Rapidly-inserted heat insulation tile assembly and preparation and installation method thereof

Abstract

The invention relates to the field of heat insulation materials, in particular to a quick-plug-in heat insulation tile assembly and a preparation and installation method thereof, and the quick-plug-in heat insulation tile assembly comprises a plug-in structure which is used for quickly fixing a heat insulation tile to a skin / aircraft shell through mechanical connection. A threaded hole with an opening perpendicular to the skin is formed in the end, in butt joint with the skin, of the inserting structure, and a rotatable T-shaped inserting structure is arranged on the heat insulation tile structure. And the positioning block can be movably inserted into or separated from the free stroke of the inserting piece. The free path of the plug-in is limited through the positioning hole, the stability and the structural strength of plug-in connection of the plug-in and the bayonet can be effectively improved, and the installation space is reduced to the maximum extent due to the design of the movable plug-in. The inserting structure can achieve standardized design and manufacturing, the installation time of a single heat insulation tile is smaller than or equal to 2 min, the assembly damage load is 20-850 N, rapid installation and replacement of the heat insulation tile can be achieved, the installation and maintenance efficiency is greatly improved, and the inserting structure is an important development direction for achieving rapid assembly of the heat insulation tile in the future.

Description

Technical Field

[0001] The invention relates to a quick-plug heat-insulating tile assembly design and a preparation and installation method thereof, and belongs to the field of heat protection materials. Background Art

[0002] During the use of aerospace vehicles, after a long period of aerodynamic heating, the surface temperature reaches thousands of degrees. The thermal protection system not only plays a role in thermal protection, but is also the most important component of the aerodynamic shape. Its assembly quality directly affects the safety and flight performance of the aircraft. Its harsh service environment also puts forward requirements for thermal protection systems such as heat insulation and anti-scouring. In addition, in order to reduce costs, most aerospace vehicles also put forward the need for reuse, which also puts forward clear requirements for the reusability of thermal protection systems.

[0003] Ceramic thermal insulation tiles have attracted much attention as early as the 1880s for their good thermal insulation and mechanical properties. They were successfully used as thermal protection materials for space shuttles in the United States. Ceramic thermal insulation tiles are used on the windward side of the fuselage, ailerons and body flaps, etc. The application temperature range is 650-1250℃, which meets the thermal protection requirements of large areas and other parts, and realizes the safe return and reusability of the space shuttle. There are more than 24,300 ceramic thermal insulation tiles on the US space shuttle. Ceramic thermal insulation tiles are usually bonded to the fuselage skin using cured silicone, covering more than 70% of the entire outer surface of the aircraft, but these materials or thermal protection systems have high preparation and maintenance costs, long cycles, and low reliability. In addition, the thermal expansion coefficients of ceramic thermal insulation tiles and aluminum alloys are very different, and the temperature difference between the two is also very large during re-entry, so a suitable gap must be left between the thermal insulation tiles, and the connection layer between the ceramic thermal insulation tiles and the fuselage skin must also have greater elasticity to coordinate the deformation of the two. There is a certain step difference between the outer surfaces of the thermal insulation tiles due to manufacturing and assembly errors. The existence of gap deviation and step difference has a certain impact on the performance of the thermal protection system. For the assembly of this special object, since it involves key research and development technologies, there is little content related to the assembly process of thermal insulation tiles in the publicly published literature. The few graphic materials show that the assembly of thermal insulation tiles is mainly manual, and digital measurement equipment is used as an auxiliary tool for assembly quality inspection.

[0004] NASP has designed a parasitic multi-layer panel structure. The surface layer can be designed as an anti-oxidation C / C composite panel or a titanium alloy composite material (TMC) panel that can withstand high temperatures according to different temperature zones; the subsurface layer is a space shuttle ceramic insulation tile, which has good temperature resistance and excellent thermal insulation performance. Most of the lower surface and side areas of the Soviet Buran space shuttle fuselage are high-temperature areas generated by aerodynamic heat loads, with temperatures ranging from 700 to 1250°C. The thermal protection system uses ceramic tile insulation materials. The bonding process of the insulation tile is similar to that of the space shuttle, using an adhesive process. Japan's HOPE reusable aircraft mainly uses an adhesive solution to connect its insulation materials to the cold structure. The windward surface of the US X-37B fuselage uses BRI rigid ceramic tiles on a large area, and the rigid insulation tiles also use an adhesive solution similar to that of the space shuttle.

