An eVTOL aircraft cabin door hinge

Abstract

The utility model discloses a kind of eVTOL aircraft cabin door hinges, including hinge, cabin door and machine body, the both ends of the hinge are respectively installed on the surface of cabin door and machine body, the quantity of the hinge is set to two groups, and two groups of hinges are respectively arranged in cabin door opening position up and down, the axis of two groups The hinge is located on the same straight line.The utility model is designed by whole forming limiting platform on fixed page, when cabin door is opened to design angle, limiting platform and movable page plane contact, can effectively limit cabin door opening angle, prevent cabin door over opening, avoid cabin door damage due to over opening, guarantee cabin door structural integrity, solve the problem that hinge lacks effective over opening protection in the similar technology of existing.

Description

Technical Field

[0001] This utility model relates to the field of eVTOL aircraft cabin door hinge technology, specifically an eVTOL aircraft cabin door hinge. 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] The hinges for eVTOL aircraft cabin doors need to meet the requirements for opening the cabin doors, ensuring smooth opening, meeting the rigidity requirements of the cabin doors, and preventing the cabin doors from sagging. At the same time, eVTOL aircraft use multiple power systems, and the vibration of the propellers when they rotate is relatively large. Therefore, under large vibration environments, it is necessary to maintain the stability of the cabin doors and prevent them from being shaken open due to insufficient rigidity.

[0004] Chinese utility model patent application number 202222828780.1 discloses "an eVTOL aircraft cabin door," comprising a door body connected to the fuselage via a support member, and a sealing strip connected to the inner perimeter of the door body. The door body includes a door structure with a transparent glass panel installed in the center. The support member includes a strut and a hinge; one end of the hinge is connected to the door structure, and the other end is connected to the fuselage. One end of the strut is connected to the fuselage, and the other end is connected to the hinge. This cabin door features a large area of ​​glass, providing passengers with a wider field of vision and improving passenger comfort. It also boasts high safety and an aesthetically pleasing structure: the support structure is located at the top of the door, hidden inside the fuselage, preventing it from hitting passengers' heads during boarding and remaining concealed, contributing to its aesthetic appeal.

[0005] The Chinese utility model patent application number 202222828780.1, entitled "An eVTOL aircraft cabin door", uses a hinge with a small size and insufficient rigidity. When subjected to the weight of the cabin door itself, it is easy to deform, and the deformation is large when under load. Under the strong vibration of the eVTOL aircraft, the cabin door can easily be shaken open, affecting the safety of passengers. 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 cabin door hinge that has the advantages of preventing the cabin door from opening too much, having an aesthetically pleasing appearance, high rigidity, and good anti-detachment effect. It solves the problems of existing similar technologies (such as Chinese utility model patent application number 202222828780.1, "An eVTOL Aircraft Cabin Door"), where the hinge size is too small, resulting in insufficient rigidity, easy deformation under the weight of the cabin door itself, large deformation under load, and easy for the cabin door to be shaken open in the strong vibration environment of eVTOL aircraft, affecting passenger safety. At the same time, it is difficult to accurately adjust the assembly gap and surface difference between the cabin door and the fuselage, and there is a lack of effective over-opening protection.

[0007] To achieve the above objectives, this utility model provides the following technical solution: an eVTOL aircraft cabin door hinge, comprising a hinge, a cabin door, and a fuselage, wherein the two ends of the hinge are respectively installed on the surfaces of the cabin door and the fuselage, and the number of the hinges is set to two sets, with the two sets of hinges arranged vertically at the cabin door opening position, and the axes of the two sets of hinges being located on the same straight line.

[0008] The hinge includes a movable leaf, a fixed leaf, a shaft support joint, a shaft, and multiple adjusting plates. The movable leaf is detachably connected to the hatch by bolts and nuts. The fixed leaf is fixedly connected to the body. The shaft support joint inserts the shaft and connects it to the movable leaf. The movable leaf and the shaft support joint can rotate around the shaft. The shaft support joint is fixedly connected to the fixed leaf. The shaft is the common rotation axis of the movable leaf and the shaft support joint.

