An eVTOL aircraft charge port cover

Abstract

The utility model discloses an eVTOL aircraft charging port cover, including the charging port cover for eVTOL aircraft, the position of charging port cover is arranged in the lower part of eVTOL aircraft fuselage, and the position of charging port cover is located the position of being close to the battery pack of eVTOL aircraft rear cabin. The utility model discloses through with inner support and outer support in the middle part use fastener connection to form the three -dimensional structure, and inner support and fuselage inner skin, outer support and fuselage outer skin are fixedly connected respectively, make the space three -dimensional support of inner skin and outer skin to charging port cover, greatly promote overall structure rigidity, effectively reduce the structural deformation when plugging charging gun, guarantee charging gun and plug smoothly, reduce the damage risk of fuselage skin because of repeatedly deforming simultaneously, prolong the service life of charging port cover and fuselage related parts.

Description

Technical Field

[0001] This utility model relates to the technical field of eVTOL aircraft charging port covers, specifically an eVTOL aircraft charging port cover. Background Technology

[0002] eVTOL (Electric Vertical Takeoff and Landing) aircraft can take off and land vertically, eliminating the need for long runways and enabling takeoff and landing operations within limited spaces. This significantly improves the flexibility and accessibility of air transport, making them suitable for scenarios such as urban air mobility. Powered by electricity, they produce no pollutants such as carbon dioxide and nitrogen oxides during operation, meeting the zero-carbon vision and environmental requirements. They also significantly reduce noise, enhancing the passenger experience and comfort. The overall configuration allows for various innovative aerodynamic-propulsion integrated designs and unconventional aerodynamic layouts, including multi-rotor, compound, and vector propulsion types, to meet diverse travel needs. Their structure is relatively simple, maintenance requirements are low, and electricity costs are typically lower than fuel costs, suggesting the potential for lower operating costs after large-scale commercial operation.

[0003] eVTOL aircraft are powered by battery packs. When the battery packs are depleted, they need to be replenished promptly. Therefore, a charging port cover needs to be designed for the eVTOL aircraft to secure the charging plug. The charging port cover is opened during charging and closed after charging is complete. The design of the charging port cover must consider ease of use and speed, as well as service life and secure installation, ensuring reliable functionality even after tens of thousands of charging cycles throughout the eVTOL aircraft's lifespan.

[0004] Chinese utility model patent application number 202421265333.2 discloses "an eVTOL aircraft charging port installation structure," including a fuselage skin with a through hole. A support is provided at the through hole, and the support is connected to the fuselage skin. A charging port is installed on the support via a connector I. A cover is provided to cover the through hole, and the cover is connected to the support via the connector. This structure is lightweight: the charging port is located relatively close to the high-voltage control box of the entire aircraft, where the battery pack is installed, minimizing the length of the charging harness and reducing the length of the charging harness on the eVTOL aircraft, thereby reducing weight; it also has low aerodynamic drag: the cover is manufactured according to the shape of the eVTOL aircraft, maintaining a smooth surface and minimizing aerodynamic drag.

[0005] The Chinese utility model patent application number 202421265333.2, entitled "An eVTOL Aircraft Charging Port Installation Structure," uses a bracket, nut, and bolt connection to install the port cover onto the support. Each charging operation requires disassembling and reassembling multiple bolts and bracket nuts, which is time-consuming and inefficient to maintain. Furthermore, repeated disassembly and reassembly of the bolts and bracket nuts can easily damage the threads, resulting in a shorter service life. The support is connected to the fuselage skin; since the fuselage skin on one side is thinner and less rigid, the area where the support is connected to the skin can deform significantly when the charging plug is inserted or removed. After repeated use, this may damage the fuselage skin. Utility Model Content

[0006] To address the problems mentioned in the background art, the purpose of this utility model is to provide an eVTOL aircraft charging port cover, which has the advantages of short operation time, high rigidity, long service life, good sealing performance, and good safety. It solves the problems of the existing technology "An eVTOL aircraft charging port installation structure" (application number: 202421265333.2), which uses a plate nut and bolts to connect the cover and the support, resulting in the need to disassemble multiple bolts for each charging, long operation time, poor maintainability, and repeated disassembly is prone to thread damage and short service life. At the same time, the support only connects to the fuselage skin, and the skin on one side is thin and weak, which can easily cause deformation of the skin area when plugging and unplugging the charging gun, and long-term use may damage the fuselage skin.