[0005] Many domestic material units have successively carried out the research and development of rigid thermal insulation tile materials and the application evaluation work. The windward surface of a series of aircraft has been largely selected with ceramic thermal insulation tile solutions and cover plate combination solutions. Most of the thermal insulation tiles use a similar adhesive solution as the space shuttle, and the other part is mechanically connected to the skin through components.

[0006] Based on the above examples, the connection scheme between ceramic insulation tiles and fuselage skin is mainly based on bonding; another scheme is that the insulation tile is a component of the cover-type component, and is connected to the fuselage skin together with the cover structure through a mechanical connection structure.

[0007] When installing rigid insulation tiles by gluing, the glue layer needs time to cure during the installation process, and the glue layer and other residues need to be cleaned when replacing. This is not only time-consuming, but also easy to scratch the surrounding insulation tiles when replacing and cleaning. The installation and replacement cycle is long. Summary of the invention

[0008] The technical problem solved by the present application is: to overcome the deficiencies of the prior art, to provide a quick-plug thermal insulation tile assembly and a preparation method thereof, to achieve rapid assembly of the thermal insulation tiles, and to greatly improve installation and maintenance efficiency.

[0009] This patent does not use bonding structure, but designs a special quick-plug metal structure to quickly connect the thermal insulation tile to the fuselage skin. Through standardized structural design and universal installation, the rapid assembly of thermal insulation tiles is achieved, and the installation and maintenance efficiency is greatly improved, which is the future development trend of thermal insulation tiles.

[0010] The technical solutions provided by this application are as follows:

[0011] In the first aspect, a quick-plug thermal insulation tile assembly is provided, including a ceramic thermal insulation tile and a plug-in structure, wherein a T-shaped slot is provided on one surface of the ceramic thermal insulation tile; the plug-in structure includes a fixing column, a supporting plate and a nut, wherein the supporting plate is fixedly connected to the end of the fixing column, a through hole is provided in the aircraft shell, the supporting plate is clamped in the T-shaped slot, the fixing column extends from the T-shaped slot and passes through the through hole, and the nut is threadedly connected to the end of the fixing column passing through the through hole.

[0012] The plug-in structure also includes a positioning block, which is fixedly connected to one side of the fixing column. The aircraft shell is provided with a positioning hole, which is communicated with the through hole, and the positioning hole cooperates with the positioning block.

[0013] The surface of the ceramic thermal insulation tile with the T-shaped groove facing the aircraft shell is the mounting surface, and the length of the T-shaped groove starts from one end of the mounting surface and extends from the other end to the middle of the mounting surface.

[0014] The installation surface of the ceramic insulation tile is provided with a locking groove, which is located on one side of the T-shaped groove along the length direction of the T-shaped groove, so that after the plug-in structure moves along the open end of the T-shaped groove to the middle of the installation surface, the positioning block is just locked in the locking groove.

[0015] A flexible heat insulation component is arranged between the ceramic heat insulation tile and the aircraft shell.

[0016] The flexible thermal insulation component comprises multiple layers of thermal insulation material, and the thermal insulation material is ceramic fiber wool, ceramic fiber felt and / or ceramic fiber paper.

[0017] In a second aspect, a method for preparing and installing a quick-plug thermal insulation tile assembly is provided, comprising:

[0018] Process the ceramic insulation tiles according to the designed dimensions and process T-shaped grooves on the installation surface of the ceramic insulation tiles;

[0019] Process the plug-in structure according to the designed dimensions;

[0020] Cutting flexible insulation materials;

[0021] Align the T-slot end of the ceramic insulation tile with the support piece of the plug-in structure and insert it. When the support piece is inserted to the right depth in the T-slot, rotate the ceramic insulation tile until the positioning block on the plug-in structure engages with the positioning slot on the insulation tile.

[0022] The flexible heat-insulating material is laid on the surface of the aircraft shell, the ceramic heat-insulating tile with the plug-in structure is passed through the through hole on the shell, and the positioning block is passed through the positioning hole, and the nut is threadedly connected to the end of the fixing column and tightened.

[0023] In summary, this application at least includes the following beneficial technical effects:

[0024] 1. Since the thermal insulation tile is a porous structure (with a porosity of more than 80wt%), it is very easy to fail when hit by sharp objects. In the present invention, a "T" structure is designed on the thermal insulation tile structure for the plug-in structure to rotate, and the plug-in structure is connected to the thermal insulation tile in a surface contact manner without damaging the thermal insulation tile material.

