Multi-functional door for an aircraft

Abstract

The application discloses a multifunctional hatch for an aircraft, and relates to the technical field of spaceflight, comprising a main body part, a plurality of lifting point parts and a plurality of connecting parts, wherein the main body part comprises a hatch part and a hatch peripheral side area part surrounding the hatch part, the hatch part comprises an operation hatch and a wave-transparent hatch, and the wave-transparent hatch is embedded in the operation hatch; the plurality of lifting point parts are distributed around the main body part; the plurality of connecting parts are distributed around the main body part, and the hatch part is connected with the hatch peripheral side area part through the connecting parts. The multifunctional hatch for the aircraft integrates multiple functions of operation, wave transmission and lifting, and avoids the reduction of the overall structural rigidity of the aircraft caused by too many openings arranged on the cabin structure of the aircraft.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and in particular to a multi-functional cover for aircraft. Background Technology

[0002] Currently, aircraft cabin structures typically feature operating ports for personnel to operate and for installing instruments and equipment, with operating port covers installed on the outside of these ports. Simultaneously, to meet antenna wave transmission requirements, the cabin usually has wave-transmitting openings, with wave-transmitting port covers installed at these openings. During aircraft installation and transportation, lifting points are usually provided to facilitate hoisting, and plugs or other structures are installed at the openings of these lifting points. These covers and plugs are non-load-bearing structures, primarily used to realize the opening functions of the aircraft and maintain the aerodynamic shape of the cabin's outer surface.

[0003] In related technologies, the operating ports, wave-transparent ports, and lifting points on the aircraft cabin structure are located at different positions on the aircraft cabin. For aircraft with small diameter and high loading ratio, too many openings will affect the rigidity of the overall aircraft structure and make operation more complicated. Summary of the Invention

[0004] This application provides a multi-functional hatch for aircraft to solve the problem in related technologies where excessive openings on the aircraft cabin structure lead to a reduction in the overall structural rigidity of the aircraft.

[0005] This application provides a multi-functional hatch for aircraft, comprising:

[0006] The main body includes a cover portion and a cover periphery region portion surrounding the cover portion. The cover portion includes an operation cover and a wave-transmitting cover, and the wave-transmitting cover is embedded in the operation cover.

[0007] Multiple lifting points are distributed around the main body.

[0008] Multiple connectors are distributed around the main body, and the cover is connected to the periphery of the cover via the connectors.

[0009] In some embodiments, the wave-transmitting port cover is in the shape of a boss, and the operation port cover has a through hole in the middle that matches the size of the wave-transmitting port cover, and the wave-transmitting port cover is embedded in the through hole.

[0010] In some embodiments, the periphery of the cover has a frame-like structure, and a limiting plate extending toward the cover is provided around the bottom of the periphery of the cover.

[0011] In some embodiments, the lifting point component includes a lifting point steel sleeve and a lifting point heat-proof plug, which are embedded in the main body. The lifting point heat-proof plug is located on the top surface of the lifting point steel sleeve, and the top surface of the lifting point heat-proof plug is flush with the outer surface of the cap portion.

[0012] In some embodiments, the heat plug at the suspension point has two blind holes inside.

[0013] In some embodiments, the connector includes a special screw and a heat plug, which are embedded in the main body. The heat plug is located on the top surface of the special screw, and the top surface of the heat plug is flush with the outer surface of the cap.

[0014] In some embodiments, the main body further includes an antenna disposed inside the wave-transparent port cover.

[0015] In some embodiments, the antenna is in the shape of a boss, and a pressure plate is fitted around the antenna boss, the pressure plate being a frame structure with a hollow center.

[0016] In some embodiments, a first gasket is embedded between the wave-transparent port cover and the pressure plate.

[0017] In some embodiments, a second gasket is fitted around the periphery of the wave-transparent port cover boss.