[0009] The fixed page is provided with an integrally formed limiting platform, the movable page is provided with a hatch connecting edge, a bushing and a clearance groove, and one end of the shaft support joint is a blind hole.

[0010] In a preferred embodiment of this utility model, the two hinges are spaced a considerable distance apart vertically, the perimeter of the hatch is a frame with a crossbeam for reinforcement in the middle, the outer panel of the hatch is a single piece of glass, the body is composed of a window frame, inner skin, outer skin, and frame around the hatch, the hinges are embedded inside the body and only extend out to connect with the hatch, and the hinges are fixed to the frame of the hatch.

[0011] As a preferred embodiment of this utility model, the shaft support joint, the shaft, and the movable page are all made of stainless steel, with the stainless steel material being 15-5PH and the heat treatment state being H900. The fixed page is made of aluminum alloy, with the aluminum alloy material being 7050 and the heat treatment state being T7451.

[0012] As a preferred embodiment of this utility model, the limiting platform is a square protrusion, and the upper surface of the limiting platform is a small plane. The fixing page has a groove for connecting the shaft support joint, and the fixing page is connected to the machine body in multiple places around its perimeter.

[0013] As a preferred embodiment of this utility model, the door connecting edge is fitted to the door frame and is fixedly connected to the door in both directions. The bushing is fitted onto the shaft with a gap of 0.01-0.02mm. There are two bushings, which cooperate with the shaft support joint to form a three-ear and two-ear fit. The clearance groove is used to avoid the door frame of the aircraft body.

[0014] In a preferred embodiment of this invention, the shaft support joint is fixed inside the fixed page, the fixed page limits the shaft, a gap is provided between the shaft sleeve and the fixed page, an adjustment piece is provided between the shaft support joint and the movable page, and an adjustment piece is provided between the movable page and the hatch.

[0015] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0016] 1. This utility model designs an integrally formed limiting platform on the fixed page. When the hatch is opened to the designed angle, the limiting platform contacts the plane of the movable page, which can effectively limit the opening angle of the hatch, prevent the hatch from being over-opened, avoid damage to the hatch due to over-opening, and ensure the structural integrity of the hatch. This solves the problem of the lack of effective over-opening protection for hinges in existing similar technologies.

[0017] 2. This utility model provides double protection by setting one end of the shaft support joint as a blind hole, and after the shaft support joint is fixed to the fixed page, the fixed page limits the shaft, preventing the shaft from coming out of the movable page and the shaft support joint. At the same time, it sets two hinges with a long distance between them, and the clearance between the movable page bushing and the shaft is small (0.01-0.02mm). It also adopts a three-ear and two-ear mating structure, which greatly improves the hinge stiffness and prevents the door from deforming or opening due to its own weight or strong vibration of the aircraft. This solves the problems of insufficient hinge stiffness, poor anti-derailment effect, and easy impact on safety in vibration environment in existing similar technologies.

[0018] 3. This utility model, by setting adjustment plates between the shaft support joint and the movable leaf, and between the movable leaf and the hatch, can realize the position adjustment of the hatch in three directions: up and down, left and right, and front and back. It can compensate for the assembly gap and surface difference deviation between the hatch and the body caused by manufacturing tolerances, ensuring that the hatch and the body surface are flat and the gap is uniform, taking into account both sealing and aesthetics. At the same time, the hinge is embedded in the body and only partially protrudes, further improving the appearance. It solves the problems of difficulty in accurately adjusting the assembly precision of the hatch and poor appearance in existing similar technologies. Attached Figure Description

[0019] Figure 1 This is an isometric view of an eVTOL aircraft cabin door hinge installed in the fuselage structure according to the present invention.

[0020] Figure 2 This is an exploded view of an eVTOL aircraft cabin door hinge installed in the fuselage structure according to the present invention.

[0021] Figure 3 This is an isometric view of the hinge and body of this utility model.