[0025] 2. Carry out standardized and universal design of thermal insulation tile primitives and plug-in structures to form standardized thermal insulation tile component units, which can reduce the time of searching and identifying a single tile, thereby reducing installation time;

[0026] 3. The method of all mechanical plug-in is used to replace the bonding method. There is no need for curing time. When replacing, there is no need to clean the glue layer and other residues. It can achieve fast installation and replacement, which can further shorten the installation time;

[0027] 4. After the positioning grooves, positioning blocks and skins on the thermal insulation tiles are installed, the three will restrain each other to fix the position. Unless the tile itself is damaged, its installation position will not change, and the installation reliability is high. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 A schematic diagram of the structure of the plug-in structure;

[0029] Figure 2 Schematic diagram of the structure of ceramic insulation tiles with T-shaped grooves;

[0030] Figure 3 Schematic diagram of the structure of the skin / aircraft shell;

[0031] Figure 4 Schematic diagram of the structure of the insulation component.

[0032] Description of the numbers in the attached figures: 1. Insulation tile; 11. T-shaped slot; 12. Clamping slot;

[0033] 2. Plug-in structure; 21. Fixing column; 22. Support sheet; 23. Nut; 24. Positioning block;

[0034] 3. Aircraft shell; 31. Through hole; 32. Positioning hole;

[0035] 4. Thermal insulation components. DETAILED DESCRIPTION

[0036] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments disclosed in the present invention will be further described in detail below with reference to the accompanying drawings.

[0037] The present application embodiment discloses a design concept of a quick-plug thermal insulation tile assembly as follows:

[0038] 1. Plug-in structure design

[0039] like Figure 1 As shown, the plug-in structure 2 is used to quickly connect and fix the thermal insulation tile to the aircraft shell 3, so the plug-in structure 2 needs good toughness and strength. The free travel of the plug-in is limited by the positioning hole 32, which can effectively improve the stability and structural strength of the plug-in and the bayonet plug-in, and the movable plug-in design can minimize the installation space and achieve rapid installation and removal. In addition, the use of a unified structural standardized design can also achieve universal installation, further improving installation efficiency.

[0040] 2. Connection method between plug-in structure and ceramic insulation tile

[0041] like Figure 2 As shown, since the thermal insulation tile is a porous structure (with a porosity of up to 80wt% or more), it is very easy to fail when hit by sharp objects, so it is necessary to fully consider the connection method between the metal plug structure 2 and the thermal insulation tile 1. The basic design principle is that the plug structure 2 cannot be directly connected to the thermal insulation tile 1 in a sharp shape. The design of the present invention adopts a surface contact method to connect the plug structure 2 to the thermal insulation tile 1. A "T" structure is provided on the thermal insulation tile 1 structure to allow the plug structure 2 to rotate. Surface contact is used when the plug structure 2 is rotated and positioned, so as not to damage the thermal insulation tile 1 material;

[0042] 3. Thermal insulation tile component design and rapid assembly

[0043] like Figure 2 and Figure 3 As shown, the standardized and universal design of the heat insulation tile unit and the plug-in structure 2 is carried out to form a standardized heat insulation tile assembly unit, which can reduce the time of searching and identifying a single tile, thereby reducing the installation time; in addition, the use of a full mechanical plug-in method instead of a bonding method does not require curing time, and does not require cleaning of the adhesive layer and other residues during replacement, which can achieve rapid installation and replacement, and can further shorten the installation time. The design of the present invention uses multiple layers of heat insulation materials to form a heat insulation assembly, and the metal plug-in structure 2 is used to instantly insert the multi-layer heat insulation assembly and connect it to the aircraft shell 3, so as to achieve the purpose of rapid installation.

