Thermal protection structure for surface of aircraft body of hypersonic aircraft

Abstract

The invention belongs to the field, and particularly relates to a hypersonic aircraft body surface thermal protection structure which comprises a heat insulation tile, a flexible filling material and a ceramic tile. A plurality of heat insulation tiles are laid on the surface of the machine body; gaps among the heat insulation tiles are filled with the flexible filling material; a plurality of ceramic tiles are laid above the heat insulation tiles; the joints between the ceramic tiles and the gaps between the heat insulation tiles are staggered to cover the gaps between the heat insulation tiles, and the flexible filling material is limited in the gaps between the heat insulation tiles; transverse ribs are arranged in the parts, protruding out of the edges of the heat insulation tiles, of the edges of the ceramic tiles, and a plurality of longitudinal ribs are arranged between the transverse ribs and the edges of the ceramic tiles; the transverse ribs are correspondingly inserted into gaps among the heat insulation tiles and are pressed on the flexible filling material; the longitudinal ribs on the transverse ribs are inserted into a plurality of clamping grooves formed in the edges of the corresponding heat insulation tiles.

Description

Technical Field

[0001] This application belongs to the field of thermal protection structure for the surface of a hypersonic aircraft fuselage. Background Technology

[0002] When a hypersonic vehicle is in flight, its surface is subjected to an extremely high heat load. Currently, the most common method to address this is to install heat-insulating tiles on the surface of the vehicle for thermal protection.

[0003] Thermal insulation tiles are typically made of brittle materials. When they are large in size, they are prone to damage due to the large thermal stress generated by the temperature gradient. Therefore, thermal insulation tiles should not be designed to be too large. They are usually designed as small block structures that are spliced ​​on the surface of the machine body.

[0004] Gaps exist between the heat insulation tiles on the airframe surface. To ensure effective thermal protection, these gaps are typically filled with flexible insulation material and bonded with high-temperature adhesive. However, this method suffers from significant drawbacks, including the low strength of the flexible insulation material and poor reliability of the high-temperature adhesive bonding. The tiles are prone to detachment under high temperatures, leading to sealing failure and posing a significant threat to the safety of the hypersonic vehicle. Furthermore, assembly quality limitations can easily result in uneven surface finishes, leading to poor surface quality and severely impacting the aerodynamic performance of the hypersonic vehicle.

[0005] This application is made in view of the aforementioned technical deficiencies. Summary of the Invention

[0006] The purpose of this application is to provide a thermal protection structure for the surface of a hypersonic aircraft fuselage to overcome or mitigate at least one of the known technical defects.

[0007] The technical solution of this application is:

[0008] A thermal protection structure for the surface of a hypersonic aircraft fuselage includes heat-insulating tiles, flexible filling materials, and ceramic tiles;

[0009] There are multiple heat insulation tiles, which are laid on the surface of the machine body;

[0010] Flexible filler material is used to fill the gaps between the insulation tiles;

[0011] There are multiple ceramic tiles, which are laid on top of each heat-insulating tile;

[0012] The joints between the ceramic tiles are staggered from the gaps between the insulation tiles, covering the gaps between the insulation tiles and confining the flexible filling material within the gaps between the insulation tiles.

[0013] Horizontal ribs are provided in the part of each ceramic tile that protrudes from the edge of the heat insulation tile, and multiple longitudinal ribs are provided between the horizontal ribs and the edge of the ceramic tile;

[0014] Each horizontal rib is inserted into the gap between each heat insulation tile and pressed onto the flexible filling material;

[0015] The longitudinal ribs on each transverse rib are inserted into multiple slots opened on the edge of each corresponding heat insulation tile.

[0016] According to at least one embodiment of this application, in the above-described hypersonic aircraft fuselage surface thermal protection structure, the flexible filling material is a high-temperature heat insulation felt.

[0017] According to at least one embodiment of this application, in the above-mentioned hypersonic aircraft body surface thermal protection structure, high-temperature adhesive is injected into the gaps between each heat insulation tile.

[0018] The edges of the gaps between each heat insulation tile have multiple serrated grooves distributed along the height.

[0019] According to at least one embodiment of this application, in the above-mentioned hypersonic aircraft fuselage surface thermal protection structure, each ceramic tile and the heat insulation tile are co-sintered or bonded and mechanically connected.

