An aircraft cabin and an aircraft

Abstract

This application relates to an aircraft cabin and an aircraft, specifically to the field of aircraft thermal protection structure technology. The cabin includes an outer shell comprising a load-bearing layer and a heat-resistant layer. The heat-resistant layer is disposed outside the load-bearing layer and includes an outer three-dimensional woven fabric layer and an inner three-dimensional woven fabric layer. The density of the outer three-dimensional woven fabric layer is greater than that of the inner three-dimensional woven fabric layer, and the density of the outer three-dimensional woven fabric layer is greater than the critical density value required to achieve ablation resistance. Because the outer three-dimensional woven fabric layer has a higher density, exceeding the critical density value for ablation resistance, it can improve ablation resistance. Furthermore, the higher density of the outer three-dimensional woven fabric layer compared to the inner three-dimensional woven fabric layer allows for a reduction in the overall density of the heat-resistant layer while maintaining its ablation resistance performance, thus improving its overall thermal insulation performance. This addresses the problem in existing technologies where it is difficult to meet both heat protection and ablation resistance requirements, affecting the reliable operation of the aircraft.

Description

Technical Field

[0001] This invention relates to the field of aircraft thermal protection structure technology, specifically to an aircraft cabin and an aircraft. Background Technology

[0002] Thermal protection materials are generally called ablation materials or ablation heat-resistant materials. The application of ablation heat-resistant materials is one of the main uses of composite materials in high-tech fields. Aircraft flying at high speeds in the atmosphere experience severe aerodynamic heating. To protect the structure and internal equipment of the aircraft and ensure their safe and reliable operation, thermal protection structures need to be designed.

[0003] In the existing technology, under normal circumstances, the aircraft cabin will preferably use an integral shell and thermal protection structure, which has the advantages of simple structure and high reliability.

[0004] However, under conditions of high heat flux, high dynamic pressure, and high shear force, traditional high-silica phenolic fiberglass or low-density quartz fiber phenolic composite materials are difficult to meet the requirements for ablation resistance, and there are problems that cannot meet the requirements for heat protection and ablation resistance, affecting the reliable operation of the aircraft. Summary of the Invention

[0005] This application provides an aircraft cabin and an aircraft that can solve the problem in the prior art that, under the conditions of high heat flux, high dynamic pressure, and high shear force thermal environment, the traditional high silica phenolic fiberglass or low density quartz fiber phenolic composite materials are difficult to meet the ablation resistance requirements, and have difficulty meeting the heat protection and ablation resistance requirements, thus affecting the reliable operation of the aircraft.

[0006] In a first aspect, embodiments of this application provide an aircraft cabin, which includes: The outer shell of the cabin includes a load-bearing layer and a heat-insulating layer. The heat-insulating layer is disposed outside the load-bearing layer. The heat-insulating layer includes an outer three-dimensional woven fabric layer and an inner three-dimensional woven fabric layer. The density of the outer three-dimensional woven fabric layer is greater than the density of the inner three-dimensional woven fabric layer, and the density of the outer three-dimensional woven fabric layer is greater than the critical density value that satisfies the ablation resistance effect.

[0007] In one embodiment, the system includes four load-bearing layers, each of which has a corresponding heat-insulating layer. The load-bearing layers have an L-shaped cross-section, and the four load-bearing layers are interconnected to form the frame of the cabin shell.

[0008] In one embodiment, both ends of the heat-insulating layer are stepped, and the ends of adjacent heat-insulating layers match in shape and overlap each other.

[0009] In one embodiment, the outer three-dimensional woven fabric layer of the heat-insulating layer on the overlapping side extends toward the supporting layer, covering the end of the corresponding inner three-dimensional woven fabric layer, and is stepped, with the heat-insulating layer on the overlapping side overlapping the end of the outer three-dimensional woven fabric layer of the heat-insulating layer on the overlapping side.

[0010] In one embodiment, the end of the bearing layer on the overlapping side extends outward to form an overlapping boss, the bearing layer on the overlapping side overlaps the overlapping boss, and is fixed by a screw assembly passing through the bearing layer on the overlapping side and the overlapping boss.

[0011] In one embodiment, the heat-insulating layer has stepped holes, and the screw assembly includes: The fastening screw has its shank passing through the heat-insulating layer and the load-bearing layer on the overlapping side and is fixed on the overlapping boss. The screw head of the fastening screw is located in the large-diameter section of the stepped hole. A heat-resistant cap is disposed at the end of the fastening screw and located within the large-diameter section of the stepped hole, with the upper side of the heat-resistant cap flush with the upper side of the heat-resistant layer.