[0044] The present application embodiment discloses a quick-connect insulation tile assembly, such as Figure 4 As shown, it comprises a ceramic thermal insulation tile 1, a plug-in structure 2 and a flexible thermal insulation material (ceramic fiber wool, ceramic fiber felt and / or ceramic fiber paper are used in this embodiment), wherein the ceramic thermal insulation tile 1 is installed on the outer surface of the aircraft shell 3 through the plug-in structure 2, and the flexible thermal insulation material plays a buffering role between the rigid aircraft shell 3 and the ceramic thermal insulation tile 1. The specific preparation steps are:

[0045] Step 1: Process the ceramic heat insulation tile 1 according to the designed digital model size, and process the T-shaped groove 11 on the installation surface of the ceramic heat insulation tile 1 to obtain a "T"-shaped opening structure on the side, and process the positioning groove 12 on the installation surface of the ceramic heat insulation tile 1. Figure 2 as shown

[0046] Step 2: Process the plug-in structure 2 according to the designed digital model dimensions to obtain a plug-in structure 2 similar to the shape of "down", as Figure 1 shown. The plug-in structure 2 includes a fixed column 21, a support piece 22 and a positioning block 24. The positioning block 24 is fixedly connected to the side surface of the fixed column 21, the support piece 22 is fixedly connected to one end of the fixed column 21, the support piece 22 cooperates with the T-shaped groove 11, and the fixed column 21 is used to pass through the through hole 31 of the aircraft shell 3.

[0047] Step 3: Process a through hole 31 and a positioning hole 32 on the surface of the aircraft shell 3 according to the designed digital model dimensions; the through hole 31 cooperates with the fixed column 21 for the fixed column 21 to pass through, and the positioning hole 32 cooperates with the positioning block 24 so that the rotation of the fixed column 21 drives the positioning block 24 to rotate together. When the positioning block 24 is aligned with the positioning hole 32, insert the positioning block 24 into the positioning hole 32. At this time, the fixed column 21 and the aircraft surface cannot rotate relative to each other. As Figure 3 shown

[0048] Step 4: Cut ceramic fiber cotton, ceramic fiber felt and / or ceramic fiber paper with the same size as the aircraft shell 3.

[0049] Step 5: Align the end of the T-shaped groove 11 of the ceramic heat insulation tile 1 with the support piece 22 of the plug-in structure 2 and quickly insert it. When the insertion depth of the support piece 22 in the T-shaped groove 11 is in place, rotate the ceramic heat insulation tile 1 until the positioning block 24 on the plug-in structure 2 is buckled with the clamping groove on the heat insulation tile.

[0050] Step 6: Combine the materials obtained in Step 2, Step 3, Step 4 and Step 5; that is, lay the flexible heat insulation material on the surface of the aircraft shell 3, pass the plug-in structure 2 through the through hole 31 on the shell, and make the positioning block 24 pass through the positioning hole 32, and use a nut 23 to be threadedly connected to the end of the fixed column 21. Finally, tighten the nut 23, and the rapid installation of the component is completed.

[0051] Embodiment 1:

[0052] A kind of rapid plug-in heat insulation tile assembly described in the present invention specifically includes:

[0053] (1) Ceramic heat insulation tile, with dimensions of 50mm×50mm×60mm. Process a "T" structure on the side surface, where the size of the "one" character is 29mm×33mm×3.5mm; the size of the "vertical bar" is 24.5mm×8.5mm×9.5mm; process a positioning hole with dimensions of 2.5mm×2mm×1.5mm on the contact surface between the heat insulation tile and the aircraft shell.

[0054] (2) The plug-in structure is similar to the character "下" and is entirely made of stainless steel. Among them, the "-" is a support piece with dimensions of 24 mm × 8 mm × 3 mm; the upper end of the "丨" is a guide post with a diameter of Φ5 mm and a length of 15 mm; the lower end of the "丨" is a fixing post machined according to the standard M4 screw rod, with a height of ~5 mm; the "、" is a positioning block, the upper end of which is 9 mm away from the support piece, with dimensions of 6 mm × 2 mm × 1.5 mm;

[0055] (3) The aircraft shell. In this embodiment, a local structure of the aircraft shell is used for simulation. The dimensions of the local structure of the aircraft shell are 50 mm × 50 mm × 5 mm, which includes a Φ5 mm through hole and a positioning through hole of 2 mm × 2.5 mm × 5 mm.

[0056] Process (1), (2), and (3) separately. Cut ceramic fiber cotton / felt / paper with the same dimensions as the local structure of the aircraft shell. After completion, quickly insert the support piece of the (2) plug-in structure in the direction of the processing surface of the ceramic heat insulation tile. When the depth of the guide post is in place, rotate the plug-in structure until the positioning block on the plug-in structure is buckled with the clamping groove on the ceramic heat insulation tile. Then, insert the fixing post at the bottom end of the plug-in structure into the single-layer zirconia fiber paper (with a thickness of ~0.7 mm) and the local structure of the aircraft shell respectively. Here, it is necessary to buckle the positioning block with the positioning hole on the local structure of the aircraft shell. Finally, tighten the nut with the fixing post on the back of the local structure of the aircraft shell to complete the installation of the component. The installation time of the component is 1.2 min, and the failure load of the tested component is 440 N.

