A head seal protection member for an aircraft

Abstract

The present application relates to a kind of heat sealing structures for aircraft, and specifically relates to a kind of head sealing protection components for aircraft.The technical problem that the present application solves is that the whole forming is used in the existing head protection component, which leads to the installation space being all concentrated between the head protection component and the aircraft body, making the connection of the head protection component and the aircraft body complex, inconvenient to install, high in cost and difficult to maintain.The head protection component includes a head cover, a metal connecting piece and a heat sealing assembly.The heat sealing assembly includes a plug, a pad and a rigid thermal insulation pad.The plug includes a plug cap and a cylindrical boss.A first clamping slot and a first threaded hole are provided on the pad.The cylindrical boss is inserted into the first threaded hole of the pad, and the plug cap is in contact with the first clamping slot.The rigid thermal insulation pad is provided with a first round hole and a second clamping slot.The pad is arranged in the second clamping slot.A first mounting slot and a second threaded hole are provided on the head cover.The rigid thermal insulation pad is arranged in the first mounting slot.The plug, the pad and the head cover are all made of ceramic matrix composite material.

Description

Technical Field

[0001] This invention relates to a heat-sealing protective component for aircraft, specifically to a nose sealing protective component for aircraft. Background Technology

[0002] During high-speed flight, the nose of an aircraft is exposed to a high-temperature and high-abrasion environment. Typically, the nose is protected by ablation-resistant ceramic composite material nose protection components. The nose protection components of high-speed aircraft need to protect the aircraft from high temperatures and friction during high-speed flight. Therefore, the thermal sealing performance and installation feasibility of the ceramic composite material nose protection components are subject to extremely high requirements.

[0003] Ceramic composite head protection components are generally large-sized, thin-walled composite parts, typically manufactured using the CVI molding method. Because composite parts are prone to deformation and other defects during CVI molding, existing head protection components are integrally molded to ensure heat sealing and control of component deformation. This results in the entire installation space being concentrated between the head protection component and the aircraft fuselage, making the connection between the head protection component and the aircraft fuselage complex, installation extremely inconvenient, costly, and difficult to maintain later. Summary of the Invention

[0004] The purpose of this invention is to solve the technical problems of existing ceramic composite head protection components using CVI integral molding, which results in the entire installation space being concentrated between the head protection component and the aircraft body, making the connection between the head protection component and the aircraft body complex, extremely inconvenient to install, high cost, and difficult to maintain later. The invention provides a head sealing protection component for aircraft.

[0005] The technical solution of this invention is:

[0006] The present invention provides a head sealing and protection component for an aircraft, including a head cover for protecting the head of the aircraft body and a metal connector connecting the head cover and the head of the aircraft body. Its special feature is that it also includes a heat-sealing component that is detachably disposed on the upper end face of the head cover.

[0007] The heat-sealing assembly includes a plug, a gasket, and a rigid heat insulation pad;

[0008] The plug includes a plug cap and a columnar boss located in the middle of the bottom surface of the plug cap, and the outer surface of the columnar boss is provided with external threads;

[0009] The upper end face of the pad is provided with a first groove whose inner diameter is adapted to the outer diameter of the plug cap, and the middle part is provided with a first threaded hole that mates with the external thread of the columnar boss.

[0010] The columnar boss is inserted into the first threaded hole through a threaded connection, and the bottom surface of the plug cap is in contact with the bottom of the first slot, and the outer side wall of the plug cap is in contact with the wall of the first slot.

[0011] The rigid heat insulation pad has a first circular hole in the middle and a second slot with an inner diameter that matches the outer diameter of the pad on the upper surface.

[0012] The pad is disposed in the second slot, and the bottom surface of the pad is in contact with the bottom of the second slot, and the outer side wall of the pad is in contact with the wall of the second slot.

[0013] The upper surface of the head cover is provided with a first mounting groove and a second threaded hole. The second threaded hole is located in the first mounting groove and is used to connect the head of the aircraft body through a metal connector.

[0014] The rigid heat insulation pad is disposed in the first mounting groove, and the bottom surface of the rigid heat insulation pad is in contact with the bottom of the first mounting groove, and the outer side wall of the rigid heat insulation pad is in contact with the groove wall of the first mounting groove; the first threaded hole and the first round hole are respectively provided with the second threaded hole for the installation and disassembly of the metal connector.