[0012] In one embodiment, the screw assembly further includes a flat washer located within the large-diameter section of the stepped hole and between the screw head of the fastening screw and the heat-insulating layer.

[0013] In one embodiment, the overlapping protrusion is provided with an installation groove, the installation groove is provided along the length direction of the bearing layer, and a sealing ring is provided in the installation groove, the sealing ring abutting against the lower side of the bearing layer on the overlapping side.

[0014] In one embodiment, the outer three-dimensional woven fabric layer comprises three outer three-dimensional woven fabric layers, and the inner three-dimensional woven fabric layer comprises four inner three-dimensional woven fabric layers, wherein any outer three-dimensional woven fabric or inner three-dimensional woven fabric is connected to the adjacent outer three-dimensional woven fabric or inner three-dimensional woven fabric.

[0015] Secondly, embodiments of this application also provide an aircraft, which includes the aforementioned aircraft cabin.

[0016] The beneficial effects of the technical solutions provided in this application include: In designing the aircraft cabin, the heat insulation layer is located outside the load-bearing layer. This layer comprises an outer three-dimensional woven fabric layer and an inner three-dimensional woven fabric layer. The density of the outer three-dimensional woven fabric layer is greater than that of the inner layer, and its density also exceeds the critical density value required for ablation resistance. Because the outer three-dimensional woven fabric layer has a higher density than the critical density value for ablation resistance, it enhances ablation resistance. Furthermore, the higher density of the outer layer compared to the inner layer allows for a reduction in the overall density of the heat insulation layer while maintaining its ablation resistance performance, thus improving its overall thermal insulation performance. This addresses the problem in existing technologies where traditional high-silica phenolic fiberglass or low-density quartz fiber phenolic composite materials struggle to meet ablation resistance requirements under conditions of high heat flux, high dynamic pressure, and high shear force, resulting in insufficient heat insulation and ablation resistance and impacting the reliable operation of the aircraft.

[0017] The heat-resistant layer is formed by composite curing of a 2.5D quartz fiber woven preform and an ablation-resistant phenolic resin matrix. All the outer and inner three-dimensional woven fabrics are sewn together by connecting lines using a through-stitch method, which simplifies the product manufacturing process while ensuring the heat-resistant performance of the heat-resistant layer.

[0018] A refined heat-insulating layer fabric structure design was implemented, which improved the heat insulation performance and air-peel resistance of the heat-insulating layer. 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 This is a structural schematic diagram of an embodiment of an aircraft cabin according to the present invention.

[0021] Figure 2 This is a cross-sectional structural diagram of an embodiment of an aircraft cabin according to the present invention.

[0022] Figure 3 This is a schematic diagram of the structure of the outer surface of an embodiment of an aircraft cabin according to the present invention.

[0023] Figure 4 for Figure 3 A schematic diagram of the structure of section AA.

[0024] Figure 5 for Figure 3 Schematic diagram of the structure of section BB.

[0025] Figure 6 for Figure 3 A schematic diagram of the CC section.

[0026] Figure 7 This is a schematic diagram of the structure of the heat-resistant layer in an embodiment of an aircraft cabin according to the present invention.

[0027] Figure 8 This is a schematic diagram of the connecting line structure in one embodiment of the aircraft cabin of the present invention.

[0028] In the diagram: 1. Outer shell; 2. Heat shield layer; 21. Outer 3D woven fabric layer; 211. Outer 3D woven fabric; 22. Inner 3D woven fabric layer; 221. Inner 3D woven fabric; 3. Bearing layer; 31. Overlapping boss; 311. Mounting groove; 4. Screw assembly; 41. Fastening screw; 42. Heat shield cap; 43. Flat washer; 5. Sealing ring; 6. Connecting wire; 7. Mounting screw; 8. Heat sealant. Detailed Implementation

[0029] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present application.

[0030] This application provides an aircraft cabin and an aircraft that can solve the problem in the prior art that, under the conditions of high heat flux, high dynamic pressure, and high shear force thermal environment, traditional high silica phenolic fiberglass or low density quartz fiber phenolic composite materials are difficult to meet the ablation resistance requirements, and have difficulty meeting the heat protection and ablation resistance requirements, thus affecting the reliable operation of the aircraft.