[0057] Embodiment 2:

[0058] The quick plug-in heat insulation tile component described in the present invention specifically includes:

[0059] (1) The ceramic heat insulation tile has dimensions of 50 mm × 50 mm × 60 mm. A "T" character structure is machined on the side, where the "-" character has dimensions of 19 mm × 33 mm × 3.5 mm; the "丨" character has dimensions of 8.5 mm × 25.5 mm × 9.5 mm; a positioning hole with dimensions of 2.5 mm × 2 mm × 1.5 mm is machined on the contact surface between the heat insulation tile and the aircraft shell.

[0060] (2) The plug-in structure is similar to the character "下" and is entirely made of stainless steel. Among them, the "-" is a support piece with dimensions of 14 mm × 8 mm × 3 mm; the upper end of the "丨" is a guide post with a diameter of Φ5 mm and a length of 15 mm; the lower end of the "丨" is a fixing post machined according to the standard M4 screw rod, with a height of ~5 mm; the "、" is a positioning block, the upper end of which is 9 mm away from the support piece, with dimensions of 6 mm × 2 mm × 1.5 mm;

[0061] (3) Aircraft hull. In this embodiment, a local structure of the aircraft hull is used for simulation, and the size of the local structure of the aircraft hull is 50 mm × 50 mm × 5 mm, including a Φ5 mm through hole and a positioning through hole of 2 mm × 2.5 mm × 5 mm.

[0062] Process (1), (2), and (3) separately. Cut ceramic fiber cotton / felt / paper with the same size as the local structure of the aircraft hull. After completion, quickly insert the support piece of the (2) plug-in structure in the direction aligned with the processing surface of the ceramic heat insulation tile. When the depth of the guide post is in place, rotate the plug-in structure until the positioning block on the plug-in structure is buckled with the positioning hole on the ceramic heat insulation tile. Then, insert the fixed columns at the bottom of the plug-in structure into 3 layers of quartz fiber cloth (with a thickness of about 0.6 mm) and the local structure of the aircraft hull respectively. Here, the positioning block needs to be buckled with the positioning hole on the local structure of the aircraft hull. Finally, tighten the nut with the fixed column on the back of the local structure of the aircraft hull to complete the installation of the component. The installation time of the component is 1.2 min, and the failure load of the tested component is 250 N.

[0063] Example 3:

[0064] The quick-insert heat insulation tile assembly described in the present invention specifically includes:

[0065] (1) Ceramic heat insulation tile, with a size of 50 mm × 50 mm × 80 mm. Process a "T" structure on the side, where the size of the "—" is 30 mm × 35 mm × 5.5 mm; the size of the "丨" is 25.5 mm × 15.5 mm × 34.5 mm; process a positioning hole with a size of 3.5 mm × 3.5 mm × 3.0 mm on the contact surface between the heat insulation tile and the aircraft hull.

[0066] (2) Plug-in structure, similar to the "下" character structure, all made of stainless steel. Among them, the "—" is the support piece, with a size of 25 mm × 15 mm × 5 mm; the upper end of the "丨" is the guide post, with a diameter of Φ5 mm and a length of 40 mm; the lower end of the "丨" is the fixed column, processed according to the standard M4 screw rod, with a height of about 5 mm; the "、" is the positioning block, the distance from its upper end to the support piece is 32 mm, and the size is 8 mm × 3 mm × 3 mm;

[0067] (3) Aircraft hull, with a size of 50 mm × 50 mm × 5 mm, including a Φ5 mm through hole and a positioning through hole of 3.5 mm × 3.5 mm × 5 mm.

[0068] Process (1), (2), and (3) separately. Cut ceramic fiber cotton / felt / paper with the same size as the local structure of the aircraft shell. After completion, quickly insert the support piece of the plug-in structure (2) with the direction aligned with the processing surface of the ceramic heat insulation tile. When the depth of the guide post reaches the position, rotate the plug-in structure until the positioning block on the plug-in structure engages with the positioning hole on the ceramic heat insulation tile. Then, insert the fixing posts at the bottom of the plug-in structure into the single-layer quartz fiber cotton (~0.8 mm thickness) and the local structure of the aircraft shell respectively. Here, it is necessary to engage the positioning block with the positioning hole on the local structure of the aircraft shell. Finally, tighten the nut with the fixing post on the back of the local structure of the aircraft shell to complete the installation of the component. The installation time of the component is 1.2 min, and the failure load of the tested component is 850 N.

