Sealing and support structure and aircraft comprising the same

Abstract

A seal and support structure for a joint between a first component and a second component at a non-zero angle to each other, the seal and support structure comprising a seal, a first member and a second member, wherein the first member presses a first side of the seal against the first component and the second member presses a second side of the seal, opposite the first side, against the second component, wherein the seal, the first member and the second member are each connected to the first component and the second component by a releasable connection and the first member and the second member each support the first component and the second component. The seal assembly of the invention can further comprise at least one stiffener to provide locally stiffened rigidity at the joint between the first component and the second component. Furthermore, the invention proposes an aircraft comprising such a seal and support structure.

Description

Technical Field

[0001] This invention relates to the technical field of civil aircraft. Specifically, it relates to a sealing and support structure at the connection between two components that are at an angle to each other in the fuselage structure of a civil aircraft. This invention also proposes a civil aircraft. Background Technology

[0002] In the structure of civil aircraft, there are situations where components form non-zero angles that need to be sealed. Typically, the structure used to seal these angles also needs to withstand load transfer between components and accommodate coordinated deformation.

[0003] For example, the sealing structure at the connection between the fuselage airtight floor assembly and the airtight end frame assembly located at the rear of the main landing nacelle needs to provide structural support for both the airtight floor assembly and the airtight end frame assembly, and also serve a sealing function. Furthermore, a similar connection structure is required at the connection between the airtight floor assembly at the front of the main landing nacelle and the center wing rear spars frame assembly.

[0004] In current civil aircraft fuselage structural designs, angle metal structures, such as "L"-shaped profiles, are often used at such component connections to achieve support and sealing. However, due to the need to withstand forced displacement caused by the deformation of adjacent components, this support and sealing structure area is prone to fatigue.

[0005] To address the issue of profile fatigue, some aircraft models currently ensure safety by increasing the number of airworthiness restriction items for inspection and maintenance. Additionally, some models employ a single-piece, machined floor longitudinal beam in the rear of the main takeoff and landing bay to significantly increase the rigidity of the deformation-coordinated areas and address the aforementioned localized fatigue problems caused by deformation. However, both solutions significantly increase aircraft maintenance and operating costs. Furthermore, in existing technologies, the connection between such support and sealing structures and the two components is often fixed using rivets. Such connections are not removable. Therefore, when profiles in the connecting structure need to be replaced due to localized fatigue, the connection is irreversibly damaged, requiring the removal and replacement of the corner piece, which further increases the manpower and costs required for maintenance.

[0006] Therefore, it is desirable to propose a structure suitable for this connection part that can achieve the functions of sealing and support, and can reduce maintenance and operation costs compared to the existing technology. Summary of the Invention

[0007] The present invention was made in view of the above-mentioned technical problems, and its object is to provide a sealing and support structure for the connection between two components that are at an angle to each other on an aircraft, such as a sealing and support mechanism for the connection between an airtight floor assembly and a central wing rear spars frame assembly, or for the connection between an airtight floor assembly and an airtight end frame assembly.

[0008] The sealing and support structure according to the present invention includes a seal, a first component, and a second component, wherein the first component presses a first side of the seal against a first component, and the second component presses a second side of the seal opposite to the first side against a second component, the first component and the second component respectively support the first component and the second component, and the seal, the first component, and the second component are respectively connected to the first component and the second component by detachable connections.

[0009] In the sealing and support structure of the present invention, by separately providing a sealing element and a first and a second component serving as a support element, the sealing and support functions in the connection structure are separated. The use of detachable connecting parts, such as clearance-fit threaded connectors or bolts, compared to the use of corner pieces for both support and sealing in the prior art, facilitates the replacement of the sealing element when it reaches the fatigue threshold, ensuring the efficiency of sealing element replacement during aircraft inspection and maintenance.

[0010] In a non-limiting embodiment of the invention, the seal in the sealing and support structure is made of rubber.