[0015] The plug, pad, and head cover are all made of ceramic matrix composite material.

[0016] Furthermore, the heat-sealing assembly also includes a cap; the cap has a second circular hole with an inner diameter that matches the outer diameter of the plug cap, the bottom end of the columnar boss passes through the second circular hole and is connected to the first threaded hole, and the upper end face of the plug cap is flush with the upper end face of the cap, and the upper end face of the pad is in contact with the lower end face of the cap; the head cover has a second mounting groove with a size that matches the cap, the first mounting groove is located in the second mounting groove, and the two form a stepped structure; the cap is disposed in the second mounting groove.

[0017] Furthermore, the heat-sealing assembly also includes a flexible heat-insulating pad disposed on the upper surface of the rigid heat-insulating pad; the flexible heat-insulating pad is provided with a third circular hole whose inner diameter is adapted to the outer diameter of the pad block, the flexible heat-insulating pad is fitted around the pad block through the third circular hole, the outer wall of the upper part of the pad block is in contact with the inner wall of the third circular hole, and the outer wall of the lower part is in contact with the groove wall of the second slot; the upper end face of the flexible heat-insulating pad is connected to the lower end face of the cap.

[0018] Furthermore, the cover is made of ceramic-based composite material; the flexible heat insulation pad is also made of ceramic-based composite material.

[0019] Furthermore, the pad and the head cap are connected by ceramic matrix composite screws, and the pad and the head cover are riveted by ceramic matrix composite pins.

[0020] Furthermore, the heat-sealing assembly also includes high-temperature anti-loosening adhesive; the high-temperature anti-loosening adhesive is filled between the columnar boss of the plug and the first threaded hole.

[0021] Furthermore, the first slot of the pad is provided with six equally divided threaded holes, and the pad and the plug are connected to the six equally divided threaded holes by ceramic matrix composite screws, and the distance between adjacent threaded holes is 1mm.

[0022] Furthermore, the cover is riveted to the second mounting groove by ceramic matrix composite screws and ceramic matrix composite pins; the pad (2) is riveted to the rigid heat insulation pad (6) by ceramic matrix composite pins; the rigid heat insulation pad (6) is connected to the bottom of the first mounting groove (41) by ceramic matrix composite screws.

[0023] Furthermore, the plug, pad, cap, flexible heat insulation pad, and head cover are all ceramic matrix composite materials resistant to high temperatures above 1600°C; the ceramic matrix composite pins and ceramic matrix composite screws are all ceramic matrix composite materials resistant to high temperatures above 1600°C.

[0024] Furthermore, the columnar boss is a hollow structure; the bottom surface of the pad is provided with an annular step structure around the first threaded hole, and the lower outer diameter of the annular step structure is smaller than the upper outer diameter.

[0025] Compared with the prior art, the advantages of the present invention are as follows:

[0026] 1. The present invention provides a nose sealing and protection component for an aircraft. The heat sealing component is located on the end face outside the connection channel between the nose of the aircraft body and the nose cone. It is quick and flexible to disassemble. The pad is fixed to the upper end face of the nose cone by riveting, which greatly increases the stability of the sealing component and also has a positioning function. When the metal connector needs to be disassembled or installed, only the plug needs to be removed for operation. The present invention has a simple and compact structure and high heat sealing reliability.

[0027] 2. The present invention provides a nose sealing and protection component for aircraft. The pad has six equally divided threaded holes that can cooperate with the plug to prevent loosening. Combined with high-temperature anti-loosening adhesive, it greatly eliminates the form and position error of the plug and pad after CVI, and controls the maximum error to 0.15mm, which greatly improves the heat sealing performance.

[0028] 3. The present invention provides a nose sealing and protection component for an aircraft. The cover is connected to the nose cone by means of ceramic matrix composite screws and ceramic matrix composite pins, forming a stepped fit gap with the nose cone, which greatly guides and decomposes the heat flow, forming heat insulation protection. The plug and the pad also form a stepped fit gap, which diverts the heat flow in a Z-shaped manner, forming heat insulation protection for the internal metal connectors connected to the fuselage, greatly increasing the high temperature resistance of the aircraft.