[0069] Example 4:

[0070] A fast plug-in heat insulation tile component described in the present invention specifically includes:

[0071] (1) A ceramic heat insulation tile with dimensions of 50 mm × 50 mm × 40 mm. Process a "T" structure on the side, where the size of the "—" is 13 mm × 18 mm × 1.5 mm; the size of the "|" is 8.5 mm × 4.5 mm × 4.5 mm; process a positioning hole with dimensions of 1.5 mm × 1.5 mm × 1.5 mm on the contact surface between the heat insulation tile and the aircraft shell.

[0072] (2) A plug-in structure, similar to the shape of the Chinese character "下" (xia), all made of stainless steel. The "—" is a support piece with dimensions of 8 mm × 4 mm × 0.8 mm; the upper end of the "|" is a guide post with a diameter of Φ4 mm and a length of 10 mm; the lower end of the "|" is a fixing post processed according to the standard M4 screw rod with a height of ~5 mm; the "," is a positioning block, the distance from its upper end to the support piece is 3 mm, and the dimensions are 7 mm × 1 mm × 1 mm;

[0073] (3) An aircraft shell. In this embodiment, a local structure of the aircraft shell is used for simulation. The dimensions of the local structure of the aircraft shell are 50 mm × 50 mm × 5 mm, including a Φ5 mm through hole and a 1.5 mm × 1.5 mm × 5 mm positioning through hole.

[0074] Process (1), (2), and (3) separately. Cut ceramic fiber cotton / felt / paper with the same size as the local structure of the aircraft shell. After completion, quickly insert the support piece of the insertion structure in (2) with the direction aligned with the processing surface of the ceramic heat insulation tile. When the depth of the guide post is in place, rotate the insertion structure until the positioning block on the insertion structure engages with the positioning hole on the ceramic heat insulation tile. Then, insert the fixing posts at the bottom of the insertion structure into 2 layers of quartz fiber cloth (with a thickness of about 0.4 mm) and the local structure of the aircraft shell respectively. Here, it is necessary to engage the positioning block with the positioning hole on the local structure of the aircraft shell. Finally, tighten the nut with the fixing post on the back of the local structure of the aircraft shell to complete the installation of the component. The installation time of the component is 1.3 min, and the failure load of the tested component is 20 N.

[0075] Example 5:

[0076] A fast-insertion heat insulation tile component according to the present invention specifically includes:

[0077] (1) A ceramic heat insulation tile with dimensions of 50 mm × 50 mm × 60 mm. Process a "T" structure on the side, where the size of the "—" is 29 mm × 33 mm × 2.5 mm; the size of the "|" is 24.5 mm × 8.5 mm × 19.5 mm; process a positioning hole with dimensions of 1.5 mm × 4.5 mm × 5 mm on the contact surface between the heat insulation tile and the aircraft shell.

[0078] (2) An insertion structure, similar to the structure of the Chinese character "下" (xia), all made of stainless steel. Among them, the "—" is a support piece with dimensions of 24 mm × 8 mm × 2 mm; the upper end of the "|" is a guide post with a diameter of Φ5 mm and a length of 25 mm; the lower end of the "|" is a fixing post processed according to the standard M4 screw rod with a height of about 5 mm; the "," is a positioning block, the distance from its upper end to the support piece is 14.5 mm, and its dimensions are 10.5 mm × 1 mm × 4 mm; (3) An aircraft shell. In this embodiment, a local structure of the aircraft shell is used for simulation. The dimensions of the local structure of the aircraft shell are 50 mm × 50 mm × 5 mm, which includes a Φ5 mm through hole and a 1.5 mm × 4.5 mm × 5 mm positioning through hole.