[0011] In another non-limiting embodiment of the invention, the seal, the first component, and the second component in the sealing and support structure are detachably connected to the first and second components by preload bolts. Under the preload force of the preload bolts, the first and second components can better press the seal against the corresponding surfaces of the first and second components, which are at an angle to each other, thereby improving the sealing effect.

[0012] Depending on the angle between the two components at the connection where the sealing and support structure is applied, the shape of the components, and the load to be transmitted between the components, the shapes of the first and second components in the sealing and support structure according to the invention are adapted to the specific conditions. For example, the first and second components can be L-shaped profiles or flat pieces.

[0013] In a preferred embodiment of the invention, the sealing and support structure further includes at least one reinforcing member for strengthening the support of the first and second components. This at least one reinforcing member is connected to both the first and second components. Thus, the sealing and support structure achieves the transmission of force and load at the connection between the first and second components, and also achieves corner sealing at the angle between the first and second components.

[0014] In the sealing and support structure according to the present invention, the sealing and support effects of the first and second components are achieved by the sealing element and the reinforcing element, respectively. The two functions of sealing and support are separated to realize the overall variable stiffness design, avoid local high stress at the R-zone connection between the first and second components, thereby avoiding the occurrence of fatigue cracks and reducing the maintenance cost of the aircraft.

[0015] Preferably, the reinforcing member of the sealing and support structure is only partially provided at the connection between the first and second components. For example, the reinforcing member is only provided along a portion of the connection in the length direction. That is, the reinforcing member is not provided along the entire length of the connection between the first and second components. This partially provided reinforcing member allows the sealing portion of the sealing and support structure, where the reinforcing member is not present, to deform freely, while the reinforcing member, provided only along a portion of the length, provides locally enhanced stiffness to the components and sufficient support to the rest of the structure. This achieves a design of sealing and support structure according to the invention with varying overall stiffness, and because the reinforcing member is only partially provided instead of along the entire length of the connection, the weight of the sealing and support structure can be significantly reduced.

[0016] For example, when the sealing and support structure proposed in this invention is used at the connection between the airtight floor assembly and the airtight end frame assembly, a reinforcement member may be provided only at the floor longitudinal beam, specifically at the connection between the floor longitudinal beam and the column.

[0017] In a non-limiting embodiment of the invention, the reinforcing member is in the form of a reinforcing corner box. The reinforcing corner box has a first surface and a second surface, and the angle between the first surface and the second surface is formed according to the included angle between the first component and the second component.

[0018] Preferably, in order to further enhance the local rigidity provided by the reinforcing corner box, the first surface and the second surface are fixedly connected by reinforcing ribs.

[0019] Therefore, according to the present invention, the sealing and support structure, while achieving separation of sealing and support functions, provides further reinforced support to the first and second components used as support members in the structure through reinforcing members, thus making it suitable for situations where large loads are transmitted at the connection points between aircraft components. This allows the proposed sealing and support structure to provide a design with variable overall stiffness, and while significantly reducing the weight of the sealing and support structure, it still provides sufficient support to the surrounding structure. Furthermore, the proposed connection and support structure is applicable to existing aircraft structures, and the fatigue problem of existing corner fitting profiles can be improved through simple assembly. The detachable connection used in the structure related to the seal facilitates the replacement of the seal rubber after aging.

[0020] Furthermore, the present invention also proposes an aircraft having a sealing and support structure as described in any of the above embodiments.

[0021] In a non-limiting embodiment of the invention, the aircraft has an airtight floor assembly, a center wing rear spars frame assembly, and a sealing and support structure as described above. The connection between the airtight floor assembly and the rear spars frame is angled, and the sealing and support structure is used to seal and support this angled connection. A first component is a first pressure strip disposed at the frame edge of the center wing rear spars frame assembly, and a second component is a second pressure strip disposed at the airtight end plate of the airtight floor assembly. The first pressure strip is connected to the frame edge of the rear spars frame by means of a detachable connector, for example, in the form of a pre-tightened bolt, with a first side of the seal sandwiched between them. The second pressure strip is connected to the airtight end plate by means of a detachable connector, with an opposite second side of the seal sandwiched between them.