[0031] like Figure 1 and Figure 2 As shown, in one aspect, this application provides an aircraft cabin, which includes: The outer shell 1 of the cabin includes a load-bearing layer 3 and a heat-insulating layer 2. The heat-insulating layer 2 is disposed outside the load-bearing layer 3. The heat-insulating layer 2 includes an outer three-dimensional woven fabric layer 21 and an inner three-dimensional woven fabric layer 22. The density of the outer three-dimensional woven fabric layer 21 is greater than the density of the inner three-dimensional woven fabric layer 22, and the density of the outer three-dimensional woven fabric layer 21 is greater than the critical density value that satisfies the ablation resistance effect.

[0032] When designing the aircraft cabin, the heat shield 2 is set outside the load-bearing layer 3. The heat shield 2 includes an outer three-dimensional woven fabric layer 21 and an inner three-dimensional woven fabric layer 22. The density of the outer three-dimensional woven fabric layer 21 is greater than the density of the inner three-dimensional woven fabric layer 22, and the density of the outer three-dimensional woven fabric layer 21 is greater than the critical density value that satisfies the ablation resistance effect. Because the outer three-dimensional woven fabric layer 21 has a higher density than the critical density value required to meet the ablation resistance effect, the outer three-dimensional woven fabric layer 21 can improve the ablation resistance. Since the density of the outer three-dimensional woven fabric layer 21 is greater than that of the inner three-dimensional woven fabric layer 22, the overall density of the heat-insulating layer 2 can be reduced while ensuring the ablation resistance performance of the heat-insulating layer 2, thereby improving the comprehensive heat insulation performance of the heat-insulating layer 2. This can solve the problem in the existing technology that, under the conditions of high heat flux, high dynamic pressure, and high shear force thermal environment, it is difficult to meet the ablation resistance requirements using traditional high-silica phenolic fiberglass or low-density quartz fiber phenolic composite materials, resulting in the inability to meet the heat protection and ablation resistance requirements and affecting the reliable operation of the aircraft.

[0033] like Figure 3 and Figure 4 As shown, in this example, the heat-insulating layer 2 is a composite material of 2.5D quartz fiber woven preform and ablation-resistant phenolic resin matrix, cured to meet the heat insulation requirements. The load-bearing layer 3 is made of aluminum alloy or other metal materials through casting and machining to meet the load-bearing requirements. The load-bearing layer 3 and the heat-insulating layer 2 are bonded together with high-temperature resistant rubber, and the heat-insulating layer 2 is also fixed to the load-bearing layer 3 by mounting screws 7, which improves the assembly reliability between the heat-insulating layer 2 and the load-bearing layer 3. The mounting screws 7 are made of a composite material of high-silica fiber and phenolic resin molded together with high temperature resistance.

[0034] like Figure 1 , Figure 2 and Figure 3 As shown, in some optional embodiments, four load-bearing layers 3 are included, each load-bearing layer 3 is provided with a corresponding heat-insulating layer 2, the cross-section of the load-bearing layer 3 is L-shaped, and the four load-bearing layers 3 are connected to each other to form the frame of the cabin shell 1.

[0035] In this embodiment, the aircraft cabin includes four load-bearing layers 3, each load-bearing layer 3 is provided with a corresponding heat-insulating layer 2, the cross-section of the load-bearing layer 3 is L-shaped, and the four load-bearing layers 3 are connected to each other to form the frame of the cabin shell 1. Compared with the design where the connection is set at the four corners of a rectangle, this design has a relatively higher load-bearing capacity, making the structure of the split aircraft cabin more stable.

[0036] In this example, 12 mounting screws 7 are provided on two opposing support layers 3, and 24 mounting screws 7 are provided on the other two opposing support layers 3.

[0037] like Figure 5 , Figure 6 and Figure 7 As shown, in some optional embodiments, both ends of the heat-insulating layer 2 are stepped, the ends of adjacent heat-insulating layers 2 match in shape and overlap each other.

[0038] In this embodiment, both ends of the heat shield 2 are stepped, the ends of adjacent heat shield 2 are matched and overlap each other, adopting a stepped fit and a labyrinthine structure, which helps to reduce the impact of aerodynamic heat flow on the cabin.

[0039] In this example, the thickness of heat-insulating layer 2 is 14mm. The protrusion of the overlapping side of heat-insulating layer 2 is 8mm thick and 7.5mm wide. The step depth of the overlapping side of heat-insulating layer 2 is 8.5mm and the width is 8mm. The gap between the heat-insulating layers 2 on both sides of the overlap is 0.5mm. A heat-sealing filler 8 is provided at the joint of the heat-insulating layers 2 on both sides to ensure the heat sealing requirements of the overlap. The heat-sealing filler 8 is a high-temperature resistant quartz fiber cloth, and the fibers are bonded and fixed in the gap with high-temperature resistant putty.