[0018] The beneficial effects of the technical solution provided in this application include: the embodiments of this application provide a multi-functional cover for aircraft, in which a wave-transparent cover is embedded in an operation cover, which can realize that the operation cover for personnel operation and installation of instruments and equipment and the wave-transparent cover for antenna wave transmission are located on the same main cover, avoiding excessive openings from affecting the overall structural rigidity of the aircraft; the lifting point components are distributed around the main body for easy lifting, and the lifting point components can also cooperate with the connectors to realize the function of connecting and fixing the cover part and the surrounding area of ​​the cover. This application has multiple functions such as operation, wave transmission, and lifting. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 A schematic diagram of a multi-functional hatch for an aircraft provided in this application embodiment;

[0021] Figure 2 A schematic diagram of a multi-functional hatch for an aircraft provided in this application embodiment;

[0022] Figure 3 This is a schematic diagram of the mouth cover assembly provided in an embodiment of this application;

[0023] Figure 4 This is a general schematic diagram of the cover portion provided in an embodiment of this application;

[0024] Figure 5 This is a schematic diagram of the periphery of the lid provided in an embodiment of this application;

[0025] Figure 6 This is a schematic diagram of the wave-transparent port cover provided in an embodiment of this application;

[0026] Figure 7 This is a schematic diagram of the operating cover provided in an embodiment of this application;

[0027] Figure 8 This is a schematic diagram of an antenna provided in an embodiment of this application;

[0028] Figure 9 A schematic diagram of the pressure plate provided in an embodiment of this application;

[0029] Figure 10 A schematic diagram of a specially designed screw provided in an embodiment of this application;

[0030] Figure 11 A schematic diagram of a heat plug provided in an embodiment of this application;

[0031] Figure 12 This is a schematic diagram of the lifting point steel sleeve provided in an embodiment of this application;

[0032] Figure 13 This is a schematic diagram of the heat plug at the suspension point provided in an embodiment of this application;

[0033] Figure 14 A schematic diagram of the first gasket provided in an embodiment of this application;

[0034] Figure 15 This is a schematic diagram of the second gasket provided in an embodiment of this application.

[0035] In the diagram: 1. Main body; 2. Lifting point; 3. Connector; 4. First gasket; 5. Second gasket; 11. Cover; 12. Peripheral area of ​​cover; 13. Antenna; 14. Pressure plate; 21. Lifting point steel sleeve; 22. Lifting point heat plug; 31. Special screw; 32. Heat plug; 111. Operating cover; 112. Wave-transparent cover; 113. Through hole; 114. Limiting plate; 221. Blind hole. Detailed Implementation

[0036] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0037] This application provides a multi-functional hatch for aircraft, which can solve the problem in related technologies where too many openings on the aircraft cabin structure lead to a reduction in the overall structural rigidity of the aircraft.

[0038] See Figure 1 As shown, this application provides a multi-functional hatch for aircraft, including: a main body 1, multiple lifting points 2, and multiple connectors 3. The main body 1 includes a hatch portion 11 and a hatch peripheral area portion 12 surrounding the hatch portion 11. The hatch portion 11 includes an operation hatch 111 and a wave-transparent hatch 112, with the wave-transparent hatch 112 embedded within the operation hatch 111. See also... Figure 2 As shown, multiple lifting points 2 are distributed around the main body 1; multiple connectors 3 are also distributed around the main body 1, and the cover portion 11 is connected to the cover periphery area portion 12 via the connectors 3. Correspondingly, the cover portion 11 and the cover periphery area portion 12 are provided with mounting holes that match the dimensions of the lifting points 2 and the connectors 3. This application does not limit the specific dimensions or quantity of the lifting points 2 and the connectors 3.

[0039] Compared with the prior art, the multi-functional cover for aircraft in this application embodiment has a wave-transparent cover 112 embedded in the operation cover 111. This allows the operation cover, which is convenient for personnel to operate and for installing instruments and equipment, and the wave-transparent cover for antenna 13 to transmit waves, to be located on the same main cover. This avoids excessive openings from affecting the overall structural rigidity of the aircraft. The lifting points 2 are distributed around the main body 1 for easy lifting. The lifting points 2 can also work with the connectors 3 to connect and fix the cover 11 and the surrounding area 12 of the cover. This application has multiple functions, including operation, wave transmission, and lifting.