[0022] In another non-limiting embodiment of the invention, the aircraft has an airtight floor assembly, an airtight end frame assembly, and a sealing assembly according to the invention as described above, the sealing assembly having a reinforcement. The connection between the airtight floor assembly and the airtight end frame assembly is angled as described above, and the sealing and connection structure provides sealing and support to the connection.

[0023] Specifically, the sealing and support structure includes a first profile member of the floor beam disposed on a first side of the airtight floor assembly and a second profile member of the floor beam disposed on a second side of the airtight floor assembly, wherein the first side and the second side are opposite to each other. These two profile members are respectively connected to the surrounding structure via detachable connectors, and press the seals against the corresponding surfaces of the airtight floor assembly and the airtight end frame assembly, thereby achieving the effect of sealing and support.

[0024] Preferably, the aircraft has multiple floor longitudinal beams, and the sealing and support structure includes multiple reinforcing members. Particularly preferably, the number of reinforcing members corresponds to the number of floor longitudinal beams of the aircraft. More preferably, the reinforcing members are arranged only locally along the length of the connection, and particularly preferably only at the connection between the column and the floor longitudinal beam.

[0025] The aircraft according to the present invention avoids the high stress problem caused by coordinated deformation at the corner of the connection between two components in the fuselage structure, thereby improving the fatigue of the seals at the connection due to high stress. Furthermore, the locally provided reinforcement can increase the local stiffness of the structure, thereby adapting to the force and load transmission at the connection of the components and providing sufficient support for the relevant components and parts on the aircraft.

[0026] The present invention also proposes an assembly method for a sealing and support structure including a reinforcing member, used for connecting a first component and a second component on an aircraft whose connection parts are in the form of an angle and are at an angle to each other. The method includes the following steps:

[0027] 1) Complete the assembly of the first component and the second component themselves, wherein the first component is an airtight floor component and the second component is an airtight end frame component;

[0028] 2) Use tooling to position the airtight floor, airtight end frame, and floor longitudinal beams;

[0029] 3) Prepare a number of reinforcing members corresponding to the number of floor longitudinal beams;

[0030] 4) Prepare the sealing components, the first profile component of the floor beam, and the second profile component of the floor beam;

[0031] 5) Use tooling to position the sealing components, the first profile component of the floor beam, and the second profile component of the floor beam;

[0032] 6) Position the corresponding number of reinforcing components mentioned above;

[0033] 7) Rivet the reinforcing parts where greater local stiffness is required;

[0034] 8) Fasten the sealing assembly at the remaining locations of the connection with fasteners. Attached Figure Description

[0035] The advantages of the present invention will become apparent from the following detailed description with reference to the accompanying drawings. The drawings illustrate preferred embodiments of the invention by way of example, but do not limit the scope of the inventive concept.

[0036] Figure 1 The peripheral connection of the floor beam structure of an aircraft according to an embodiment of the present invention is shown in an isometric view.

[0037] Figure 2 It is shown Figure 1 A front view of the perimeter connections of the floor beam structure of the aircraft shown.

[0038] Figure 3 This is a magnified view of the perimeter connections of the aircraft's floor beam structure.

[0039] Figure 4 An isometric view shows the sealing and support structure of an embodiment of the present invention in its assembled state.

[0040] Figure 5 It shows Figure 4 An exploded three-dimensional view of the sealing and support structure is shown.

[0041] Figure 6 It shows Figure 4 The side view of the sealing and support structure shown;

[0042] Figure 7 A perspective view illustrates the connection between the airtight floor in front of the main landing bay and the rear spars frame of the central wing according to another embodiment of the present invention;

[0043] Figure 8 Shown from another angle in a 3D view Figure 7 The connecting part shown;

[0044] Figure 9 Shown in 3D Figure 7 The sealing and support structure at the connection point shown.