[0007] To achieve the above objectives, the present invention provides the following technical solution: an eVTOL aircraft charging port cover, comprising a charging port cover applied to an eVTOL aircraft, wherein the charging port cover is located at the lower part of the eVTOL aircraft fuselage, and the charging port cover is located near the battery pack in the rear cabin of the eVTOL aircraft.

[0008] The charging port cover includes an inner support, an outer support, a hinge, a sealing strip, a cover body, a quick-release lock, and fasteners. The inner and outer supports are connected in the middle by fasteners to form a three-dimensional structure. The inner and outer supports are fixedly connected to the inner and outer skins of the eVTOL aircraft fuselage. The surface of the outer support is provided with a hinge connection area and a quick-release lock connection area. One end of the hinge is fixedly connected to the hinge connection area of ​​the outer support by fasteners, and the other end of the hinge is fixedly connected to the cover body. One end of the quick-release lock is fixed to the cover body by fasteners, and the other end of the quick-release lock is pressed against the quick-release lock connection area. The sealing strip is bonded to the overlapping area between the outer support and the cover body by structural adhesive.

[0009] As a preferred embodiment of this utility model, the surface of the inner support is provided with an inner and outer support connecting edge and an inner skin connecting edge. The surface of the inner and outer support connecting edge is provided with a hole for fasteners to pass through. The inner skin connecting edge is fixedly connected to the inner skin of the eVTOL aircraft by fasteners. The surface of the outer support is provided with an outer skin connecting edge, which is fixedly connected to the outer skin of the eVTOL aircraft by fasteners.

[0010] In a preferred embodiment of this invention, the hinge includes a hinge head, a hinge shaft, and a movable leaf. The hinge head includes a base and three ears, and the movable leaf includes a cap body connecting area and two ears. The base is fixedly connected to the hinge connecting area by fasteners, the cap body connecting area is fixedly connected to the cap body by fasteners, the two ears and three ears are connected in cooperation, and the hinge shaft passes through the shaft holes inside the two ears and three ears.

[0011] As a preferred embodiment of this utility model, the gap between the hinge shaft and the movable page and the hinge joint is 0.01-0.05mm. The hinge shaft is made of bolt, and the end of the bolt has a small hole. A cotter pin is fitted inside the small hole. The end of the cotter pin is fixedly connected to a slotted nut that mates with the end of the hinge shaft, so that the slotted nut and the cotter pin cooperate to achieve locking.

[0012] As a preferred embodiment of this utility model, the cover body is made of 6061 aluminum alloy and heat-treated to T6. The outer surface of the cover body is flush with the outer surface of the eVTOL aircraft. The inner and outer supports are both made of 7050 aluminum alloy and heat-treated to T7451. The movable leaf and hinge joint are both made of 7075 aluminum alloy and heat-treated to T7451.

[0013] As a preferred embodiment of this utility model, the fastener consists of bolts and nuts. The bolts include convex head bolts and countersunk head bolts. The countersunk head bolts are used for connection surfaces with pneumatic requirements on the outside, and the convex head bolts are used for internal connections within the machine body.

[0014] As a preferred embodiment of this utility model, the side wall of the outer support is provided with a cavity area, the hinge connection area is installed inside the cavity area, the hinge connection area and the hinge joint are fixedly connected by fasteners, and the range of the cavity area is larger than the envelope of the hinge movement, and the periphery of the opening of the quick-release lock connection area is provided with vertical ribs.

[0015] As a preferred embodiment of this utility model, the sealing strip is made of compressible high-temperature foam material with a compression capacity of up to 80%. The surface of the outer support has a charging plug connection edge, and the surface of the charging plug connection edge is provided with a large central hole for the charging plug to pass through and four peripheral connection holes for fixing the charging plug.