[0029] 4. The present invention provides a nose sealing and protection component for aircraft, which is composed of a flexible heat insulation pad, a rigid heat insulation pad, a plug, and a pad to ensure its heat sealing performance. The rigid heat insulation pad not only plays a heat insulation role, but also has a slot for installing the pad to ensure the accurate positioning of the pad. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the structure of an embodiment of a nose sealing and protection component for an aircraft according to the present invention (showing the nose of the aircraft body);

[0031] Figure 2 This is an exploded view of an embodiment of a nose sealing and protection component for an aircraft according to the present invention;

[0032] Figure 3 This is a schematic diagram of the plug structure in an embodiment of the nose sealing and protection component for aircraft of the present invention;

[0033] Figure 4 This is a schematic diagram of the structure of the pad (lower end face side) in an embodiment of a nose sealing and protection component for aircraft according to the present invention;

[0034] Figure 5 This is a schematic diagram of the structure of the pad (upper end face) in an embodiment of the nose sealing and protection component for aircraft of the present invention;

[0035] Figure 6 This is a schematic diagram (upper end face) of the rigid heat insulation pad in an embodiment of the aircraft head sealing protection component of the present invention;

[0036] Figure 7 This is a schematic diagram (lower end face) of the rigid heat insulation pad in an embodiment of the aircraft head sealing and protection component of the present invention.

[0037] Figure 8 This is a schematic diagram of the head cover structure in an embodiment of the head sealing and protection component for aircraft of the present invention;

[0038] Figure 9 This is a schematic diagram of the structure of the opening cover in an embodiment of the nose sealing and protection component for an aircraft according to the present invention;

[0039] Figure 10 This is a schematic diagram of the structure of a flexible heat insulation pad in an embodiment of a nose sealing and protection component for an aircraft according to the present invention;

[0040] Figure 11 This is a heat flow diagram (arrows indicate heat flow direction) during flight of an embodiment of the aircraft head sealing protection component of the present invention;

[0041] Figure label:

[0042] 1-Plug, 11-Columnar boss, 12-Plug cap, 13-Plug cap threaded hole; 2-Pan block, 21-Anti-loosening positioning threaded hole, 22-First threaded hole, 23-First slot, 24-Pin riveting hole; 3-Cap; 31-Screw connection hole, 33-Second round hole; 32-Pin riveting hole; 4-Head cover, 41-First mounting groove, 42-Second mounting groove, 43-Second threaded hole; 5-Flexible heat insulation pad, 51-Third round hole; 6-Rigid heat insulation pad; 61-Second slot, 62-First round hole; 7-Aircraft fuselage nose. Detailed Implementation

[0043] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0044] This invention provides a nose sealing and protection component for aircraft, such as... Figure 1 and Figure 2 As shown, the invention includes a nose cone 4 for protecting the nose of the aircraft, a metal connector connecting the nose cone 4 and the nose of the aircraft, and a heat-sealing assembly detachably mounted on the upper surface of the nose cone 4. The heat-sealing assembly includes a plug 1, a pad 2, a cap 3, a flexible heat-insulating pad 5, a high-temperature anti-loosening adhesive, and a rigid heat-insulating pad 6. As a sealing assembly protecting the nose of the aircraft, it must operate in a high-temperature environment and requires extremely high heat-sealing performance. Therefore, the plug 1, pad 2, cap 3, nose cone 4, and flexible heat-insulating pad 5 are all ceramic matrix composite materials resistant to temperatures above 1600°C. The ceramic matrix composite pins and screws used in the connection of this invention are also ceramic matrix composite materials resistant to temperatures above 1600°C.