[0045] List of reference numerals

[0046] 1. Sealing and support structure

[0047] 11. Seals

[0048] 12. First profile component of floor beam

[0049] 13. Second profile component of floor beam

[0050] 14 Reinforced Corner Box

[0051] 141 (Reinforcing ribs for corner boxes)

[0052] 142 (First side of the reinforced corner box)

[0053] 143 (Second side of the reinforced corner box)

[0054] 2. Airtight Floor

[0055] 3. Airtight end frame

[0056] 4 pillars

[0057] 5 Floor longitudinal beams

[0058] 6. Sealing and Support Structure

[0059] 61. Edge trim

[0060] 62 Seals

[0061] 63. Pressure strip at airtight end plate

[0062] 7. Upper edge strip

[0063] 8. Airtight end plate

[0064] 9. Lower edge strip;

[0065] C. Beam frame. Detailed Implementation

[0066] Reference will now be made in detail to various embodiments of the invention, which are illustrated in the accompanying drawings and described below. Although the invention will be described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the invention to those exemplary embodiments. Rather, the invention is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of the invention as defined by the appended claims.

[0067] For ease of interpretation and precise definition in the appended claims, the terms “upper,” “lower,” “inner,” and “outer” are used to describe features with reference to the location of features in the exemplary embodiments shown in the figures, and are not intended to be limiting.

[0068] Example 1

[0069] Figure 1 The diagram schematically illustrates the perimeter connections of the aircraft's floor beam structure, showing the airtight end frame 3 within the aircraft fuselage. The airtight end frame 3 is airtightly connected to the aircraft's main landing bay aft airtight floor 2 via a sealing and support structure 1. (See diagram for details.) Figure 1 As can be seen, floor longitudinal beams 5 are also supported on the airtight floor 2. In the illustrated embodiment, a total of five floor longitudinal beams are supported. However, the number of floor longitudinal beams on the airtight floor 2 may vary depending on the actual design and construction of the aircraft. Furthermore, Figure 1 Column 4 is also shown. (For example...) Figure 1 As can be seen, there is a certain angle between the airtight floor 2 and the airtight end frame 3.

[0070] Next, turn to Figures 2 to 6 To explain in more detail how the sealing and support structure 1 achieves the airtight connection and support between the airtight end frame 3 and the airtight floor 2.

[0071] like Figure 2 As can be seen, the sealing and support structure 1 specifically includes a sealing element 11, a first profile member 12 of the floor beam, a second profile member 13 of the floor beam, and a reinforcing corner box 14 serving as a reinforcing member. In the illustrated embodiment, the first profile member 12 of the floor beam is disposed on the first side of the airtight floor 2 and is an upper profile member of the floor beam, while the second profile member 13 of the floor beam is disposed on the second side of the airtight floor 2 opposite to the first side and is a lower profile member of the floor beam.

[0072] As later Figures 4 to 6 As further shown, the first profile member 12 and the second profile member 13 of the floor beam are both L-shaped corner members made of aluminum alloy, and the seal 11 is specifically a rubber sealing strip.

[0073] Figure 3 A magnified perspective view shows details of the sealing and support structure 1 between the floor longitudinal beam 5 and the column 4. Figure 3 In the attached drawing, the line indicated by reference numeral 11 represents the rubber sealing strip 11. During the installation of the sealing and support structure 1, the sealing element 11 is pressed together by the first profile member 12 and the second profile member 13 of the floor beam. In the illustrated embodiment, specifically, under the preload of the connecting bolts, the rubber sealing element 11 is pressed together by the first profile member 12 and the second profile member 13 of the floor beam, thereby achieving the function of sealing the connection corner between the airtight floor 2 and the airtight end frame 3. Furthermore, since the airtight floor 2 and the airtight end frame 3 are supported by the aforementioned floor beam profile members 12 and 13 in the sealing and support structure 1, the sealing element 11 no longer needs to bear the high stress generated by the coordinated deformation at the connection corner.