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

[0023] Figure 5 This is an isometric view of the hinge of this utility model;

[0024] Figure 6 This is an exploded view of the hinge of this utility model;

[0025] Figure 7 This is an isometric view of the fixed page of this utility model;

[0026] Figure 8 This is an isometric view of the movable page of this utility model;

[0027] Figure 9 This is a cross-sectional view of the hinge axis position of this utility model;

[0028] Figure 10 This is a cross-sectional view of the connection between the hinge and the hatch of this utility model.

[0029] In the diagram: 1. Hinge; 11. Movable flap; 111. Door connecting edge; 112. Bushing; 113. Clearance groove; 12. Fixed flap; 121. Limiting platform; 13. Shaft support joint; 14. Shaft; 15. Adjusting plate; 2. Door; 3. Airframe. Detailed Implementation

[0030] 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.

[0031] like Figures 1 to 10 As shown, the present invention provides an eVTOL aircraft door hinge, including a hinge 1, a door 2 and a body 3. The two ends of the hinge 1 are respectively installed on the surfaces of the door 2 and the body 3. The number of hinges 1 is set to two sets, and the two sets of hinges 1 are respectively arranged vertically at the opening position of the door 2. The axes of the two sets of hinges 1 are located on the same straight line.

[0032] Hinge 1 includes a movable leaf 11, a fixed leaf 12, a shaft support joint 13, a shaft 14, and multiple adjusting plates 15. The movable leaf 11 is detachably connected to the hatch 2 by bolts and nuts. When maintenance is required, only the bolts and nuts need to be loosened. The fixed leaf 12 is fixedly connected to the body 3, providing reinforced support and minimizing overall deformation of hinge 1 to ensure the accuracy of hatch 2 after installation. The shaft support joint 13 first inserts the shaft 14 into it and then fixes it to the movable leaf 11, allowing the movable leaf 11 to rotate around the shaft 14 relative to the shaft support joint 13. Finally, the shaft support joint 13 is fixedly connected to the fixed leaf 12 to achieve the overall assembly of hinge 1. The shaft 14 is the common rotation axis of the movable leaf 11 and the shaft support joint 13, which in turn allows hatch 2 to rotate through shaft 14, realizing the opening and closing of hatch 2.

[0033] The fixed page 12 is provided with an integrally formed limiting platform 121, and the movable page 11 is provided with a hatch connecting edge 111, a bushing 112, and a clearance groove 113. When the hatch 2 is opened to the designed angle, the movable page 11 contacts the limiting platform 121, preventing the movable page 11 from continuing to move outward, thus limiting the hatch 2 and preventing the hatch 2 from opening too wide. One end of the shaft support joint 13 is a blind hole, so the shaft 14 will not come out from the blind hole side. After the shaft support joint 13 is fixed on the fixed page 12 and the fixed page 12 is fixed on the body 3, the fixed page 12 limits the shaft 14, preventing the shaft 14 from coming out and ensuring that the shaft 14 is always between the shaft support joint 13 and the movable page 11.

[0034] refer to Figure 2 , Figure 3 and Figure 4 The two hinges 1 are far apart vertically. The perimeter of the hatch 2 is a frame, and the middle is reinforced by a crossbeam. The outer panel of the hatch 2 is a single piece of glass. The fuselage 3 is composed of a window frame, inner skin, outer skin, and frame around the hatch 2. The hinges 1 are embedded inside the fuselage 3, and only a part of the structure protrudes to connect with the hatch 2. The hinges 1 are fixed to the frame of the hatch 2.