[0016] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0017] 1. This utility model forms a three-dimensional structure by connecting the inner support and the outer support in the middle with fasteners. The inner support is fixedly connected to the inner skin of the body, and the outer support is fixedly connected to the outer skin of the body. This allows the inner and outer skins to form a three-dimensional spatial support for the charging port cover, which greatly improves the overall structural rigidity, effectively reduces structural deformation when plugging and unplugging the charging gun, ensures the smoothness of plugging and unplugging the charging gun, and reduces the risk of damage to the body skin caused by repeated deformation, thus extending the service life of the charging port cover and related body components.

[0018] 2. This utility model features a quick-release lock, one end of which is fixed to the cover body with fasteners, and the other end is pressed into the quick-release lock connection area of ​​the outer support. Pressing the open or lock button of the quick-release lock unlocks or locks the cover body. Combined with the hinge, the cover body can be quickly opened and closed, significantly shortening the cover operation time during each charging, improving charging efficiency, and meeting the high-frequency charging needs of eVTOL aircraft. At the same time, a compressible high-temperature foam sealing strip with a compression of up to 80% is bonded to the overlapping area between the outer support and the cover body using structural adhesive. This effectively prevents rainwater from flowing into the charging cover, avoiding internal short circuits and the risk of electric shock to users, thus improving safety. Attached Figure Description

[0019] Figure 1 This is an isometric view of an eVTOL aircraft charging port cover installed on an eVTOL aircraft according to the present invention.

[0020] Figure 2 This is an isometric drawing of an eVTOL aircraft charging port cover according to this utility model;

[0021] Figure 3 This is an exploded view of an eVTOL aircraft charging port cover according to this utility model.

[0022] Figure 4 This is an external isometric view of the connection between the hinge and the outer support of this utility model.

[0023] Figure 5 An isometric view of the quick-release lock and the outer support of this utility model, showing the connection of the charging plug of the outer support hidden.

[0024] Figure 6 This is an axonometric drawing of the internal support of this utility model;

[0025] Figure 7 This is an axonometric view of the outer side of the outer support of this utility model;

[0026] Figure 8 This is an axonometric view of the inner side of the outer support of this utility model;

[0027] Figure 9 This is an isometric view of the hinge of this utility model;

[0028] Figure 10 This is an isometric view of the movable page of this utility model;

[0029] Figure 11 This is an isometric view of the hinge joint of this utility model.

[0030] In the diagram: 1. Charging port cover; 11. Inner support; 111. Connecting edge of inner and outer supports; 112. Connecting edge of inner skin; 12. Outer support; 121. Connecting edge of outer skin; 122. Hinge connecting area; 123. Connecting edge of charging plug; 124. Connecting area of ​​quick-release lock; 13. Hinge; 131. Hinge connector; 1311. Base; 1312. Three ears; 132. Hinge shaft; 133. Moving flap; 1331. Connecting area of ​​the cover body; 1332. Two ears; 14. Sealing strip; 15. Cover body; 16. Quick-release lock; 17. Fastener; 2. eVTOL aircraft. Detailed Implementation

[0031] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0032] like Figures 1 to 11 As shown, the present invention provides an eVTOL aircraft charging port cover, including a charging port cover 1 applied to an eVTOL aircraft 2. The charging port cover 1 is located at the lower part of the fuselage of the eVTOL aircraft 2, and the charging port cover 1 is located close to the battery pack in the rear cabin of the eVTOL aircraft 2.

