EVTOL airplane charging port mounting structure

Abstract

The utility model discloses an eVTOL airplane charging port installation structure which comprises an airplane body skin, a through hole is formed in the airplane body skin, a support is arranged at the position of the through hole, the support is connected to the airplane body skin, a charging port is installed on the support through a connecting piece I, a port cover covers the position of the through hole, and the port cover is connected with the support through a connecting piece. The structure is light in weight, the charging port is arranged at the position close to the high-voltage disc box of the whole machine, the battery pack is installed in the high-voltage disc box, the length of a charging wire harness is saved as much as possible, the length of the charging wire harness on an eVTOL airplane is reduced, and then the weight is reduced; the appearance of the covering cap is manufactured according to the appearance of the eVTOL aircraft, the surface of the eVTOL aircraft is kept smooth, and the aerodynamic resistance is small.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation equipment, and in particular to an eVTOL aircraft charging port installation 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, the government, the military and academia. The potential future applications of eVTOL involve a variety of scenarios such as urban passenger transport, regional passenger transport, freight, personal aircraft, and emergency medical services. The American Vertical Flight Association believes that eVTOL technology is one of the most important technological changes in the aviation industry since the birth of the helicopter 75 years ago, and may be more revolutionary than the emergence of turbine engines. According to the "World Electric Vertical Takeoff and Landing (eVTOL) Aircraft Directory" published online by the association, there are currently more than 260 projects engaged in eVTOL development around the world. The use of electric propulsion systems instead of internal combustion engine power has gained 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, low noise and vibration levels, good ride comfort, and a truly environmentally friendly aircraft. In addition, it also has the characteristics of safety and reliability, 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, and both optimal layout and unconventional / innovative layout can be adopted; aircraft with extraordinary performance can be designed to meet special purpose requirements, etc.

[0003] The eVTOL aircraft uses electricity as its energy source. When the internal battery pack runs out of power, the battery pack needs to be charged, and a charging port needs to be arranged and installed to charge the battery pack. Many existing charging ports are far away from the battery pack installation location, which increases the length of the charging harness and the weight of the entire aircraft. In addition, the charging ports of many aircraft do not conform to the surface of the aircraft, and are in a convex or concave state, which increases the aerodynamic resistance of the aircraft. Utility Model Content

[0004] The purpose of the utility model is to provide an eVTOL aircraft charging port installation 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 charging port installation structure, including a fuselage skin, a through hole is opened on the fuselage skin, a support is provided at the through hole, the support is connected to the fuselage skin, a charging port is installed on the support through a connecting member I, the through hole is covered with a cover, and the cover is connected to the support through a connecting member.

[0005] Preferably, the support is a box-shaped structure with a groove inside, one side of the groove is an open structure, and a through hole is opened at the bottom, one end of the charging port passes through the through hole, and the other end is located inside the groove, a flange edge is provided at the opening of the support, a cover connecting hole is opened on the flange edge, and a charging port connecting hole is opened at the bottom of the groove, and the charging port connecting hole is located around the through hole.

[0006] Preferably, the opening cover covers the through hole and is consistent with the shape of the fuselage.

[0007] Preferably, the connecting members are support plate nuts and bolts.

[0008] Preferably, the connecting member I is a bolt and a nut.

[0009] The technical effects and advantages of the utility model are as follows: the structure is light in weight: the charging port is arranged at a position relatively close to the high-voltage disk box of the whole machine, and a battery pack is installed inside the high-voltage disk box, so as to save the length of the charging harness as much as possible, reduce the length of the charging harness on the eVTOL aircraft, and thus reduce the weight;

[0010] Human-machine friendly: The charging port is installed at a height suitable for human operation, 1.2 meters in this example, to facilitate charging;

[0011] Secure installation: The charging port and the support are connected by multiple bolts and nuts, which ensures secure installation.

[0012] Small aerodynamic drag: The shape of the cover is manufactured according to the shape of the eVTOL aircraft, keeping the surface of the eVTOL aircraft smooth and the aerodynamic drag small. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is an axonometric view of the present invention from the outside perspective;

[0014] Figure 2 An axonometric view of the interior perspective of the present invention;

[0015] Figure 3 It is an exploded view of the utility model;

[0016] Figure 4 It is an axonometric drawing of the support of the utility model;

[0017] Figure 5 It is a cross-sectional view of the utility model at the connection piece I;

[0018] Figure 6 This is an axonometric view of the utility model in the position of an eVTOL aircraft.

[0019] In the figure, 1. Charging port installation structure; 11. Fuselage skin; 12. Cover; 13. Connector; 14. Charging port; 15. Support; 151. Cover connection hole; 152. Flange edge; 153. Through hole; 154. Charging port connection hole; 155. Groove; 16. Connector I; 161. Bolt; 162. Nut; 17. Structural adhesive; 18. Through hole; 2. eVTOL aircraft. DETAILED DESCRIPTION

[0020] 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.

[0021] Example

[0022] like Figure 6 As shown, the charging port mounting structure 1 is arranged at the rear of the fuselage of the eVTOL aircraft 2, close to the battery pack, so that the wiring harness between the charging port assembly and the battery pack is as short as possible, saving the weight of the wiring harness; at the same time, the height of the charging port mounting structure 1 from the ground is arranged at a position that is more suitable for personnel operation, so as to facilitate charging operations by ground personnel. In this example, the height of the charging port mounting structure from the ground is 1.2 meters.

