Cabin door structure of eVTOL aircraft and eVTOL aircraft

Abstract

The utility model discloses a cabin door structure of an eVTOL aircraft, and relates to the field of aircrafts. The cabin door structure comprises a cabin door body, a cabin door lock is installed below the cabin door body, the cabin door lock comprises a lock body and a lock seat which are locked with each other, the lock seat is embedded in the fuselage, the lock body is fixedly connected with the cabin door body, and the lock body is connected with a handle on the cabin door body through a push-pull wire; a hinge assembly is fixed to the upper edge of a cabin door body and comprises a hinge embedded part, hinge bases and a hinge, the hinge embedded part is fixed in the cabin door body, the two hinge bases are fixed to the corresponding positions of a machine body, the hinge is rotationally connected between the two hinge bases, and the hinge is connected with the hinge embedded part through a bolt; a telescopic supporting rod structure is installed on the side face of the cabin door body, and the two ends of the supporting rod structure are connected with the cabin door body and a fuselage. The designed cabin door structure can enable the cabin door to be in a locking state with the fuselage when the cabin door is in a closed state, effectively reduces open seams of the hinged door, and is simple in structure and low in airtight requirement.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft, especially eVTOL aircraft's cabin door structure and eVTOL aircraft. BACKGROUND

[0002] In the field of aerospace, the design of aircraft cabin doors is of great importance. When traditional cabin doors are closed, there are often large gaps at the door joints due to poor sealing design or structural stress changes. This not only destroys the integrity of the overall appearance, but also seriously affects the sealing performance of the cabin, leading to a decline in air-tightness, thermal insulation, and sound insulation performance, which cannot meet the strict requirements of aircraft flying at high altitudes. To overcome these challenges, engineers must use advanced materials and precise manufacturing techniques to ensure that the cabin door maintains good sealing performance under various extreme conditions. In addition, the design of the cabin door also needs to consider the limitations of weight and space, as every additional weight may affect the performance and fuel efficiency of the aircraft. Therefore, designing a cabin door that is both lightweight and safe and reliable is a challenging task for aerospace engineers. SUMMARY

[0003] To solve the above technical problems, the utility model provides a kind of cabin door structure of eVTOL aircraft, make to open cabin door gap deformation meet the use requirement. Specifically as follows: the utility model provides a kind of cabin door structure of eVTOL aircraft, comprising: cabin door body (1), install cabin door lock (11) below cabin door body (1), cabin door lock (11) includes the lock body (111) and lock seat (112) that can be locked each other, lock seat (112) is embedded in the interior of fuselage, lock body (111) is fixedly connected with cabin door body (1), lock body (111) is connected with the push-pull line embedded in the interior of cabin door body (1), the other end of push-pull line is connected with handle installed on cabin door body (1);Hinge assembly (12) is fixedly installed on the upper edge of cabin door body (1), hinge assembly (12) includes hinge embedded part (121), hinge seat (122) and hinge (123), hinge embedded part (121) is fixed in cabin door body, two hinge seats (122) are fixed on the position corresponding to hinge embedded part (121) on the fuselage, hinge (123) is rotatably connected between two hinge seats (122), hinge (123) is connected with hinge embedded part (121) by bolt;The telescopic strut structure (13) is installed on the side of cabin door body (1), and the telescopic strut structure (13) is connected with the fuselage and the cabin door body (1) at both ends respectively.

[0004] The cabin door structure of the eVTOL aircraft as described above, wherein one cabin door lock (11) is installed on each side below the cabin door body (1), and the two cabin door locks (11) are connected to the handle through the push-pull line.

[0005] The cabin door structure of the eVTOL aircraft as described above, wherein an inner pull handle (113) is installed inside the cabin door body (1), and the inner pull handle (113) is connected to the cabin door lock (11) through an inner pull cable; an outer pull handle is installed outside the cabin door body (1), and the outer pull handle is connected to the cabin door lock (11) through an outer pull cable.

[0006] The cabin door structure of the eVTOL aircraft as described above, wherein the lock body (111) is fixedly connected to the cabin door skin through screw connection; and the hinge seat (122) is fixedly connected to the fuselage through rivets.

[0007] The cabin door structure of the eVTOL aircraft as described above, wherein a hinge shaft bushing is arranged at the connection position of the hinge (123) and the two hinge seats (122).