[0020] According to at least one embodiment of this application, in the above-described hypersonic aircraft fuselage surface thermal protection structure, the joints between the ceramic tiles are filled with high-temperature adhesive.

[0021] According to at least one embodiment of this application, in the above-mentioned hypersonic aircraft body surface thermal protection structure, there is a 2mm gap between the part of each ceramic tile edge that protrudes from the edge of the heat insulation tile and the heat insulation tile.

[0022] There are small gaps between the longitudinal ribs on each transverse rib and the slot.

[0023] According to at least one embodiment of this application, the above-described hypersonic aircraft fuselage surface thermal protection structure further includes a strain isolation pad.

[0024] Strain-resistant insulating pads are placed between each heat insulation tile and the surface of the machine body.

[0025] According to at least one embodiment of this application, in the above-described hypersonic aircraft fuselage surface thermal protection structure, strain isolation pads are bonded or mechanically connected between each heat insulation tile and the fuselage surface. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the thermal protection structure on the surface of a hypersonic aircraft provided in an embodiment of this application;

[0027] Figure 2 This is a schematic diagram of the transverse ribs provided in the embodiment of this application, which are provided in the part of each ceramic tile that protrudes from the edge of the heat insulation tile.

[0028] Figure 3 This is a schematic diagram of a slot being formed at the edge of the heat insulation tile (1) according to an embodiment of this application;

[0029] Figure 4 This is an analytical structural model diagram of the thermal protection structure of the supersonic aircraft fuselage surface provided in the embodiments of this application;

[0030] Figure 5 This is a temperature distribution diagram of the analytical structure of the thermal protection structure on the surface of a supersonic aircraft provided in the embodiments of this application;

[0031] in:

[0032] 1-Insulation tile; 2-Flexible filling material; 3-Ceramic tile; 4-Strain isolation pad; 5-Body; 6-Transverse rib; 7-Longitudinal rib.

[0033] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0034] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0035] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0036] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0037] A thermal protection structure for the surface of a hypersonic aircraft fuselage, such as Figure 1 As shown, it includes heat insulation tile 1, flexible filling material 2, ceramic tile 3, and strain isolation pad 4.

[0038] There are multiple heat insulation tiles 1, which are laid on the surface of the body 5.

[0039] The flexible filler material 2 is filled in the gaps between each heat insulation tile 1. Specifically, high-temperature heat insulation felt can be used. At the same time, high-temperature adhesive can be injected into the gaps between each heat insulation tile 1. In order to prevent the flexible filler material 2 from falling out of the gaps between each heat insulation tile 1, the edge of each heat insulation tile 1 can be designed to have multiple serrated grooves distributed along the height to increase the friction of the flexible filler material 2 in the gaps between each heat insulation tile 1.

[0040] There are multiple ceramic tiles 3, which are laid on top of each heat insulation tile 1. They can be co-sintered or bonded and mechanically connected to the heat insulation tile 1.

[0041] The joints between each ceramic tile 3 are staggered from the gaps between each heat insulation tile 1, so as to cover the gaps between each heat insulation tile 1, confine the flexible filling material 2 in the gaps between each heat insulation tile 1, prevent the flexible filling material 2 from falling off, ensure the sealing of the gaps between each heat insulation tile 1, and ensure the thermal protection effect on the surface of the body 5.

[0042] The ceramic tile 3 is relatively thin, and the joint size between each ceramic tile 3 can be designed to be small. The surface is easy to smooth and the joints between each ceramic tile 3 can be filled with high-temperature adhesive. When it is laid on top of the heat insulation tile 1, it can ensure the quality of the surface of the body 5, thereby ensuring the aerodynamic performance of the hypersonic aircraft. In addition, the ceramic tile 3 has high impact resistance and airflow erosion resistance. When it is laid on top of each heat insulation tile 1, it can provide effective protection for each heat insulation tile 1.

[0043] Because the seams between the ceramic tiles 3 are staggered from the seams between the insulation tiles 1, there are areas where the edges of the ceramic tiles 3 protrude from the edges of the insulation tiles 1, forming vulnerable cantilever beam structures. To protect these protruding areas from damage, a 2mm gap is designed between the protruding edges of the ceramic tiles 3 and the insulation tiles 1. Furthermore, transverse ribs 6 are installed within the protruding edges of the ceramic tiles 3 and the insulation tiles 1, and multiple longitudinal ribs 7 are installed between the transverse ribs 6 and the edges of the ceramic tiles 3. Figure 2 As shown, this enhances the strength of the edges of each ceramic tile 3 that protrude from the edge of the heat insulation tile 1, preventing damage.