[0023] like Figure 1 , 2, 3, the charging port installation structure includes a fuselage skin 11, a cover 12, a connector 13, a charging port 14, a support 15, a connector I 16, and a structural adhesive 17. A through hole 18 is opened on the fuselage skin 11, and a support 15 is provided at the through hole 18. The support 15 is connected to the fuselage skin 11, and the charging port 14 is installed on the support 15 through the connector I 16. The through hole 18 is covered with a cover 12, and the cover 12 is connected to the support 15 through the connector 13; the fuselage skin 11 is eV The TOL aircraft fuselage is a dimensional part. This figure only shows the local area of ​​the fuselage skin 11 near the charging port 14. The fuselage skin 11 provides support for the support 15. When the charging gun is plugged in or unplugged, the fuselage skin 11 is subjected to the plug-in load. At the same time, the fuselage skin 11 is also subjected to the aerodynamic load during flight. A larger out-of-plane stiffness is required in the area connected to the support 15, and local reinforcement is required. The fuselage skin 11 adopts a carbon fiber composite material structure with a foam core, which is lightweight and provides higher strength and stiffness.

[0024] The cover 12 provides a charging path. After removing the cover 12, the charging port 14 is exposed for charging. The cover 12 also maintains the shape of the eVTOL aircraft fuselage, effectively reducing aerodynamic resistance during flight. The cover 12 needs to be removed and installed once for each charging, so the cover 12 should be easy to disassemble. Therefore, the cover 12 is connected to the support 15 using a connector 13. The connector 13 includes a support plate nut and a bolt. The support plate nut is installed on the support, and the bolt is connected to the support plate nut through a hole on the cover 12. In order to keep the surface of the cover flat, a countersunk bolt is used. The cover 12 can be disassembled and installed by operating the bolt on one side only, which is more convenient.

[0025] The charging port 14 provides a charging interface for the battery pack, and cooperates with an external charging gun to complete the charging of the battery pack. The charging port 14 is a standard charging port product that meets relevant national standards.

[0026] The support 15 provides installation for the charging port 14 and is installed on the fuselage skin 11. The support 15 is a box-shaped structure that meets the rigidity and strength requirements for the installation of the charging port. The support in this example is machined from aluminum alloy, the preferred material is 7075, and the preferred heat treatment state is T7351.

[0027] The connector I 16 mounts the charging port 14 onto the support 15 to ensure that the charging port 14 is securely connected.

[0028] The structural adhesive 17 bonds the support 15 to the fuselage skin 11 to ensure that the support 15 will not fall off from the fuselage skin 11 under various stress conditions, thereby ensuring the reliability of the connection.

[0029] like Figure 4As shown, a groove 155 is provided inside the support 15. One side of the groove 155 is an open structure, and a through hole 153 is provided at the bottom. One end of the charging port 14 passes through the through hole 153, and the other end is located inside the groove 155. A flange 152 is provided at the opening of the support 15. The flange 152 is square, and a cover connection hole 151 is provided on the flange 152. A charging port connection hole 154 is provided at the bottom of the groove 155. The charging port connection hole 154 is located around the through hole 153. The cover connection hole 151 designed on the flange 152 is used in conjunction with the connector 13 to fix the cover 12, ensuring that the cover 12 is detachable; the structural glue 17 is applied to the overlapped part of the flange 152 and the fuselage skin 11, and connected to the fuselage skin 11, so that the support 15 and the fuselage skin 11 are fixed together. The through hole 153 allows the charging port 14 to pass through, so that the charging port 14 extends into the fuselage through the support 15 and connects with the charging harness inside the fuselage. The charging port connection hole 154 corresponds to the mounting point on the charging port 14, and is connected by a connector I 16 to mount the charging port 14 on the support 15. The groove 155 provides an escape space so that the spatial dimension of the charging port 14 does not exceed the fuselage shape, thereby maintaining the smoothness of the fuselage shape of the eVTOL aircraft.

[0030] like Figure 5 As shown, the edge of the cover 12 is aligned with the edge of the fuselage skin 11 to ensure the smoothness of the aerodynamic shape. A portion of the flange edge 152 of the support 15 corresponding to the cover 12 does not have the structural adhesive 17, and is a detachable structure. The position corresponding to the fuselage skin 11 is connected with the structural adhesive 17. The connection between the charging port 14 and the support 15 is a structure that is not frequently disassembled. Therefore, the connecting piece I16 is composed of bolts and nuts, and the bolts and nuts are connected by threads. The nuts are self-locking nuts to prevent the charging port 14 from loosening under flight conditions such as vibration, thereby ensuring the reliability of the connection.

[0031] 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 charging port mounting structure, comprising a fuselage skin, characterized in that: A through hole is opened on the fuselage skin, and a support is provided at the through hole. The support is connected to the fuselage skin, and a charging port is installed on the support via a connector I. The through hole is covered with a cover, and the cover is connected to the support via a connector. The charging port is arranged at a position close to the high-voltage disk box of the whole machine, and a battery pack is installed inside the high-voltage disk box.

2. The eVTOL aircraft charging port installation structure according to claim 1, characterized in that: The support is a box-shaped structure with a groove inside. One side of the groove is an open structure with a through hole at the bottom. One end of the charging port passes through the through hole and the other end is located inside the groove. A flange edge is provided at the opening of the support, and a cover connecting hole is provided on the flange edge. A charging port connecting hole is provided at the bottom of the groove, and the charging port connecting hole is located around the through hole.

3. The eVTOL aircraft charging port installation structure according to claim 1, characterized in that: The opening cover covers the through hole and is consistent with the shape of the fuselage.

4. The eVTOL aircraft charging port installation structure according to claim 1, characterized in that: The connecting parts are support plate nuts and bolts.

5. The eVTOL aircraft charging port installation structure according to claim 1, characterized in that: The connecting member I is a bolt and a nut.

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