[0045] The structure of plug 1 is as follows Figure 3 As shown, the plug 1 includes a plug cap 12 and a columnar boss 11 located in the middle of the bottom surface of the plug cap 12. The outer surface of the columnar boss 11 is provided with external threads, and the columnar boss 11 is a hollow structure. The structure of the pad block 2 is as follows. Figure 4 and Figure 5As shown, the upper end face of the pad 2 is provided with a first groove 23 whose inner diameter matches the outer diameter of the plug cap 12, and the middle is provided with a first threaded hole 22 that mates with the external thread. The columnar boss 11 of the plug 1 is inserted into the first threaded hole 22 through a threaded connection. After being inserted into place, the bottom surface of the plug cap 12 contacts the bottom of the groove 23, and the outer wall of the plug cap 12 fits against the groove wall of the first groove 23. The pad 2 and the plug cap 12 are connected by high-temperature ceramic matrix composite screws, and the pad 2 and the head cover 4 are riveted by high-temperature ceramic matrix composite pins. To further ensure the sealing, after the plug 1 and the pad 2 are connected and installed, high-temperature anti-loosening adhesive is used to further reinforce and seal the connection between the plug 1 and the pad 2. The spacer 2 has six equally spaced threaded holes in its first slot 23. These six equally spaced threaded holes are six anti-loosening positioning threaded holes 21 arranged circumferentially in the first slot 23. The spacer 2 and the plug 1 are connected to the six equally spaced threaded holes by ceramic matrix composite screws, and the distance between adjacent anti-loosening positioning threaded holes 21 is 1mm. Since the composite material needs to undergo multiple CVI depositions before the finished product, there is a deviation when the plug 1 and the spacer 2 are connected. The pitch of the plug 1 is set to 1mm. After the plug 1 is pre-tightened, the plug cap threaded hole 13 on the plug 1 is connected to the nearest anti-loosening positioning threaded hole 21 of the spacer 2 by a ceramic matrix composite screw. Then, high-temperature anti-loosening adhesive is used to fill the space between the columnar boss 11 of the plug 1 and the first threaded hole 22, so that the axial error is controlled to a maximum of 0.15mm. In addition, the bottom surface of the spacer 2 is set as an annular step structure around the first threaded hole 22. The outer diameter of the lower end of the annular step structure is smaller than the outer diameter of the upper end, which helps to reduce the overall weight.

[0046] The structure of the rigid heat insulation pad 6 is as follows Figure 6 and Figure 7 As shown, a first circular hole 62 is provided in the middle of the rigid heat insulation pad 6, and a second groove 61 with an inner diameter that matches the outer diameter of the pad block 2 is provided on the upper end surface of the rigid heat insulation pad 6. The pad block 2 is riveted to the second groove 61 by a ceramic matrix composite material pin passing through the pin riveting hole 24, and the bottom surface of the pad block 2 is in contact with the bottom of the groove of the second groove 61, and the outer side wall of the pad block 2 is in contact with the groove wall of the second groove 61; the bottom end of the columnar boss 11 passes through the first threaded hole 22 and maintains a distance of 1.5mm from the bottom of the groove of the second groove 61.

[0047] The structure of headgear 4 is as follows Figure 8As shown, the upper surface of the head cover 4 is provided with a first mounting groove 41 that matches the size of the rigid heat insulation pad 6, a second threaded hole 43, and a second mounting groove 42 that matches the size of the cover 3. The first mounting groove 41 is located inside the second mounting groove 42, and the two form a stepped structure. The second threaded hole 43 is located inside the first mounting groove 41 and is used to connect the aircraft head 7 to the metal connector. In this embodiment, the metal connector is a hexagonal screw. The rigid heat insulation pad 6 is installed and fixed in the first mounting groove 41 by ceramic matrix composite screws, and the bottom surface of the rigid heat insulation pad 6 is in contact with the bottom of the first mounting groove 41, and the outer side wall of the rigid heat insulation pad 6 is in contact with the groove wall of the first mounting groove 41. The first threaded hole 22 and the first round hole 62 are both provided corresponding to the second threaded hole 43 for the installation and removal of the metal connector.