[0079] Process (1), (2) and (3) separately, and cut the ceramic fiber cotton / felt / paper of the same size as the local structure of the aircraft shell. After completion, align the support plate of the (2) plug-in structure with the processing surface of the ceramic insulation tile and quickly insert it. When the guide column is in place, rotate the plug-in structure until the positioning block on the plug-in structure is engaged with the positioning hole on the ceramic insulation tile. Then, insert the fixed column at the bottom of the plug-in structure into the single-layer quartz fiber cotton (~0.8mm thickness) and the local structure of the aircraft shell respectively. Here, the positioning block needs to be engaged with the positioning hole on the local structure of the aircraft shell. Finally, tighten the nut and the fixing column on the back of the local structure of the aircraft shell to complete the installation of the component. The component installation time is 1.5 minutes, and the destructive load of the test component is 320N.

[0080] The contents not described in detail in this application specification belong to the common knowledge of those skilled in the art.

[0081] The present application is described in detail above in conjunction with specific implementation methods and exemplary examples, but these descriptions cannot be understood as limiting the present application. Those skilled in the art understand that, without departing from the spirit and scope of the present application, a variety of equivalent replacements, modifications or improvements can be made to the technical solution of the present application and its implementation methods, all of which fall within the scope of the present application. The scope of protection of the present application shall be subject to the attached claims.

Claims

1. A quick-connect thermal insulation tile assembly, characterized in that: It comprises a ceramic heat-insulating tile (1) and a plug-in structure (2), wherein a T-shaped groove (11) is provided on one surface of the ceramic heat-insulating tile (1); The plug-in structure (2) comprises a fixing column (21), a supporting sheet (22) and a nut (23); the supporting sheet (22) is fixedly connected to the end of the fixing column (21); a through hole (31) is provided in the aircraft shell (3); the supporting sheet (22) is clamped in the T-shaped groove (11); the fixing column (21) extends out of the T-shaped groove and passes through the through hole (31); and the nut (23) is threadedly connected to the end of the fixing column (21) passing through the through hole (31).

2. A quick-connect thermal insulation tile assembly according to claim 1, characterized in that: The plug-in structure (2) also includes a positioning block (24), the positioning block (24) is fixedly connected to one side of the fixing column (21), the aircraft shell (3) is provided with a positioning hole (32), the positioning hole (32) is connected to the through hole (31), and the positioning hole (32) cooperates with the positioning block (24).

3. A quick-connect thermal insulation tile assembly according to claim 2, characterized in that: The surface of the ceramic thermal insulation tile (1) with the T-shaped groove (11) facing the aircraft shell (3) is a mounting surface, and the length of the T-shaped groove (11) starts from one end of the mounting surface and extends from the other end to the middle of the mounting surface.

4. A quick-connect thermal insulation tile assembly according to claim 3, characterized in that: The mounting surface of the ceramic heat-insulating tile (1) is provided with a locking groove (12), and the locking groove (12) is located on one side of the T-shaped groove (11) along the length direction of the T-shaped groove (11), so that after the plug-in structure (2) moves along the open end of the T-shaped groove (11) to the middle of the mounting surface, the positioning block (24) is just locked in the locking groove (12).

5. The quick-connect thermal insulation tile assembly according to claim 1, characterized in that: A flexible heat insulation component is provided between the ceramic heat insulation tile (1) and the aircraft shell (3).

6. A quick-connect thermal insulation tile assembly according to claim 4, characterized in that: The flexible thermal insulation component comprises multiple layers of thermal insulation material, and the thermal insulation material is ceramic fiber wool, ceramic fiber felt and / or ceramic fiber paper.

7. A method for preparing and installing a quick-connect thermal insulation tile assembly according to claim 1, characterized in that: include: Processing the ceramic heat-insulating tile (1) according to the designed dimensions, and processing a T-shaped groove (11) on the mounting surface of the ceramic heat-insulating tile (1); Processing the plug-in structure according to the designed dimensions (2); Cutting flexible insulation materials; Align the end of the T-slot (11) of the ceramic heat-insulating tile (1) with the support sheet (22) of the plug-in structure (2) and insert the ceramic heat-insulating tile (1); when the support sheet (22) is inserted into the T-slot (11) to the required depth, rotate the ceramic heat-insulating tile (1) until the positioning block (24) on the plug-in structure (2) is engaged with the positioning slot (12) on the heat-insulating tile; A flexible heat-insulating material is laid on the surface of an aircraft shell (3), a ceramic heat-insulating tile (1) including a plug-in structure (2) is passed through a through hole (31) on the shell, and a positioning block (24) is passed through a positioning hole (32), and a nut (23) is threadedly connected to the end of a fixing column (21) and tightened.

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