[0035] As a technical optimization of this utility model, by arranging two sets of hinges 1 with a relatively long vertical distance between them, and embedding the hinges 1 inside the fuselage 3 with only a portion of the structure extending out to connect with the hatch 2, and fixing the hinges 1 to the frame of the hatch 2, combined with the reinforced structure of the hatch 2's perimeter frame and central crossbeam, the strong support structure of the fuselage 3's perimeter window frame, inner skin, outer skin, and frame, the weight of the hatch 2 itself can be balanced by the bending moment formed by the tension and pressure between the two hinges 1. The long vertical distance between the two hinges allows the weight of the hatch 2 itself to be balanced by the bending moment formed by the tension and pressure between the two hinges 1. Due to the long distance, the tension of the upper hinge 1 and the pressure of the lower hinge 1 are correspondingly reduced, thereby reducing structural deformation, improving the fitting accuracy between the hatch 2 and the fuselage 3, concealing most of the hinge 1 structure, improving visual aesthetics, and strengthening the rigidity of the hinge 1 connection point to prevent the hatch 2 from deforming under stress.

[0036] refer to Figure 6 The shaft support joint 13, shaft 14 and movable page 11 are all made of stainless steel, with the stainless steel material being 15-5PH and the heat treatment state being H900. The fixed page 12 is made of aluminum alloy, with the aluminum alloy material being 7050 and the heat treatment state being T7451. Since the fixed page 12 does not need to move, the use of aluminum alloy can effectively reduce the structural weight.

[0037] As a technical optimization of this utility model, by using 15-5PH stainless steel for the shaft support joint 13, shaft 14 and moving leaf 11 and heat-treating them with H900, these components have high strength and good wear resistance, meeting the mechanical performance and wear resistance requirements of the moving parts of hinge 1; at the same time, by using 7050 aluminum alloy for the fixed leaf 12 and heat-treating it with T7451, the overall structural weight of hinge 1 is effectively reduced while ensuring the support rigidity of the fixed leaf 12, thus adapting to the lightweight requirements of eVTOL aircraft.

[0038] refer to Figure 6 and Figure 7 The limiting platform 121 is a square protrusion, and the upper surface of the limiting platform 121 is a small plane. The fixing page 12 has a groove for the shaft support connector 13 to connect. The fixing page 12 is connected to the machine body 3 in multiple places around its perimeter.

[0039] As a technical optimization of this utility model, by setting the limiting platform 121 as an integrally formed square protrusion on the fixed page 12 with a small flat surface on the upper surface, when the hatch 2 is opened to the designed angle, the movable page 11 and the limiting platform 121 form a planar contact, increasing the contact area to reduce pressure and extend the service life of the limiting platform 121; at the same time, a groove for connecting the shaft support joint 13 is opened on the fixed page 12, and the fixed page 12 is connected to the body 3 in multiple places around it, which not only achieves stable assembly of the shaft support joint 13, but also improves the rigidity of the fixed page 12 itself and prevents its deformation from affecting the installation accuracy of the hatch 2.

[0040] refer to Figure 4 , Figure 5 , Figure 6 and Figure 8 The hatch connecting edge 111 fits against the frame of the hatch 2 and is fixedly connected to the hatch 2 in both directions. The bushing 112 fits onto the shaft 14 and the gap between the bushing and the shaft 14 is 0.01-0.02mm. There are two bushings 112, which together with the shaft support joint 13 form a three-ear and a double-ear fit. The clearance groove 113 is used to avoid the door frame of the fuselage 3.

[0041] As a technical optimization of this utility model, by making the door connecting edge 111 fit snugly with the door 2 frame and fix it in two directions, the reliability of the connection between the movable page 11 and the door 2 is improved; by fitting two bushings 112 onto the shaft 14 and controlling the gap to 0.01-0.02mm, and by making the bushings 112 and the shaft support joint 13 form a three-ear and two-ear fit, the amount of shaking is reduced and the fit rigidity is improved while ensuring that the movable page 11 rotates smoothly around the shaft 14, and the deformation under stress is reduced; by setting the clearance groove 113, interference between the movable page 11 and the door frame of the body 3 is avoided when it moves around the shaft 14, ensuring that the two always maintain a safe movement gap.