[0048] The cover 3 is riveted into the second mounting groove 42 by multiple ceramic matrix composite pins and multiple ceramic matrix composite screws. This prevents deformation of the head cover 4 and further ensures a tight seal. During installation, ensure that the contact surfaces on each side fit together to prevent gaps. After installation, the multiple ceramic matrix composite pins and multiple ceramic matrix composite screws are arranged circumferentially, with the multiple ceramic matrix composite pins located around the multiple ceramic matrix composite screws. The corresponding screw connection holes 31 and pin riveting holes 32 on the cover 3 are arranged as follows: Figure 9 As shown. The structure of the cover 3 is as follows. Figure 9 As shown, the cap 3 has a second round hole 33 with an inner diameter that matches the outer diameter of the plug cap 12. During installation, the bottom end of the columnar boss 11 passes through the second round hole 33 and connects with the first threaded hole 22. After installation, the plug 1 is screwed into the pad 2, and all contact surfaces fit tightly to ensure good sealing. At the same time, the upper end face of the plug cap 12 is flush with the upper end face of the cap 3, the upper end face of the pad 2 fits with the lower end face of the cap 3, and the inner wall of the first groove 23 of the pad 2 fits tightly with the outer wall of the lower part of the plug cap 12 to ensure the sealing of the structure. In order to further improve the sealing, the cap 3 is placed on the upper side of the pad 2 and fitted onto the plug cap 12, so that the inner wall of the second round hole 33 of the cap 3 fits tightly with the upper part of the outer wall of the plug cap 12. After installing the plug 1, install the flexible insulation pad 5. To eliminate the space between the pad 2 and the composite head protection mechanism, install it around the pad 2, located on the upper surface of the rigid insulation pad 6, and tightly fit with the end face of the pad 21. The structure of the flexible insulation pad 5 is as follows: Figure 10As shown, the flexible heat insulation pad 5 is provided with a third circular hole 51 whose inner diameter matches the outer diameter of the pad block 2. The flexible heat insulation pad 5 is fitted around the pad block 2 through the third circular hole 51. The outer wall of the upper part of the pad block 2 is in contact with the inner wall of the third circular hole 51, and the outer wall of the lower part of the pad block 2 is in contact with the groove wall of the second slot 61. The upper end face of the flexible heat insulation pad 5 is connected to the lower end face of the cover 3 by screws. The flexible heat insulation pad 5 and the rigid heat insulation pad 6 can not only play the role of heat insulation, but also double confirm the sealing of the structure. At the same time, the rigid heat insulation pad 6 is designed with a second slot 61 for the installation of the pad block 2, which can quickly and accurately position and install the pad block 2.

[0049] In traditional structures, the ceramic composite head protection component is integrally molded using CVI. During installation, disassembly, or maintenance, the entire head protection component must be installed or removed as a whole, requiring a large operating space, all concentrated between the head protection component and the aircraft fuselage, resulting in complex connections and difficult installation. In contrast, the structure of this invention designs the head cover and heat-sealing assembly within the head protection component as detachable, allowing for step-by-step installation, simplifying operation. Furthermore, when installing the heat-sealing assembly, the operating space is located above the head cover, providing ample space for easy operation. During maintenance, it is not necessary to remove the entire head protection component; only the plug 1 needs to be removed to install or remove the metal connectors connecting the head cover and the aircraft fuselage. In this invention, the plug 1, pad 2, cap 3, head cover 4, and flexible heat insulation pad 5 are all made of ultra-high temperature ceramic matrix composite material, achieving high-temperature resistance. The use of a large cap and plug sealing method ensures sufficient space for installing the metal connecting mechanism (metal connectors), while the installation of the plug 1 ensures flexibility in disassembly.

[0050] The heat flow distribution diagram of the nose protection component for aircraft of this invention during flight is shown in the figure below. Figure 11 As shown, after the structure of this invention is installed with the nose of the aircraft body, it can form a stepped fit gap during use, which greatly guides and decomposes the heat flow, forming heat insulation protection. The plug 1 and the pad 2 also form a stepped fit gap, which diverts the heat flow in a Z-shape, forming heat insulation protection for the nose of the aircraft body and the internal metal connecting parts, greatly increasing the high temperature resistance of the aircraft.

Claims

1. A nose sealing and protective component for an aircraft, comprising a nose cone (4) for protecting the nose (7) of the aircraft fuselage and a metal connector connecting the nose cone (4) and the nose (7) of the aircraft fuselage, characterized in that: It also includes a heat-sealing assembly that can be detachably mounted on the upper surface of the headgear (4); The heat-sealing assembly includes a plug (1), a pad (2), and a rigid heat insulation pad (6); The plug (1) includes a plug cap (12) and a columnar boss (11) located in the middle of the bottom surface of the plug cap (12), and the outer surface of the columnar boss (11) is provided with external threads; The upper end face of the pad (2) is provided with a first groove (23) whose inner diameter is adapted to the outer diameter of the plug cap (12), and the middle part is provided with a first threaded hole (22) that matches the external thread of the columnar boss (11); The columnar boss (11) is inserted into the first threaded hole (22) by a threaded connection, and the bottom surface of the plug cap (12) is in contact with the bottom of the first slot (23), and the outer side wall of the plug cap (12) is in contact with the slot wall of the first slot (23); The rigid heat insulation pad (6) has a first round hole (62) in the middle and a second slot (61) with an inner diameter that matches the outer diameter of the pad block (2) on the upper end face of the rigid heat insulation pad (6). The pad (2) is disposed in the second slot (61), and the bottom surface of the pad (2) is in contact with the bottom of the second slot (61), and the outer side wall of the pad (2) is in contact with the wall of the second slot (61). The upper end face of the head cover (4) is provided with a first mounting groove (41) and a second threaded hole (43). The second threaded hole (43) is located in the first mounting groove (41) and is used to connect the head of the aircraft body (7) through a metal connector. The rigid heat insulation pad (6) is disposed in the first mounting groove (41), and the bottom surface of the rigid heat insulation pad (6) is in contact with the bottom of the first mounting groove (41), and the outer side wall of the rigid heat insulation pad (6) is in contact with the groove wall of the first mounting groove (41); the first threaded hole (22) and the first round hole (62) are respectively disposed with the second threaded hole (43) for the installation and disassembly of the metal connector; The plug (1), pad (2) and head cover (4) are all ceramic matrix composite materials.