[0074] In terms of installation, the seal 11, the first profile component 12 of the floor beam, and the second profile component 13 of the floor beam are all detachably connected to the surrounding structure. Specifically, the connections between the seal 11, the first profile component 12 of the floor beam, and the second profile component 13 of the floor beam and the surrounding structure are all achieved through intermittent bolt fitting. This connection method facilitates rapid disassembly, eliminating the need for destructive and irreversible disassembly of the connection points between the connecting structure and the airtight floor 2 and the airtight end frame 3.

[0075] This allows for the determination of the replacement interval for seal 11 based on the environmental conditions of the main cabin, thereby reducing the number of times seal 11 needs to be replaced throughout its life cycle. Such replacements can be scheduled during the aircraft's C-check, thus minimizing the impact on normal aircraft operations.

[0076] like Figure 3 and Figure 4 As can be seen, due to the relatively long connection between the airtight floor 2 and the airtight end frame 3, and the large load at this point, the sealing and support structure 1 is also equipped with a reinforcing corner box 14 to enhance the load support function. The reinforcing corner box 14 is also made of aluminum alloy.

[0077] In the illustrated embodiment, as Figure 3 As can be seen, the reinforcing corner boxes 14 are arranged only partially along the length of the connection between the airtight floor 2 and the airtight end frame 3, specifically at the connection between the column 4 and the floor longitudinal beam 5. The number of reinforcing corner boxes 14 matches the number of floor longitudinal beams 5. In the sealing and support structure 1, the first profile member 12 and the second profile member 13 of the floor beam together provide support to the airtight floor 2 and the airtight end frame 3, while the reinforcing corner boxes 14 further strengthen this support, thus forming a support structure that provides variable stiffness. The following is in conjunction with... Figures 4 to 6 This will be explained in more detail.

[0078] Figures 4 to 6 An exemplary sealing and support structure 1 is shown, wherein, Figure 5 An exploded perspective view of the sealing and support structure 1 is shown.

[0079] At the location where the reinforcing corner box 14 is provided, the reinforcing corner box 14 also supports the airtight floor 2 and the airtight end frame 3, thus providing greater structural rigidity compared to the locations in the sealing and support structure 1 where only the sealing element 11 and the floor beam profile members 12 and 13 are provided. This structural rigidity matches the magnitude of the force required to be transmitted at the connection between the airtight floor assembly and the airtight end frame assembly. In other locations in the sealing and support structure 1 where only the sealing element 11 and the floor beam profile members 12 and 13 are provided, the sealing and support structure 1 can deform more freely compared to the locations where the reinforcing corner box 14 is provided.

[0080] Therefore, in the sealing and support structure 1, the stiffness of the structure is locally increased by setting the corner box 14, while ensuring sufficient support for the rest of the structure, thereby realizing the design of the sealing and support structure 1 as a whole with variable stiffness, for example, in the length direction.

[0081] In other words, the sealing and support structure 1 can increase the rigidity of local positions in the structure by setting up the reinforced corner box 14, so that the sealing and support structure 1 can better adapt to the force and load transmission at the connection between the airtight floor 2 component and the airtight end frame 3 component of the aircraft, thereby providing sufficient rigidity support for the relevant components and parts on the fuselage.

[0082] In addition, such as Figure 4 As shown, the first surface 142 and the second surface 143 of the reinforcing corner box 14 form an angle, which in the illustrated embodiment is adapted to the angle between the airtight floor 2 assembly and the airtight end frame 3 assembly. The angle between the first surface 142 and the second surface 143 is approximately a right angle. The first surface 142 of the reinforcing corner box 14 abuts against the first profile member 12 of the floor beam, while the second surface 143 of the reinforcing corner box 14 abuts against the second profile member 13 of the floor beam. The reinforcing corner box 14 can transfer loads between the first profile member 12 and the second profile member 13 of the floor beam.