[0042] refer to Figure 6 , Figure 9 and Figure 10 The shaft support joint 13 is fixed inside the fixed page 12. The fixed page 12 limits the shaft 14. There is a gap between the bushing 112 and the fixed page 12. The adjusting piece 15 between the shaft support joint 13 and the movable page 11 is used to adjust the vertical direction of the hatch 2. The adjusting piece 15 between the movable page 11 and the hatch 2 is used to adjust the horizontal and vertical directions of the hatch 2. When installing the hatch 2, the vertical direction of the hatch 2 can be adjusted by adjusting the thickness and number of adjusting pieces 15.

[0043] As a technical optimization of this utility model, by fixing the shaft support joint 13 inside the fixed page 12, the fixed page 12 forms a limit on the shaft 14. With the blind hole structure at one end of the shaft support joint 13, the shaft 14 is protected against detachment, preventing the shaft 14 from coming out of the movable page 11 and the shaft support joint 13. By leaving a gap between the bushing 112 and the fixed page 12, it is ensured that there is no interference when the movable page 11 rotates. At the same time, the vertical direction of the hatch 2 is adjusted by the adjusting piece 15 between the shaft support joint 13 and the movable page 11, and the horizontal and forward and backward directions of the hatch 2 are adjusted by the adjusting piece 15 between the movable page 11 and the hatch 2. This achieves precise adjustment of the hatch 2 in three directions, ensuring that the gap and surface tolerance between the hatch 2 and the body 3 meet the requirements.

[0044] The working principle and usage process of this utility model are as follows: First, when assembling the hinge, the fixed leaf 12 in the hinge 1 is installed to the corresponding position in the body 3 using fasteners. The body 3 is composed of a window frame, inner skin, outer skin, and skeleton around the hatch 2, which can provide stable support for the fixed leaf 12. Next, the shaft 14 is inserted into the bushing 112 and shaft support joint 13 of the movable leaf 11 of the hinge 1. One end of the shaft support joint 13 is a blind hole to prevent the shaft 14 from coming out from the blind hole side. At this time, according to the design requirements, the corresponding number and thickness of adjustment pieces 15 are installed between the shaft support joint 13 and the movable leaf 11. At the same time, corresponding adjustment pieces 15 are also installed between the hatch connecting edge 111 of the movable leaf 11 and the hatch 2. The hatch 2 is surrounded by a frame and reinforced by a crossbeam in the middle. The hatch connecting edge 111 of the movable leaf 11 is attached to the frame of the hatch 2 and detachably connected in two directions by bolts and nuts. Then, the shaft support is secured with fasteners. The connector 13 is fixed to the fixed page 12. The fixed page 12 has a groove for the shaft support connector 13 to connect. After the fixed page 12 is fixed, it further limits the shaft 14 to prevent the shaft 14 from coming out. At the same time, there is a gap between the bushing 112 of the movable page 11 and the fixed page 12 to avoid interference between the movable page 11 and the fixed page 12 when it rotates. The assembly of the hinge 1 with the hatch 2 and the fuselage 3 is now complete. The two sets of hinges 1 are arranged vertically at the opening of the hatch 2, with their axes on the same straight line. After the assembly is completed, the gap and surface difference between the hatch 2 and the fuselage 3 are measured. If the requirements are not met, the deviation values ​​in three directions are calculated. The vertical direction of the hatch 2 is adjusted by adjusting the thickness and number of the adjusting pieces 15 between the shaft support connector 13 and the movable page 11. The horizontal and forward and backward directions of the hatch 2 are adjusted by adjusting the thickness and number of the adjusting pieces 15 between the movable page 11 and the hatch 2. After reinstallation, the measurement is repeated until the gap and surface difference are qualified.