2. The nose sealing and protection component for an aircraft according to claim 1, characterized in that: The heat-sealing assembly also includes a cover (3); The cap (3) is provided with a second round hole (33) whose inner diameter is adapted to the outer diameter of the plug cap (12). The bottom end of the columnar boss (11) passes through the second round hole (33) and is connected to the first threaded hole (22). The upper end face of the plug cap (12) is flush with the upper end face of the cap (3), and the upper end face of the pad (2) is in contact with the lower end face of the cap (3). The head cover (4) is provided with a second mounting groove (42) whose size is adapted to the mouth cover (3), the first mounting groove (41) is located in the second mounting groove (42), and the two form a stepped structure; The cover (3) is disposed in the second mounting groove (42).

3. The nose sealing and protection component for an aircraft according to claim 2, characterized in that: The heat-sealing assembly also includes a flexible heat-insulating pad (5) disposed on the upper surface of the rigid heat-insulating pad (6); The flexible heat insulation pad (5) is provided with a third circular hole (51) whose inner diameter is adapted to the outer diameter of the pad block (2). The flexible heat insulation pad (5) is fitted around the pad block (2) through the third circular hole (51). The outer wall of the upper part of the pad block (2) is in contact with the inner wall of the third circular hole (51), and the outer wall of the lower part is in contact with the groove wall of the second slot (61). The upper end face of the flexible heat insulation pad (5) is connected to the lower end face of the cap (3).

4. The nose sealing and protection component for an aircraft according to claim 3, characterized in that: The cap (3) is made of ceramic matrix composite material; The flexible heat insulation pad (5) is a ceramic-based composite material.

5. The nose sealing and protection component for an aircraft according to claim 4, characterized in that: The pad (2) and the cap (12) are connected by ceramic matrix composite screws, and the pad (2) and the head cover (4) are riveted by ceramic matrix composite pins.

6. The nose sealing and protection component for an aircraft according to claim 5, characterized in that: The heat-sealing assembly also includes high-temperature anti-loosening adhesive; High-temperature anti-loosening adhesive is filled between the columnar boss (11) and the first threaded hole (22) of the plug (1).

7. The nose sealing and protection component for an aircraft according to claim 6, characterized in that: The first slot (23) of the pad (2) is provided with six equally divided threaded holes. The pad (2) and the plug (1) are connected to the six equally divided threaded holes by ceramic matrix composite screws, and the distance between adjacent threaded holes is 1mm.

8. The nose sealing and protection component for an aircraft according to claim 7, characterized in that: The cap (3) is riveted to the second mounting groove (42) by ceramic matrix composite screws and ceramic matrix composite pins; The pad (2) is riveted to the rigid heat insulation pad (6) by ceramic matrix composite pins; The rigid heat insulation pad (6) is connected to the bottom of the first mounting groove (41) by ceramic matrix composite screws.

9. The nose sealing and protection component for an aircraft according to claim 8, characterized in that: The plug (1), pad (2), cap (3), flexible heat insulation pad (5) and head cover (4) are all ceramic matrix composite materials resistant to high temperatures above 1600°C; The ceramic matrix composite pins and ceramic matrix composite screws are both ceramic matrix composite materials resistant to high temperatures above 1600°C.

10. A nose sealing and protective component for an aircraft according to any one of claims 1-9, characterized in that: The columnar boss (11) is a hollow structure; The bottom surface of the pad (2) is provided with an annular step structure around the first threaded hole (22), and the lower outer diameter of the annular step structure is smaller than the upper outer diameter.

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