[0083] In particular, the reinforcing corner box 14 is also provided with reinforcing ribs 141 connecting the first surface 142 and the second surface 143, so as to further enhance the reinforcement of the sealing and support structure 1 by the reinforcing corner box 14.

[0084] In use, the local stiffness provided by the reinforcing corner box 14 at the sealing and support structure 1 can be adjusted by adjusting the length of the connection between the airtight floor 2 component and the airtight end frame 3 component and the thickness of the reinforcing rib 141 of the reinforcing corner box 14.

[0085] The sealing and support structure 1 may include a plurality of reinforcing corner boxes 14, each of which may vary in its extension length and the thickness of the reinforcing ribs 141, depending on the required local stiffness.

[0086] The method for connecting and assembling the sealing and support structure 1 with the airtight floor 2 assembly and the airtight end frame 3 assembly on the aircraft is as follows:

[0087] 1) Complete the assembly of the corresponding components of the airtight floor 2 and airtight end frame 3 of the civil aircraft;

[0088] 2) Use tooling to position the airtight floor 2, airtight end frame 3, and floor longitudinal beam 5;

[0089] 3) Prepare a number of reinforcing corner boxes 14 corresponding to the floor longitudinal beam 5;

[0090] 4) Prepare sealing component 11, first profile component of floor beam 12, and second profile component of floor beam 13;

[0091] 5) Position the sealing element 11, the first profile component 12 of the floor beam, and the second profile component 13 of the floor beam using tooling;

[0092] 6) Position the reinforcing corner box 14;

[0093] 7) Rivet the reinforcing corner box 14 at locations requiring greater local stiffness;

[0094] 8) Fasten the remaining parts of the sealing and support structure 1 with fasteners.

[0095] Therefore, the sealing and support structure 1 achieves a functional separation of sealing and support at corner connections between components of civil aircraft, such as the connection between the airtight floor assembly and the airtight end frame assembly. This improves the problem of fatigue in rigid connectors at the main landing bay assembly connection, specifically between the airtight floor and the airtight end frame, which is prone to fatigue and requires frequent maintenance and replacement due to coordinated deformation. Compared to existing structures that use corner fittings to achieve both sealing and support functions, the sealing and support structure 1 is significantly lighter and can be applied to existing aircraft corner component connections, thus solving the fatigue problem with only minor modifications to the existing structure. The use of bolted connections facilitates subsequent replacement of seals.

[0096] In fact, the sealing and support structure 1 according to the present invention can also be used in other structures of an aircraft that require airtight connections, as will be explained in detail in the following description of embodiment 2.

[0097] Example 2

[0098] Figure 7-9 Another application of the sealing and support structure 6 according to an embodiment of the present invention is shown.

[0099] In this embodiment 2, the sealing and support structure 6 is located at the connection between the airtight floor assembly at the front of the main landing bay and the rear spars frame assembly of the central wing. For example... Figure 7 , Figure 8 As can be seen in Figure 7 The sealing and support structure 6, shown by the dashed line, is located at the connection structure between the upper edge strip 7, the airtight end plate 8, the lower edge strip 9, and the beam frame C.

[0100] Beam frame C here is a large reinforcing frame located at the free end. Beam frame C is a single, C-shaped component. Figure 8 To clearly show the sealing and support structure 6, only a portion of the beam frame C is shown, and the upper part of the beam frame C is not shown.

[0101] like Figure 9 As can be seen, the sealing and support structure 6 includes a frame edge strip 61, a seal 62, and an airtight end plate strip 63. The seal 62 is a rubber seal. The frame edge strip 61 and the airtight end plate strip 63 are made of aluminum alloy.

[0102] Unlike Embodiment 1 described above, the frame edge strip 61 and the airtight end plate strip 63, which play a supporting role in the sealing and supporting structure 6, are adapted to the angle between the airtight floor assembly and the beam frame assembly and are constructed in the form of planar parts.