[0040] As an optional embodiment, see [link to example]. Figure 6 As shown, the wave-transmitting port cover 112 is in the shape of a boss, see [reference]. Figure 7 As shown, the operating port cover 111 has a through hole 113 in the middle that matches the size of the wave-transparent port cover 112. (See Figure 113) Figure 4 As shown, the wave-transparent cover 112 is embedded in the through hole 113, and the wave-transparent cover 112 is used for wave transmission of the antenna 13. This application does not limit the specific connection method between the wave-transparent cover 112 and the operation cover 111.

[0041] As an optional embodiment, see [link to example]. Figure 5 As shown, the periphery area 12 of the cover has a frame structure, and the bottom of the periphery area 12 of the cover has a limiting plate 114 extending towards the cover 11. The limiting plate 114 has a slightly larger mounting hole for installing the lifting point 2 and a slightly smaller mounting hole for installing the connecting piece 3. The limiting plate 114 as a whole limits the cover 11.

[0042] As an optional embodiment, see [link to example]. Figure 12 and Figure 13 As shown, the lifting point component 2 includes a lifting point steel sleeve 21 and a lifting point heat plug 22, see [reference]. Figure 2 As shown, the lifting point steel sleeve 21 and the lifting point heat plug 22 are embedded in the main body 1. The lifting point heat plug 22 is located on the top surface of the lifting point steel sleeve 21, and the top surface of the lifting point heat plug 22 is flush with the outer surface of the cap portion 11. In this embodiment, there is a certain gap between the top surface of the lifting point steel sleeve 21 and the lifting point heat plug 22. Both the lifting point steel sleeve 21 and the lifting point heat plug 22 are threadedly connected to the main body 1, making disassembly and assembly convenient. After removing the lifting point heat plug 22 and the lifting point steel sleeve 21, their exposed threaded holes can be used to install special lifting fixtures for aircraft lifting. Furthermore, the lifting point component 2 can cooperate with the connecting component 3 to further connect and fix the cap portion 11 and the cap peripheral area portion 12.

[0043] As an optional embodiment, see [link to example]. Figure 13 As shown, the heat plug 22 at the suspension point has two blind holes 221 inside, which can be used to easily remove the heat plug 22 at the suspension point.

[0044] As an optional embodiment, see [link to example]. Figure 10 and Figure 11 As shown, the connector 3 includes a special screw 31 and a heat plug 32. The special screw 31 and the heat plug 32 are embedded in the main body 1. The heat plug 32 is located on the top surface of the special screw 31, and the top surface of the heat plug 32 is flush with the outer surface of the cap 11. The top surface of the heat plug 32 is also provided with a blind hole, which makes it easy to disassemble and assemble.

[0045] As an optional embodiment, see [link to example]. Figure 3 As shown, the main body 1 also includes an antenna 13, which is located inside the wave-transmitting cover 112 to ensure the wave transmission of the antenna.

[0046] As an optional embodiment, see [link to example]. Figure 8 As shown, antenna 13 is in the shape of a boss, and pressure plates 14 are fitted around the boss of antenna 13. (See Figure 14.) Figure 9 As shown, the pressure plate 14 is a frame-shaped structure with a hollow center, used to protect the antenna 13 from damage; the pressure plate 14 has through holes and threaded holes, wherein the through holes are used to connect the pressure plate 14 to the operating port cover 111, and the threaded holes are used to install the antenna 13. This application does not limit the number of through holes and threaded holes.

[0047] As an optional embodiment, see [link to example]. Figure 14 As shown, a first gasket 4 is embedded between the wave-transmitting cover 112 and the pressure plate 14.

[0048] As an optional embodiment, see [link to example]. Figure 15 As shown, a second gasket 5 is fitted around the protrusion of the wave-transmitting cover 112. Both the first gasket 4 and the second gasket 5 are made of rubber and are used to prevent damage to the wave-transmitting cover 112.