[0045] When using hatch 2 in daily use, push hatch 2, and hatch 2 will cause the movable leaf 11 to rotate around shaft 14. The clearance groove 113 on the movable leaf 11 avoids the door frame of the body 3, ensuring that the movable leaf 11 and the door frame of the body 3 always have a safe movement clearance. The clearance between the bushing 112 and shaft 14 is 0.01-0.02mm, and there are two bushings 112, which cooperate with the shaft support joint 13 to form a three-ear and two-ear fit, ensuring that the movable leaf 11 rotates smoothly without large shaking. When hatch 2 is opened to the design angle, the movable leaf 11 contacts the small plane of the integrally formed square protruding limiting platform 121 on the fixed leaf 12. The limiting platform 121 prevents the movable leaf 11 from continuing to move outward, preventing hatch 2 from opening too wide. When it is necessary to repair hinge 1 or hatch 2, unscrew the bolts and nuts connecting the movable leaf 11 and hatch 2 to separate the movable leaf 11 from hatch 2 for subsequent maintenance operations. After the maintenance is completed, reinstall according to the assembly process.

[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. An eVTOL aircraft cabin door hinge, comprising a hinge (1), a cabin door (2), and a fuselage (3), characterized in that: The two ends of the hinge (1) are respectively installed on the surface of the hatch (2) and the fuselage (3). The number of the hinge (1) is set to two sets, and the two sets of hinges (1) are arranged vertically at the opening position of the hatch (2). The axes of the two sets of hinges (1) are on the same straight line. The hinge (1) includes a movable leaf (11), a fixed leaf (12), a shaft support joint (13), a shaft (14), and multiple adjusting plates (15). The movable leaf (11) is detachably connected to the hatch (2) by bolts and nuts. The fixed leaf (12) is fixedly connected to the body (3). The shaft support joint (13) inserts the shaft (14) into it and connects it to the movable leaf (11). The movable leaf (11) and the shaft support joint (13) can rotate around the shaft (14). The shaft support joint (13) is fixedly connected to the fixed leaf (12). The shaft (14) is the common rotation axis of the movable leaf (11) and the shaft support joint (13). The fixed page (12) is provided with an integrally formed limiting platform (121), the movable page (11) is provided with a hatch connecting edge (111), a bushing (112) and a clearance groove (113), and one end of the shaft support joint (13) is a blind hole.

2. The eVTOL aircraft door hinge according to claim 1, characterized in that: The two hinges (1) are far apart vertically. The perimeter of the hatch (2) is a frame, and the middle is reinforced by a crossbeam. The outer panel of the hatch (2) is a single piece of glass. The body (3) around the hatch (2) consists of a window frame, inner skin, outer skin, and frame. The hinges (1) are embedded inside the body (3), and only a part of the structure protrudes to connect with the hatch (2). The hinges (1) are fixed to the frame of the hatch (2).

3. The eVTOL aircraft door hinge according to claim 1, characterized in that: The shaft support joint (13), shaft (14) and movable page (11) are all made of stainless steel, with the stainless steel material being 15-5PH and the heat treatment state being H900. The fixed page (12) is made of aluminum alloy, with the aluminum alloy material being 7050 and the heat treatment state being T7451.

4. The eVTOL aircraft door hinge according to claim 1, characterized in that: The limiting platform (121) is a square protrusion, and the upper surface of the limiting platform (121) is a small plane. The fixing page (12) has a groove for connecting the shaft support connector (13). The fixing page (12) is connected to the machine body (3) in multiple places around its perimeter.

5. The eVTOL aircraft door hinge according to claim 1, characterized in that: The door connecting edge (111) fits against the frame of the door (2) and is fixedly connected to the door (2) in both directions. The bushing (112) fits onto the shaft (14) and the gap between the bushing (14) and the shaft (14) is 0.01-0.02mm. There are two bushings (112) and they form a three-ear and two-ear fit with the shaft support joint (13). The clearance groove (113) is used to avoid the door frame of the body (3).

6. The eVTOL aircraft door hinge according to claim 1, characterized in that: The shaft support joint (13) is fixed inside the fixed page (12), the fixed page (12) limits the shaft (14), a gap is provided between the bushing (112) and the fixed page (12), the adjusting piece (15) between the shaft support joint (13) and the movable page (11) is used to adjust the vertical direction of the hatch (2), and the adjusting piece (15) between the movable page (11) and the hatch (2) is used to adjust the horizontal and vertical direction of the hatch (2).

Images