[0040] like Figure 7 As shown, in some optional embodiments, the outer three-dimensional woven fabric layer 21 of the heat-insulating layer 2 on the overlapping side extends toward the supporting layer 3, covering the end of the corresponding inner three-dimensional woven fabric layer 22, and is in a stepped shape, with the heat-insulating layer 2 on the overlapping side overlapping the end of the outer three-dimensional woven fabric layer 21 of the heat-insulating layer 2 on the overlapping side.

[0041] In this embodiment, the outer three-dimensional woven fabric layer 21 of the heat-insulating layer 2 on the overlapping side extends toward the supporting layer 3, covering the corresponding inner three-dimensional woven fabric layer 22 and forming a stepped shape. The heat-insulating layer 2 on the overlapping side overlaps the outer three-dimensional woven fabric layer 21 of the heat-insulating layer 2 on the overlapping side. By constraining the heat-insulating layer 2 on the overlapping side, the heat-insulating layer 2 on the overlapping side is constrained, thereby improving the anti-pneumatic peeling performance of the heat-insulating layer 2 and preventing the surface woven fabric from peeling off as a whole under pneumatic shearing force.

[0042] like Figure 5 , Figure 6 and Figure 7 As shown, in some optional embodiments, the end of the bearing layer 3 on the overlapping side extends outward to form an overlapping boss 31, the bearing layer 3 on the overlapping side overlaps on the overlapping boss 31, and is fixed by a screw assembly 4 passing through the bearing layer 3 on the overlapping side and the overlapping boss 31.

[0043] In this embodiment, the end of the bearing layer 3 on the overlapping side extends outward to form an overlapping boss 31. The bearing layer 3 on the overlapping side overlaps on the overlapping boss 31. The screw assembly 4 passes through the bearing layer 3 on the overlapping side and is fixed on the overlapping boss 31. In this way, the bearing layer 3 on the overlapping side and the bearing layer 3 on the overlapping side are connected, the connection is more stable, the load-bearing performance is relatively higher, and the structure of the split aircraft cabin is more stable. In addition, the stepped fit and the labyrinth structure are beneficial to reducing the impact of aerodynamic heat flow on the cabin.

[0044] like Figure 5 As shown, in some optional embodiments, the heat-insulating layer 2 has stepped holes, and the screw assembly 4 includes: Fastening screw 41, the screw shank of fastening screw 41 passes through the heat-insulating layer 2 and the bearing layer 3 on the overlapping side and is fixed on the overlapping boss 31, and the screw head of fastening screw 41 is located in the large diameter section of the stepped hole. The heat-proof cap 42 is located at the end of the fastening screw 41 and within the large-diameter section of the stepped hole. The upper side of the heat-proof cap 42 is flush with the upper side of the heat-proof layer 2.

[0045] In this embodiment, a stepped hole is provided on the heat-insulating layer 2. The screw assembly 4 includes a fastening screw 41 and a heat-insulating cap 42. The screw shank of the fastening screw 41 passes through the heat-insulating layer 2 and the bearing layer 3 on the overlapping side and is fixed on the overlapping boss 31. The screw head of the fastening screw 41 is located in the large diameter section of the stepped hole. The heat-insulating cap 42 is provided at the end of the fastening screw 41 and is located in the large diameter section of the stepped hole. The upper side of the heat-insulating cap 42 is flush with the upper side of the heat-insulating layer 2, which ensures the connection performance of the bearing layer 3 on the overlapping side and the bearing layer 3 on the overlapping side. The heat-insulating cap 42 can ensure thermal protection at the stepped hole. The fact that the upper side of the heat-insulating cap 42 is flush with the upper side of the heat-insulating layer 2 also reduces the resistance that may be caused by the unevenness of the surface of the heat-insulating layer 2.

[0046] In this example, the diameter of the hole through which the fastening screw 41 passes in the bearing layer 3 on the overlapping side is the same as the diameter of the small diameter section of the stepped hole. The heat-resistant cap 42 is made of ablation-resistant heat-protective material and is molded integrally with the fastening screw 41. Seven screw assemblies 4 are provided at a single mating step of the heat-resistant layer 2.

[0047] like Figure 5 As shown, in some optional embodiments, the screw assembly 4 further includes a flat washer 43 located within the large-diameter section of the stepped hole and between the screw cap of the fastening screw 41 and the heat-insulating layer 2.