[0008] The cabin door structure of the eVTOL aircraft as described above, wherein the strut structure (13) comprises a strut seat (131), a strut mounting seat (132) and a strut (133), the strut seat (131) is connected to the cabin door skin and a strut embedded part inside the cabin door body (1) through bolts, the strut seat (131) is rotationally connected to one end of the strut (133), so that the strut (133) can rotate around the connection position when being stretched, the strut (133) is a telescopic link, the other end of the strut (133) is connected to the strut mounting seat (132), and the strut mounting seat (132) is connected to a strut support seat embedded in the fuselage through bolts.

[0009] The cabin door structure of the eVTOL aircraft as described above, wherein the cabin door body (1) comprises an upper frame body and a lower frame body, the upper frame body is used for installing door frame glass, and the lower frame body adopts a honeycomb sandwich structure.

[0010] The cabin door structure of the eVTOL aircraft as described above, wherein an inner handle (14) is installed below the lower frame body of the cabin door body (1).

[0011] The application also provides an eVTOL aircraft, wherein the eVTOL aircraft is provided with the cabin door structure as described above.

[0012] The beneficial effects realized by the utility model are as follows: the cabin door structure of the utility model adopts an innovative design concept, the telescopic connecting rod and the honeycomb sandwich structure are introduced, the structural strength and stability of the cabin door are improved, and the deformation caused by temperature change or mechanical stress is effectively reduced. In addition, the upper frame body and the lower frame body of the cabin door body are designed to ensure that the door gap is tightly fitted, thereby improving the sealing performance of the cabin body and meeting the air tightness, heat insulation and sound insulation requirements of the aircraft in the high-altitude environment. This design not only ensures the safety of the aircraft, but also improves the comfort of passengers, and lays a solid foundation for the wide application of the eVTOL aircraft; the specific embodiments are as follows:

[0013] (1) The utility model can make the cabin door present a locked state with the fuselage in the closed state, make the cabin door fit the fuselage more tightly, effectively reduce the gap of the open door, and the structure is simple and the air tightness requirement is low.

[0014] (2) The shaft of the hinge is close to the upper edge of the split cabin door, which can make the hinge seat and the hinge embedded part bear smaller load during the opening and closing of the cabin door and effectively improve the service life of the hinge.

[0015] (3) The cabin door adopts a honeycomb sandwich structure, which effectively reduces the weight of the cabin door under the premise of meeting the requirements of stiffness, strength, fatigue and reliability of the cabin door. BRIEF DESCRIPTION OF DRAWINGS

[0016] In order to more clearly illustrate the technical scheme in the embodiments of the utility model or the prior art, the drawings needed in the embodiment or the prior art description will be briefly introduced below, and obviously, the drawings in the following description are only some embodiments described in the utility model, and other drawings can be obtained by those skilled in the art according to these drawings.

[0017] Figure 1 A front view of the cabin door structure of the eVTOL aircraft provided by the utility model embodiment is provided.

[0018] Figure 2 A lateral view of the cabin door structure of the eVTOL aircraft is provided.

[0019] Figure 3 A strut structure diagram of the cabin door structure of the eVTOL aircraft is provided.

[0020] REFERENCE NUMERALS:

[0021] 1, cabin door body; 11, cabin door lock; 111, lock body; 112, lock seat; 113, inner opening handle; 12, hinge assembly; 121, hinge embedded part; 122, hinge seat; 123, hinge; 13, strut structure; 131, strut seat; 132, strut mounting seat; 133, strut; 14, inner handle. DETAILED DESCRIPTION

[0022] The following is a clear and complete description of the technical solutions in the embodiments of the present invention, in conjunction with the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0023] Example

[0024] like Figure 1 As shown, the present invention provides a door structure of an eVTOL aircraft, including a door body 1, a door lock 11 installed below the door body 1, the door lock 11 including a lock body 111 and a lock seat 112 that can be locked with each other, the lock seat 112 is pre-buried inside the fuselage, the lock body 111 is fixedly connected to the door body 1, the lock body 111 is connected to a push-pull wire pre-buried inside the door body 1, and the other end of the push-pull wire is connected to a handle installed on the door body 1; a hinge is fixedly installed on the upper edge of the door body 1 Chain assembly 12, the hinge assembly 12 includes a hinge embedded part 121, a hinge seat 122 and a hinge 123. The hinge embedded part 121 is fixed in the cabin door body, and two hinge seats 122 are fixed on the fuselage at positions corresponding to the hinge embedded part 121. The two hinge seats 122 are rotatably connected to the hinge 123, and the hinge 123 is connected to the hinge embedded part 121 by bolts; a retractable strut structure 13 is installed on the side of the cabin door body 1, and the two ends of the strut structure 13 are respectively connected to the cabin door body 1 and the fuselage.