[0044] Each transverse rib 6 is inserted into the gap between each heat insulation tile 1, pressing it onto the flexible filling material 2 to compact it. Additionally, the longitudinal ribs 7 on each transverse rib 6 are inserted into multiple slots opened at the edges of each corresponding heat insulation tile 1. Figure 3 As shown, there is a small gap between the card and the slot.

[0045] Strain isolation pads 4 are placed between each heat insulation tile 1 and the surface of the body 5. Specifically, they can be glued or mechanically connected between each heat insulation tile 1 and the surface of the body 5 so that deformation matching can be achieved between each heat insulation tile 1 and the surface of the body 5.

[0046] In a specific experimental analysis example, a flat thermal protection structure of 600mm×600mm×40mm was selected. A 2mm thick ceramic tile, a 33mm thick heat insulation tile, and a 2mm thick strain isolation pad were installed. A 3mm thick aluminum alloy substrate was used to replace the main body 5 to construct the analysis structure. Experimental analysis was conducted, and the analysis structure model is as follows: Figure 4 As shown, a temperature load of 1228℃ was applied to the outer surface of the analyzed structure, natural convection heat transfer was provided on the inner surface of the aluminum alloy substrate, the ambient temperature was 22℃, the natural convection heat transfer coefficient was set to 10 (W / (m2·℃), and the heating time was set to 300s. The temperature distribution of the analyzed structure was obtained, as shown below. Figure 5 As shown, the results indicate that the temperature of most aluminum alloy substrates does not exceed 50°C, and the thermal protection effect is good.

[0047] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A thermal protection structure for the surface of a hypersonic aircraft fuselage, characterized in that, Including heat-insulating tiles (1), flexible filling material (2), and ceramic tiles (3); There are multiple heat insulation tiles (1), which are laid on the surface of the machine body (5); Flexible filling material (2) is filled into the gaps between each heat insulation tile (1); There are multiple ceramic tiles (3), which are laid on top of each heat insulation tile (1); The joints between each ceramic tile (3) are staggered from the gaps between each heat insulation tile (1), covering the gaps between each heat insulation tile (1), and confining the flexible filling material (2) in the gaps between each heat insulation tile (1); A transverse rib (6) is provided in the part of the edge of each ceramic tile (3) that protrudes from the edge of the heat insulation tile (1), and multiple longitudinal ribs (7) are provided between the transverse rib (6) and the edge of the ceramic tile (3); Each transverse rib (6) is inserted into the gap between each heat insulation tile (1) and pressed onto the flexible filling material (2); The longitudinal ribs (7) on each transverse rib (6) are inserted into multiple slots opened at the edges of each corresponding heat insulation tile (1).

2. The hypersonic aircraft fuselage surface thermal protection structure according to claim 1, characterized in that, The flexible filling material (2) is a high-temperature heat insulation felt.

3. The hypersonic aircraft fuselage surface thermal protection structure according to claim 2, characterized in that, High-temperature adhesive was injected into the gaps between each heat insulation tile (1); The edges of the gaps between each heat insulation tile (1) have multiple serrated grooves distributed along the height.

4. The hypersonic aircraft fuselage surface thermal protection structure according to claim 3, characterized in that, Each ceramic tile (3) is co-sintered or bonded to the heat insulation tile and mechanically connected.

5. The hypersonic aircraft fuselage surface thermal protection structure according to claim 4, characterized in that, The joints between each ceramic tile (3) are filled with high-temperature adhesive.

6. The hypersonic aircraft fuselage surface thermal protection structure according to claim 5, characterized in that, There is a 2mm gap between the edge of each ceramic tile (3) that protrudes from the edge of the heat insulation tile (1) and the heat insulation tile (1); There is a small gap between the longitudinal ribs (7) on each transverse rib (6) and the slot.

7. The hypersonic aircraft fuselage surface thermal protection structure according to claim 6, characterized in that, It also includes strain isolation pads (4); Strain isolation pads (4) are placed between each heat insulation tile (1) and the surface of the body (5).

8. The hypersonic aircraft fuselage surface thermal protection structure according to claim 7, characterized in that, Strain isolation pads (4) are bonded or mechanically connected between each heat insulation tile (1) and the surface of the body (5).

Images