[0033] The charging port cover 1 includes an inner support 11, an outer support 12, a hinge 13, a sealing strip 14, a cover body 15, a quick-release lock 16, and a fastener 17. The inner support 11 and the outer support 12 are connected in the middle by the fastener 17 to form a three-dimensional structure. The inner support 11 and the outer support 12 are fixedly connected to the inner and outer skins of the eVTOL aircraft 2 fuselage. The surface of the outer support 12 is provided with a hinge connection area 122 and a quick-release lock connection area 124. One end of the hinge 13 is connected to... The hinge connection area 122 of the outer support 12 is fixedly connected by fasteners 17. The other end of the hinge 13 is fixedly connected to the cover body 15. One end of the quick-release lock 16 is fixed to the cover body 15 by fasteners 17, and the other end of the quick-release lock 16 is pressed against the quick-release lock connection area 124. The sealing strip 14 is bonded to the overlapping area between the outer support 12 and the cover body 15 with structural adhesive. The sealing strip 14 is made of compressible high-temperature foam material, and the compression amount can reach 80%. The surface of the outer support 12 has a charging plug connection edge 123. The surface of the charging plug connection edge 123 has a large central hole for the charging plug to pass through and four peripheral connection holes for fixing the charging plug. The sealing strip is made of high-temperature foam material that can be compressed to 80%, which can fully fill the gap when the cover is closed, effectively preventing rainwater, dust and other impurities from entering the interior, avoiding short circuits or component corrosion. At the same time, its elasticity and resilience can adapt to slight deformation of the fuselage, maintain the sealing effect for a long time, and can withstand temperature changes during charging, ensuring reliable sealing in all scenarios. The "large central hole + four peripheral holes" design of the charging plug connection edge provides a passage for the charging plug to pass through, ensuring that the plug and the battery pack can be connected smoothly. The four peripheral holes fix the plug with fasteners to prevent the plug from loosening and shifting during aircraft operation. The symmetrical distribution of the four holes ensures that the plug is evenly stressed, reducing wear and tear during insertion and removal. At the same time, the standardized hole positions also simplify the installation and subsequent maintenance process of the plug.

[0034] refer to Figure 4 , Figure 6 , Figure 7 and Figure 8 The inner support 11 has an inner and outer support connecting edge 111 and an inner skin connecting edge 112 on its surface. The inner and outer support connecting edge 111 has a hole for the fastener 17 to pass through. The inner skin connecting edge 112 is fixedly connected to the inner skin of the eVTOL aircraft 2 by the fastener 17. The outer support 12 has an outer skin connecting edge 121 on its surface. The outer skin connecting edge 121 is fixedly connected to the outer skin of the eVTOL aircraft 2 by the fastener 17.

[0035] As a technical optimization of this utility model, the inner and outer support connecting edges 111 of the inner support 11 and the middle of the outer support 12 are connected by fasteners 17 to form a three-dimensional structure. At the same time, the inner support 11 is fixed to the inner skin and outer skin of the body by means of the inner skin connecting edge 112 and the outer support 12 by means of the outer skin connecting edge 121, respectively, by fasteners 17. This makes the inner skin and outer skin form a three-dimensional spatial support for the charging port cover 1, which greatly improves the overall structural rigidity, effectively reduces structural deformation when plugging and unplugging the charging gun, ensures the smoothness of plugging and unplugging the charging gun, and reduces the risk of damage to the body skin caused by repeated deformation, thus extending the service life of the charging port cover 1 and the body skin.

[0036] refer to Figure 3 , Figure 9 , Figure 10 and Figure 11 The hinge 13 includes a hinge head 131, a hinge shaft 132, and a movable flap 133. The hinge head 131 includes a base 1311 and three ears 1312. The movable flap 133 includes a cover body connecting area 1331 and two ears 1332. The base 1311 is fixedly connected to the hinge connecting area 122 by fasteners 17. The cover body connecting area 1331 is fixedly connected to the cover body 15 by fasteners 17. The two ears 1332 are engaged with the three ears 1312. The hinge shaft 132 passes through the shaft holes inside the double ears 1332 and the triple ears 1312. The gap between the hinge shaft 132 and the movable leaf 133 and the hinge connector 131 is 0.01-0.05mm. The hinge shaft 132 is made of bolt. The end of the bolt has a small hole. A cotter pin is fitted inside the small hole. The end of the cotter pin is fixedly connected to a slotted nut that mates with the end of the hinge shaft 132, so that the slotted nut and the cotter pin can lock together.

[0037] As a technical optimization of this utility model, the hinge 13 is designed as a combination structure of a hinge connector 131, a hinge shaft 132, and a movable leaf 133. The hinge connector 131 has three ears 1312, and the movable leaf 133 has two ears 1332. The two ears 1332 and the three ears 1312 cooperate to pass through the hinge shaft 132, forming a rotational structure where multiple ears work together to bear force. Simultaneously, the gap between the hinge shaft 132, the movable leaf 133, and the hinge connector 131 is controlled to be 0.01-0.05mm, and locking is achieved through the cooperation of a small hole at the end of the hinge shaft 132, a cotter pin, and a slotted nut. This optimization avoids the problem of easy damage to a single ear under force, improving the safety and service life of the hinge 13. It also reduces rotational play through precise gap control and prevents the hinge shaft 132 from disengaging through the locking structure, ensuring the reliable function of the hinge 13.

