depression 111 and is glued together with the lower skin 12 for connection. At the same time, if the lower skin 12 is depressed and the upper skin 11 is not depressed, the connection can also be achieved.

[0026] like Figure 6 As shown in the figure, the connection form of the front splicing piece 13 and the upper skin 11 and the lower skin 12 in the motor arm shape area is similar to the position connection form of the rear splicing piece 14. Due to the different force sizes, the upper skin 11 is thicker than the lower skin 12. In the splicing area, the lower skin 12 is locally thickened to keep the thickness consistent with the upper skin 11. In this way, the front splicing piece 13 and the rear splicing piece 14 do not need to be designed with a sunken design in the connection area, which ensures that the connection strength is improved while reducing the difficulty of process manufacturing and assembly.

[0027] 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 substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An eVTOL aircraft wing skin structure, comprising an upper skin, characterized in that: The lower skin is connected to the upper skin below, and the front and rear ends of the joints between the upper skin, the lower skin and the motor arm outer shape area are respectively connected with a front splicing piece and a rear splicing piece.

2. The eVTOL aircraft wing skin structure according to claim 1, characterized in that: An overlapping edge is provided at one end of the front splicing piece, and the overlapping edge is located at a corner of the upper skin and the lower skin.

3. The eVTOL aircraft wing skin structure according to claim 1, characterized in that: One end of the rear splicing piece is provided with a vertical edge.

4. The eVTOL aircraft wing skin structure according to claim 1, characterized in that: The upper skin is provided with an overlapping depression at the leading edge of the wing, and the overlapping depression is glued to the lower skin.

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