[0103] When installing the sealing and support structure 6, the seal 62 is pressed against the central wing rear beam frame C by means of the frame edge pressure strip 61 using bolts with clearance fit (not shown), and the opposite side of the seal 62 is pressed against the airtight end plate 8 by means of the airtight end plate pressure strip 63, thereby achieving a seal at the corner component connection.

[0104] The edge strip 61 and the airtight end plate strip 63 play a supporting role for the beam frame C and the airtight end plate 8 in the sealing and support structure 6, and bear the coordinated deformation between the airtight floor 8 assembly and the central wing rear beam frame C assembly.

[0105] Because the length of the connection where the sealing and support structure 6 is applied is shorter than the length of the connection where the sealing and support structure 1 is applied in Embodiment 1 described above, the load is smaller, and because... Figure 8The lower edge strip 9 shown also structurally connects the airtight floor 8 assembly and the central wing rear beam frame C assembly, which can transfer the load between the two assemblies and play a supporting and reinforcing role for the pressure strips 61 and 63. Therefore, in the embodiment shown, the sealing and support structure 6 may not have a reinforcing member, such as a reinforcing corner box.

[0106] However, in use, reinforcing corner boxes can be installed as needed, depending on the length of the connection between the two components connected by the sealing and support structures and the magnitude of the load.

[0107] In the sealing and support structure 6, when the seal 62 reaches its fatigue service life, it is only necessary to loosen the clearance fit bolts (not shown in the figure) and from... Figure 7 By disassembling the connection between the pressure strip 61 at the frame edge and the frame edge C on one side (inner side), and disassembling the connection between the pressure strip 63 at the airtight end plate and the airtight end plate 8, the seal 62 can be removed and replaced. This makes the installation, disassembly, and replacement of the seal 62 in the sealing and support structure 6 more convenient, and helps to improve the efficiency of aircraft maintenance.

[0108] Within the scope of this invention, various embodiments can be freely combined, or appropriately modified or omitted.

Claims

1. A sealing and support structure for a connection between a first component and a second component in an aircraft that are at a non-zero angle to each other, wherein, The first component is the airtight floor assembly of the aircraft, the second component is the airtight end frame assembly of the aircraft, and the sealing and support structure is used for the connection between the airtight floor assembly and the airtight end frame assembly. The sealing and support structure includes a sealing element, a first component, a second component, and a reinforcing element, wherein the reinforcing element is in the form of a reinforcing corner box. In this configuration, the first component presses a first side of the seal against the first assembly, and the second component presses a second side of the seal, opposite to the first side, against the second assembly. The sealing element, the first component, and the second component are detachably connected to the first and second assemblies, respectively. The first and second components are independent of each other and respectively support the first and second assemblies. The reinforcing member is only partially provided along the length of the connecting portion, and the reinforcing member, in the form of a reinforcing corner box, is force-transmittingly connected to the first component and the second component, respectively, and supports the first component and the second component. The first component is disposed on the first side of the airtight floor assembly as a first profile component of the floor beam, while the second component is disposed on the second side of the airtight floor assembly as a second profile component of the floor beam. The aircraft includes multiple floor longitudinal beams, and the sealing and support structure includes multiple reinforcing members in the form of reinforced corner boxes, the number of which corresponds to the number of floor longitudinal beams.

2. The sealing and support structure as described in claim 1, characterized in that, The seal, the first component, and the second component are connected to the first and second components with clearance fit via preloaded bolts.

3. The sealing and support structure as described in claim 1 or 2, characterized in that, The reinforcing member, which is in the form of a reinforced corner box, has a first surface and a second surface, and the first surface and the second surface are fixedly connected by reinforcing ribs.

4. The sealing and support structure as described in claim 1 or 2, characterized in that, The shapes of the first component and the second component are adapted to the angle between the first component and the second component.

5. An aircraft comprising: an airtight floor assembly, an airtight end frame assembly, a plurality of floor longitudinal beams, and a sealing and support structure as described in any one of claims 1 to 4.

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