[0038] refer to Figure 9 and Figure 10The cover body 15 is made of 6061 aluminum alloy and is heat treated to T6. The outer surface of the cover body 15 is flush with the outer surface of the eVTOL aircraft 2. The inner support 11 and the outer support 12 are both made of 7050 aluminum alloy and are heat treated to T7451. The movable leaf 133 and the hinge joint 131 are both made of 7075 aluminum alloy and are heat treated to T7451.

[0039] As a technical optimization of this utility model, by selecting materials and heat treatment states according to the functional requirements of each component, the cover body 15 is made of 6061 aluminum alloy and heat-treated with T6. While ensuring sufficient strength to withstand the opening and closing and sealing pressure, it also takes into account the convenience of processing and lightweight. Moreover, its outer surface is flush with the outer surface of the eVTOL aircraft 2, which meets the aerodynamic performance requirements. The inner support 11 and the outer support 12 are made of 7050 aluminum alloy and heat-treated with T7451. The high strength and high corrosion resistance of this material ensure that the inner support 11 and the outer support 12, as the supporting structure, can withstand the force of plugging and unplugging the charging gun and the corrosion of the external environment for a long time. The movable page 133 and the hinge joint 131 are made of 7075 aluminum alloy and heat-treated with T7451. With the help of the high hardness and high wear resistance of this material, the wear resistance of the rotating parts of the hinge 13 is improved, and the service life of the hinge 13 is extended.

[0040] refer to Figure 3 Fastener 17 consists of bolts and nuts. The bolts include convex head bolts and countersunk head bolts. Countersunk head bolts are used for connection surfaces with pneumatic requirements on the outside, while convex head bolts are used for internal connections within the machine body.

[0041] As a technical optimization of this utility model, countersunk bolts and convex head bolts are used according to the functional requirements of the connection positions. Countersunk bolts are used on external connection surfaces with aerodynamic requirements, such as the connection surfaces between the cover body 15 and the hinge 13 and the quick-release lock 16, so that the bolt head does not protrude from the surface of the component, ensuring the smoothness of the outer surface of the eVTOL aircraft 2 and reducing aerodynamic drag. Conversely, convex head bolts are used on internal connection positions without aerodynamic requirements, such as the connection between the inner support 11 and the outer support 12, and the connection between the hinge joint 131 and the outer support 12. The convenient installation and stable connection strength of convex head bolts ensure the reliability of internal connections. This optimization scheme achieves a precise match between the function and usage scenario of the fastener 17, taking into account both aerodynamic performance and connection reliability.

[0042] refer to Figure 7 and Figure 8The outer support 12 has a cavity area on its side wall. The hinge connection area 122 is installed inside the cavity area. The hinge connection area 122 and the hinge joint 131 are fixedly connected by fasteners 17. The cavity area is larger than the envelope of the hinge 13 movement. The periphery of the opening of the quick-release lock connection area 124 is provided with vertical ribs. The vertical ribs can enhance the local rigidity of the quick-release lock connection area 124, prevent the area from deforming when the quick-release lock 16 is pressed, and thus ensure the compression of the sealing strip 14 by the cover body 15, and ensure the sealing effect.

[0043] As a technical optimization of this utility model, a cavity area larger than the motion envelope of the hinge 13 is opened in the side wall of the outer support 12, providing sufficient space for the hinge 13 to rotate, avoiding interference between the hinge 13 and the outer support 12 during movement, and ensuring smooth opening and closing of the cover body 15. Vertical ribs are provided around the opening of the quick-release lock connection area 124, enhancing the local rigidity of the quick-release lock connection area 124 and preventing deformation of this area when the quick-release lock 16 is pressed in. This optimization solution solves the interference problem between the hinge 13 and the outer support 12, ensuring the opening and closing function of the cover body 15; on the other hand, by enhancing the rigidity of the quick-release lock connection area 124, it ensures reliable pressing of the quick-release lock 16, while preventing insufficient compression of the sealing strip 14 by the cover body 15 due to deformation of this area, thus ensuring a good sealing effect.