[0025] Specifically, the door body 1 comprises an upper frame and a lower frame. The upper frame is used to mount the door frame glass, while the lower frame utilizes a honeycomb sandwich structure. A honeycomb sandwich structure is a laminated composite material consisting of a lightweight core material sandwiched between aircraft skins. This structural design primarily serves to further reduce the overall weight of the door while maintaining structural stability and strength. Furthermore, the door body 1 is constructed of carbon fiber, a lightweight and high-strength material suitable for use in aviation. By reducing the door's weight and increasing its strength, the lateral loads it experiences during flight can be significantly reduced.

[0026] A door lock 11 is installed on both sides of the lower part of the lower frame of the door body 1. The lock body 111 of the door lock 11 is fixedly connected to the door skin by screws. The lock seat 112 of the door lock 11 is pre-buried inside the fuselage. The lock body 111 and the lock seat 112 correspond to each other in position. When the door is closed, the lock body 111 and the lock seat 112 can lock each other, thereby ensuring the safety of the door.

[0027] The lock body 111 is connected to one end of an inner push-pull wire, which is pre-buried inside the door body 1. The other end of the inner push-pull wire is connected to an inner opening handle 113. When the inner opening handle 113 is pulled, the lock body 111 is driven to separate from the lock seat 112 via the inner push-pull wire, thereby unlocking the door. This allows personnel inside the cabin to easily open the door, improving the convenience of operation. The lock body 111 is also connected to one end of an outer push-pull wire, which is also pre-buried inside the door body 1. The other end of the outer push-pull wire is connected to an outer opening handle on the outside of the door body 1. When the outer opening handle is pulled, the lock body 111 is driven to separate from the lock seat 112 via the outer push-pull wire, thereby unlocking the door. This allows personnel outside the cabin to easily open the door, improving the convenience of operation.

[0028] Hinge assemblies 12 are installed at both ends of the upper frame of the door body 1. Hinge embedded parts 121 are embedded within the upper edge of the door body 1's upper frame and secured to the door skin with bolts. The position of hinge seats 122 corresponds to that of embedded hinge parts 121. Hinge seats 122 are fixed to the fuselage via rivets. Two hinge seats 122 are provided, and hinge 123 is bolted between them. Hinge 123 is also bolted to hinge embedded parts 121, ensuring its stability and durability. When the door is opened, embedded hinge parts 121 move, driving hinge 123 to open and close smoothly around its axis.

[0029] Preferably, a hinge shaft bushing is provided at the connection position between the hinge 123 and the hinge seat 122 to ensure smooth rotation and reduce wear.

[0030] An inner handle 14 is installed below the lower frame of the door body 1 to facilitate the operator to pull down and close the door when the door is open.

[0031] See also Figure 2 and Figure 3 A strut structure 13 is installed on the right side of the door body 1. The strut structure 13 comprises a strut base 131, a strut mounting base 132, and a strut 133. The strut base 131 is bolted to the door skin and a strut embedded in the door body 1 (not shown). The strut base 131 is rotatably connected to one end of the strut 133, allowing the strut 133 to rotate about its connection point when stretched. The strut 133 is a telescopic connecting rod. The other end of the strut 133 is connected to the strut mounting base 132, which is bolted to a strut support base embedded in the fuselage. The angle between the door and the fuselage is related to the tension of the strut 133. When the door is closed, the strut 133 is in a retracted state. When the door is opened, the strut 133 automatically extends to a stretched state, providing the necessary support for the door and ensuring its stability and safety when opened and closed.

[0032] The utility model discloses a working principle:

[0033] When the internal staff opens the hatch, pull the inner opening pull handle 113, and the inner opening pull handle 113 is connected with the inner pull line, drives the lock body 111 of the hatch lock 11 and the lock seat 112 to separate, realizes the purpose of unlocking, the supporting rod 133 starts to stretch, the hatch and the fuselage are separated at the both ends of the supporting rod 133, the supporting rod 133 continues to stretch, and the hinge 123 is driven around the hinge 123 axis of the hinge embedded part 121 on the upper portion of the hatch body 1 to rotate, thereby realizing the opening of the hatch.

[0034] When closing the hatch, the staff pulls the inner handle 14 at the bottom of the hatch body 1 downward, makes the supporting rod 133 start to shrink, and the hinge 123 is driven around the hinge 123 axis of the hinge embedded part 121 on the upper portion of the hatch body 1 to reverse rotate, realizes the closing of the hatch, and the hatch body 1 and the fuselage are closed.