[0048] In this embodiment, the screw assembly 4 also includes a flat washer 43, which is located in the large diameter section of the stepped hole and between the screw head of the fastening screw 41 and the heat-insulating layer 2. The diameter of the flat washer 43 is larger than the diameter of the screw head of the fastening screw 41, which increases the contact area of ​​the installation part and can reduce the concentrated stress on the heat-insulating layer 2 by the installation preload of the fastening screw 41.

[0049] like Figure 5 As shown, in some optional embodiments, the overlapping boss 31 is provided with a mounting groove 311, which is arranged along the length direction of the bearing layer 3. A sealing ring 5 is provided in the mounting groove 311, and the sealing ring 5 abuts against the lower side of the bearing layer 3 on the overlapping side.

[0050] In this embodiment, an installation groove 311 is provided on the overlapping boss 31. The installation groove 311 is arranged along the length direction of the bearing layer 3. A sealing ring 5 is provided in the installation groove 311. The sealing ring 5 abuts against the lower side of the bearing layer 3 on the overlapping side, so as to meet the water sealing requirements of the joint between the bearing layer 3 on the overlapping side and the bearing layer 3 on the overlapping side.

[0051] In this example, the sealing ring 5 has an O-shaped cross-section and is made of silicone rubber.

[0052] like Figure 7 As shown, in some optional embodiments, the outer three-dimensional woven fabric layer 21 includes three outer three-dimensional woven fabric layers 211, and the inner three-dimensional woven fabric layer 22 includes four inner three-dimensional woven fabric layers 221. Each outer three-dimensional woven fabric layer 211 or inner three-dimensional woven fabric layer 221 is connected to the adjacent outer three-dimensional woven fabric layer 211 or inner three-dimensional woven fabric layer 221.

[0053] In this embodiment, the outer three-dimensional woven fabric layer 21 includes three layers of outer three-dimensional woven fabric 211, and the inner three-dimensional woven fabric layer 22 includes four layers of inner three-dimensional woven fabric 221. Each outer three-dimensional woven fabric 211 or inner three-dimensional woven fabric 221 is connected to the adjacent outer three-dimensional woven fabric 211 or inner three-dimensional woven fabric 221. The multi-layer three-dimensional woven fabric is more convenient to manufacture than the single-layer three-dimensional woven fabric with a larger thickness, and the cost is also lower. It achieves the heat protection effect of a high-cost overall woven body. The connection between each outer three-dimensional woven fabric 211 or inner three-dimensional woven fabric 221 and the adjacent outer three-dimensional woven fabric 211 or inner three-dimensional woven fabric 221 also ensures the overall stability of the heat protection layer 2.

[0054] In this example, both the outer three-dimensional woven fabric 211 and the inner three-dimensional woven fabric 221 are 2.5D quartz fiber woven fabrics. The fiber volume content of the outer three-dimensional woven fabric 211 is 45%, and the fiber volume content of the inner three-dimensional woven fabric 221 is 35%. The thickness of a single layer of 2.5D quartz fiber woven fabric is 2mm.

[0055] like Figure 7 and Figure 8 As shown, in this example, all outer three-dimensional woven fabrics 211 and inner three-dimensional woven fabrics 221 are sewn together using a through-stitch method via connecting thread 6, increasing the interlayer bonding strength and improving ablation resistance. Connecting thread 6 is made of quartz fiber, and the stitch span, spacing, and row spacing are all 5mm. Connecting thread 6, outer three-dimensional woven fabrics 211, and inner three-dimensional woven fabrics 221 all use type B quartz fiber.

[0056] like Figure 1 and Figure 2 As shown, on the other hand, this application also provides an aircraft that includes the aforementioned aircraft cabin.

[0057] When designing the aircraft cabin, the heat shield 2 is set outside the load-bearing layer 3. The heat shield 2 includes an outer three-dimensional woven fabric layer 21 and an inner three-dimensional woven fabric layer 22. The density of the outer three-dimensional woven fabric layer 21 is greater than the density of the inner three-dimensional woven fabric layer 22, and the density of the outer three-dimensional woven fabric layer 21 is greater than the critical density value that satisfies the ablation resistance effect. Because the outer three-dimensional woven fabric layer 21 has a higher density than the critical density value required to meet the ablation resistance effect, the outer three-dimensional woven fabric layer 21 can improve the ablation resistance. Since the density of the outer three-dimensional woven fabric layer 21 is greater than that of the inner three-dimensional woven fabric layer 22, the overall density of the heat-insulating layer 2 can be reduced while ensuring the ablation resistance performance of the heat-insulating layer 2, thereby improving the comprehensive heat insulation performance of the heat-insulating layer 2. This can solve the problem in the existing technology that, under the conditions of high heat flux, high dynamic pressure, and high shear force thermal environment, it is difficult to meet the ablation resistance requirements using traditional high-silica phenolic fiberglass or low-density quartz fiber phenolic composite materials, resulting in the inability to meet the heat protection and ablation resistance requirements and affecting the reliable operation of the aircraft.