[0044] The working principle and usage process of this utility model are as follows: When the eVTOL aircraft 2 needs to be charged, firstly, operate the quick-release lock 16 on the charging port cover 1, press the unlock button of the quick-release lock 16 to release the quick-release lock 16 from the press-fit state with the quick-release lock connection area 124 of the outer support 12, and complete the unlocking; then push the port cover body 15. Since the port cover body 15 is fixedly connected to the port cover body connection area 1331 of the movable page 133 of the hinge 13 through the fastener 17, the double ears 1332 of the movable page 133 cooperate with the triple ears 1312 of the hinge connector 131 and are connected through the hinge shaft 132, and the base 1311 of the hinge connector 131 is fixed to the hinge connection area 122 of the outer support 12 through the fastener 17, the port cover body 15 will rotate around the hinge shaft 132. At this time, the outer support 1 The cavity area opened on the side wall, which is larger than the motion envelope of the hinge 13, provides sufficient space for the rotation of the hinge 13 to avoid interference until the cover body 15 is fully opened, exposing the charging plug connected to the charging plug on the outer support 12 through the large central hole; then the charging gun is connected to the charging plug for charging. During the charging process, the inner support 11 is connected to the outer support 12 through the inner and outer support connecting edge 111 and the fastener 17 to form a three-dimensional structure. The inner skin connecting edge 112 of the inner support 11 is fixed to the inner skin of the eVTOL aircraft 2 through the fastener 17, and the outer skin connecting edge 121 of the outer support 12 is fixed to the outer skin of the eVTOL aircraft 2 through the fastener 17. The inner and outer skins together provide strong support for the charging cover 1, ensuring that the structure deforms little when the charging gun is plugged in or unplugged.

[0045] After charging is complete, first disconnect the charging gun from the charging plug, then push the cover body 15 in the opposite direction to rotate the cover body 15 around the hinge axis 132 again until the cover body 15 fits against the outer support 12. At this time, the cover body 15 compresses the sealing strip 14, which is bonded to the overlapping area between the outer support 12 and the cover body 15 by structural adhesive. The sealing strip 14 is made of compressible high-temperature foam material, with a compression of up to 80%, achieving a seal. Finally, press the locking button of the quick-release lock 16 to re-press the quick-release lock 16 against the quick-release lock connection area 124 of the outer support 12. Because the quick-release lock connection area 124 has vertical ribs around the opening, it has high rigidity and is not easily deformed during pressing, ensuring reliable locking. The entire usage process of the charging cover 1 is completed, including the fastening. In component 17, countersunk bolts are used for the connecting surfaces with aerodynamic requirements on the outside, and convex bolts are used for the internal connections of the fuselage. The hinge shaft 132 is bolted with a small hole at the end that is fitted with a cotter pin and a slotted nut to lock it in place and prevent it from coming off. The gap between the hinge shaft 132 and the movable leaf 133 and the hinge joint 131 is 0.01-0.05mm to reduce rotational play. The cover body 15 is made of 6061 aluminum alloy in T6 heat treatment condition and its outer surface is flush with the outer surface of the eVTOL aircraft 2. The inner support 11 and the outer support 12 are made of 7050 aluminum alloy in T7451 heat treatment condition. The movable leaf 133 and the hinge joint 131 are made of 7075 aluminum alloy in T7451 heat treatment condition. All components are fixed on the eVTOL aircraft 2, and there is no risk of parts being lost.