[0049] After the aircraft structure is assembled, when the aircraft needs to be lifted, the lifting point steel sleeve 21 and the lifting point heat plug 22 can be removed first, and then the lifting fixture can be installed at the corresponding lifting point hole to lift the aircraft. When the instruments and equipment inside the aircraft need to be replaced, the special screws 31, heat plugs 32, lifting point steel sleeves 21, lifting point heat plugs 22 and the cover 11 can be removed, and the instruments and equipment can be replaced through the opening on the aircraft; the wave-transparent cover 112 can meet the wave-transmission requirements of the antenna 13.

[0050] In the description of this application, it should be noted that the terms "upper," "lower," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application. Unless otherwise expressly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication between two elements. For those skilled in the art, the specific meaning of the above terms in this application can be understood according to the specific circumstances.

[0051] It should be noted that in this application, relational terms such as "first" and "second" are used merely 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 a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0052] The above description is merely a specific embodiment of this application, enabling those skilled in the art to understand or implement this application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this application. Therefore, this application is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features claimed herein.

Claims

1. A multi-functional hatch for aircraft, characterized in that, It includes: The main body (1) includes a cover portion (11) and a cover periphery region portion (12) surrounding the cover portion (11). The cover portion (11) includes an operation cover (111) and a wave-transparent cover (112), and the wave-transparent cover (112) is embedded in the operation cover (111). Multiple lifting points (2) are distributed around the main body (1); Multiple connectors (3) are distributed around the main body (1), and the cover (11) is connected to the cover periphery area (12) through the connectors (3); The peripheral area of ​​the cover (12) is a frame structure, and the bottom of the peripheral area of ​​the cover (12) is provided with a limiting plate (114) extending toward the cover (11). The lifting point component (2) includes a lifting point steel sleeve (21) and a lifting point heat-proof plug (22). The lifting point steel sleeve (21) and the lifting point heat-proof plug (22) are embedded in the main body (1). The lifting point heat-proof plug (22) is located on the top surface of the lifting point steel sleeve (21), and the top surface of the lifting point heat-proof plug (22) is flush with the outer surface of the cap part (11). There is a certain gap between the top surface of the lifting point steel sleeve (21) and the lifting point heat plug (22). The lifting point steel sleeve (21) and the lifting point heat plug (22) are threadedly connected to the main body (1). After removing the lifting point heat plug (22) and the lifting point steel sleeve (21), the exposed threaded hole is used to install a special lifting tool for lifting the aircraft. The lifting point component (2) cooperates with the connecting component (3) to further connect and fix the mouth cover part (11) and the mouth cover peripheral area part (12).

2. The multi-functional hatch for aircraft as described in claim 1, characterized in that: The wave-transmitting port cover (112) is in the shape of a boss. The operation port cover (111) has a through hole (113) in the middle that matches the size of the wave-transmitting port cover (112). The wave-transmitting port cover (112) is embedded in the through hole (113).

3. The multi-functional hatch for aircraft as described in claim 1, characterized in that: The heat-resistant plug (22) at the suspension point has two blind holes (221) inside.

4. The multi-functional hatch for aircraft as described in claim 1, characterized in that: The connector (3) includes a special screw (31) and a heat plug (32). The special screw (31) and the heat plug (32) are embedded in the main body (1). The heat plug (32) is located on the top surface of the special screw (31), and the top surface of the heat plug (32) is flush with the outer surface of the cap (11).

5. A multi-functional aircraft cover as described in claim 1, characterized in that: The main body (1) also includes an antenna (13), which is located inside the wave-transparent port cover (112).

6. A multi-functional aircraft cover as described in claim 5, characterized in that: The antenna (13) is in the shape of a boss, and a pressure plate (14) is fitted around the boss of the antenna (13). The pressure plate (14) is a frame structure with a hollow center.

7. A multi-functional aircraft cover as described in claim 6, characterized in that: A first gasket (4) is embedded between the wave-transmitting cover (112) and the pressure plate (14).

8. A multi-functional aircraft cover as described in claim 1, characterized in that: The wave-transparent cover (112) has a second gasket (5) fitted around the protrusion.

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