[0058] In summary, the aircraft cabin and aircraft proposed in this application effectively solve the problems of reliable assembly, heat protection, load bearing, and sealing of aircraft cabins, and have the advantages of simple structure, good heat protection and load bearing performance, good sealing performance, and simple assembly. It can solve the problem in existing technologies where, under conditions of high heat flux, high dynamic pressure, and high shear force, traditional high-silica phenolic fiberglass or low-density quartz fiber phenolic composite materials are unable to meet ablation resistance requirements, resulting in insufficient heat protection and ablation resistance, thus affecting the reliable operation of the aircraft.

[0059] 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.

[0060] 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.

[0061] 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. An aircraft cabin, characterized in that, include: The outer shell (1) of the cabin includes a load-bearing layer (3) and a heat-insulating layer (2). The heat-insulating layer (2) is disposed on the outside of the load-bearing layer (3). The heat-insulating layer (2) includes an outer three-dimensional woven fabric layer (21) and an inner three-dimensional woven fabric layer (22). The density of the outer three-dimensional woven fabric layer (21) is greater than the density of the inner three-dimensional woven fabric layer (22), and the density of the outer three-dimensional woven fabric layer (21) is greater than the critical density value that satisfies the ablation resistance effect. It includes four load-bearing layers (3), each load-bearing layer (3) is provided with a corresponding heat-insulating layer (2), the cross-section of the load-bearing layer (3) is L-shaped, and the four load-bearing layers (3) are connected to each other to form the frame of the cabin shell (1); Both ends of the heat-insulating layer (2) are stepped, and the ends of adjacent heat-insulating layers (2) match each other and overlap. The outer three-dimensional woven fabric layer (21) of the heat-insulating layer (2) on the overlapping side extends toward the bearing layer (3) and covers the end of the corresponding inner three-dimensional woven fabric layer (22), and is stepped. The heat-insulating layer (2) on the overlapping side overlaps the end of the outer three-dimensional woven fabric layer (21) of the heat-insulating layer (2) on the overlapping side. The end of the bearing layer (3) on the overlapping side extends outward to form an overlapping boss (31). The bearing layer (3) on the overlapping side overlaps on the overlapping boss (31) and is fixed by a screw assembly (4) passing through the bearing layer (3) on the overlapping side and the overlapping boss (31).

2. The aircraft cabin as described in claim 1, characterized in that, The heat-insulating layer (2) is provided with stepped holes, and the screw assembly (4) includes: The fastening screw (41) has its screw shank passing through the heat-insulating layer (2) and the bearing layer (3) on the overlapping side and is fixed on the overlapping boss (31). The screw head of the fastening screw (41) is located in the large diameter section of the stepped hole. A heat-resistant cap (42) is disposed at the end of the fastening screw (41) and located within the large diameter section of the stepped hole. The upper side of the heat-resistant cap (42) is flush with the upper side of the heat-resistant layer (2).

3. The aircraft cabin as described in claim 2, characterized in that, The screw assembly (4) also includes a flat washer (43) located within the large diameter section of the stepped hole and between the screw cap of the fastening screw (41) and the heat-insulating layer (2).

4. The aircraft cabin as described in claim 1, characterized in that, The overlapping boss (31) is provided with an installation groove (311), which is arranged along the length of the bearing layer (3). A sealing ring (5) is provided in the installation groove (311), and the sealing ring (5) abuts against the lower side of the bearing layer (3) on the overlapping side.

5. The aircraft cabin as described in claim 1, characterized in that, The outer three-dimensional woven fabric layer (21) includes three outer three-dimensional woven fabrics (211), and the inner three-dimensional woven fabric layer (22) includes four inner three-dimensional woven fabrics (221). Any outer three-dimensional woven fabric (211) or inner three-dimensional woven fabric (221) is connected to the adjacent outer three-dimensional woven fabric (211) or inner three-dimensional woven fabric (221).

6. An aircraft, characterized in that, Including an aircraft cabin as described in any one of claims 1-5.

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