[0035] The application also provides an eVTOL aircraft, which is provided with the hatch structure as described above.

[0036] For those skilled in the art, it is obvious that the utility model is not limited to the details of the above-mentioned exemplary embodiments, and the utility model can be realized in other specific forms without departing from the spirit or basic characteristics of the utility model. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting, and the scope of the utility model is defined by the appended claims rather than the above description, and therefore all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the utility model. Any reference signs in the claims should not be regarded as limiting the claims involved.

[0037] In the description of the utility model, unless otherwise specified, the meaning of "multiple" is two or more than two; the orientation or positional relationship indicated by the terms "upper", "lower", "left", "right", "inner", "outer", "front end", "rear end", "head", "tail" and the like is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the utility model and simplifying the description, and is not indicative or implied that the indicated device or element must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the utility model. In addition, the terms "first", "second", "third" and the like are only for the purpose of description, and cannot be understood as indicative or implied relative importance.

[0038] In the description of the utility model, it is necessary to explain, unless another explicit provision and limitation, term "link", "connection" should do broad sense understanding, for example, can be fixed connection, also can be detachable connection, or integrally connected;Can be mechanical connection, also can be electrical connection;Can be directly connected, also can be indirectly connected through intermediate medium. For ordinary skilled person in the art, the specific meaning of the above terms in the utility model can be understood according to specific circumstances.

Claims

1. A door structure for an eVTOL aircraft, characterized in that: include: A door body (1) is provided, wherein a door lock (11) is installed below the door body (1), wherein the door lock (11) comprises a lock body (111) and a lock seat (112) which can be locked with each other, wherein the lock seat (112) is pre-buried inside the fuselage, wherein the lock body (111) is fixedly connected to the door body (1), wherein the lock body (111) is connected to a push-pull wire pre-buried inside the door body (1), wherein the other end of the push-pull wire is connected to a handle installed on the door body (1); wherein a hinge assembly (12) is fixedly installed on the upper edge of the door body (1), wherein the hinge assembly (12) comprises a plurality of hinges. The invention comprises a hinge embedded part (121), a hinge seat (122) and a hinge (123), wherein the hinge embedded part (121) is fixed in the cabin door body, two hinge seats (122) are fixed at positions corresponding to the hinge embedded part (121) on the fuselage, the two hinge seats (122) are rotatably connected to the hinge (123), and the hinge (123) is connected to the hinge embedded part (121) by bolts; and a retractable strut structure (13) is installed on the side of the cabin door body (1), and the two ends of the strut structure (13) are respectively connected to the cabin door body (1) and the fuselage.

2. The door structure of an eVTOL aircraft according to claim 1, wherein: A door lock (11) is respectively installed on both sides of the lower side of the door body (1), and both door locks (11) are connected to the handle via a push-pull line.

3. The door structure of an eVTOL aircraft according to claim 2, characterized in that: An inner opening handle (113) is installed inside the door body (1), and the inner opening handle (113) is connected to the door lock (11) through an inner push-pull wire; an outer opening handle is installed outside the door body (1), and the outer opening handle is connected to the door lock (11) through an outer push-pull wire.

4. The door structure of an eVTOL aircraft according to claim 1, wherein: The lock body (111) is fixedly connected to the door skin by means of screw connection; and the hinge seat (122) is fixedly connected to the fuselage by means of rivets.

5. The door structure of an eVTOL aircraft according to claim 1, wherein: The connection positions of the hinge (123) and the two hinge seats (122) are all provided with hinge shaft bushings.

6. The door structure of an eVTOL aircraft according to claim 1, wherein: The strut structure (13) comprises a strut seat (131), a strut mounting seat (132) and a strut (133). The strut seat (131) is connected to the door skin and the strut embedded part inside the door body (1) through bolts. The strut seat (131) is rotatably connected to one end of the strut (133), so that the strut (133) can rotate around the connection position when stretched. The strut (133) is a telescopic connecting rod. The other end of the strut (133) is connected to the strut mounting seat (132). The strut mounting seat (132) is connected to the strut support seat embedded in the fuselage through bolts.

7. The door structure of an eVTOL aircraft according to claim 1, wherein: The door body (1) comprises an upper frame and a lower frame, the upper frame is used for installing door frame glass, and the lower frame adopts a honeycomb sandwich structure.

8. The door structure of an eVTOL aircraft according to claim 7, characterized in that: An inner handle (14) is installed below the lower frame of the door body (1).

9. An eVTOL aircraft, characterized in that: The eVTOL aircraft is provided with a door structure as described in any one of claims 1 to 8.

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