[0046] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0047] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A charging port cover for an eVTOL aircraft, comprising a charging port cover (1) for use in an eVTOL aircraft (2), characterized in that: The charging port cover (1) is located on the lower part of the fuselage of the eVTOL aircraft (2), and the charging port cover (1) is located near the battery pack in the rear cabin of the eVTOL aircraft (2). The charging port cover (1) includes an inner support (11), an outer support (12), a hinge (13), a sealing strip (14), a cover body (15), a quick-release lock (16), and a fastener (17). The inner support (11) and the outer support (12) are connected in the middle by the fastener (17) to form a three-dimensional structure. The inner support (11) and the outer support (12) are fixedly connected to the inner skin and outer skin of the fuselage of the eVTOL aircraft (2). The surface of the outer support (12) is provided with a hinge connection area (122) and a quick-release lock connection. In area (124), one end of the hinge (13) is fixedly connected to the hinge connection area (122) of the outer support (12) by fasteners (17), the other end of the hinge (13) is fixedly connected to the cap body (15), one end of the quick release lock (16) is fixed to the cap body (15) by fasteners (17), the other end of the quick release lock (16) is pressed into the quick release lock connection area (124), and the sealing strip (14) is bonded to the overlapping area between the outer support (12) and the cap body (15) by structural adhesive.

2. The eVTOL aircraft charging port cover according to claim 1, characterized in that: The inner support (11) has an inner and outer support connecting edge (111) and an inner skin connecting edge (112) on its surface. The inner and outer support connecting edge (111) has a hole for fasteners (17) to pass through. The inner skin connecting edge (112) is fixedly connected to the inner skin of the eVTOL aircraft (2) by fasteners (17). The outer support (12) has an outer skin connecting edge (121) on its surface. The outer skin connecting edge (121) is fixedly connected to the outer skin of the eVTOL aircraft (2) by fasteners (17).

3. The eVTOL aircraft charging port cover according to claim 2, characterized in that: The hinge (13) includes a hinge head (131), a hinge shaft (132), and a movable flap (133). The hinge head (131) includes a base (1311) and three ears (1312). The movable flap (133) includes a cap body connecting area (1331) and two ears (1332). The base (1311) is fixedly connected to the hinge connecting area (122) by fasteners (17). The cap body connecting area (1331) is fixedly connected to the cap body (15) by fasteners (17). The two ears (1332) and the three ears (1312) are connected in a mating manner. The hinge shaft (132) passes through the shaft hole inside the two ears (1332) and the three ears (1312).

4. The eVTOL aircraft charging port cover according to claim 3, characterized in that: The gap between the hinge shaft (132), the movable page (133), and the hinge connector (131) is 0.01-0.05mm. The hinge shaft (132) is made of bolt, and a small hole is provided at the end of the bolt. A cotter pin is fitted inside the small hole. A slotted nut that mates with the end of the cotter pin is fixedly connected to the end of the hinge shaft (132), so that the slotted nut and the cotter pin can lock together.

5. The eVTOL aircraft charging port cover according to claim 4, characterized in that: The cover body (15) is made of 6061 aluminum alloy and is heat-treated to T6. The outer surface of the cover body (15) is flush with the outer surface of the eVTOL aircraft (2). The inner support (11) and the outer support (12) are both made of 7050 aluminum alloy and are heat-treated to T7451. The movable leaf (133) and the hinge joint (131) are both made of 7075 aluminum alloy and are heat-treated to T7451.

6. The eVTOL aircraft charging port cover according to claim 5, characterized in that: The fastener (17) consists of bolts and nuts. The bolts include convex head bolts and countersunk head bolts. The countersunk head bolts are used for connection surfaces with pneumatic requirements on the outside, and the convex head bolts are used for internal connections within the machine body.

7. The eVTOL aircraft charging port cover according to claim 6, characterized in that: The side wall of the outer support (12) is provided with a cavity area. The hinge connection area (122) is installed inside the cavity area. The hinge connection area (122) and the hinge joint (131) are fixedly connected by fasteners (17). The range of the cavity area is larger than the envelope of the hinge (13) movement. The periphery of the opening of the quick-release lock connection area (124) is provided with vertical ribs.

8. The eVTOL aircraft charging port cover according to claim 7, characterized in that: The sealing strip (14) is made of compressible high-temperature foam material, with a compression capacity of up to 80%. The surface of the outer support (12) has a charging plug connection edge (123). The surface of the charging plug connection edge (123) is provided with a large central hole for the charging plug to pass through and four peripheral connection holes for fixing the charging plug.

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