Heat protection structure for morphing wing aircraft and morphing wing aircraft

Abstract

This invention provides a heat-resistant structure and a deformable wing aircraft suitable for use with deformable wing aircraft. The structure includes a shell and a deformable wing. A variable-density, temperature-resistant, and ablation-resistant composite material heat-resistant sleeve is laid on the outer side of the shell. A high-temperature alloy edge strip is installed at the leading edge of the heat-resistant sleeve's tip. The shell separates the deformable wing from the equipment. Dovetail grooves are formed on the surface of the deformable wing, and flexible dynamic sealing ropes are installed within these grooves. This invention improves local temperature resistance and local thermal structural strength by laying variable-density, temperature-resistant, and ablation-resistant composite material heat-resistant sleeves in sections on the outer side of the shell and installing high-temperature alloy edge strips at the leading edge of the heat-resistant sleeve's tip, thus achieving a lightweight heat-resistant structure. By installing wear-resistant and high-temperature-resistant flexible dynamic sealing ropes within the dovetail grooves, the flexible dynamic sealing ropes remain within the gap between the shell and the wing surface throughout the wing's movement. This solves the problem of reduced elasticity of spring tube seals in high-temperature environments, which makes it difficult to achieve high-temperature dynamic heat sealing, and thus meets the requirements for lightweight design and high-temperature dynamic heat sealing.

Description

Technical Field

[0001] This invention relates to the field of heat protection technology, specifically to a heat protection structure suitable for deformable wing aircraft and a deformable wing aircraft. Background Technology

[0002] With the rapid development of aerospace vehicles, the flight airspace and speed range of new aircraft are constantly expanding. Fixed shapes are increasingly unable to meet the aerodynamic and flight performance requirements of different flight conditions. Deformable wings are one of the key technical solutions to improve aircraft performance. To adapt to different flight conditions, deformable wings need to effectively deploy and retract under prolonged high-temperature, high-speed airflow. Therefore, the gap between the deformable wing and the shell needs to be dynamically sealed to prevent high-temperature airflow from entering the shell and affecting the normal operation of temperature-sensitive equipment. The thermal insulation problem between the deformable wing and the shell presents challenges in high-temperature dynamic thermal sealing, including poor temperature resistance, abrasion resistance, oxidation resistance, and resilience of the sealing components. Furthermore, the high density of high-performance thermal insulation materials is a concern in terms of structural lightweighting.

[0003] Therefore, there is a need to provide a heat-resistant structure suitable for deformable wing aircraft, which, while achieving a lightweight structure, solves the problem of reduced elasticity of spring tube seals in high-temperature environments, making it difficult to achieve dynamic heat sealing at high temperatures. Summary of the Invention

[0004] In view of the deficiencies in the prior art, the purpose of this invention is to provide a heat-resistant structure suitable for deformable wing aircraft and a deformable wing aircraft.

[0005] According to the present invention, a heat protection structure suitable for deformable wing aircraft is provided, comprising a shell and a deformable wing. The outer side of the shell is covered with a heat protection sleeve of variable density, temperature-resistant and ablation-resistant composite material. A high-temperature alloy edge strip is installed in the leading edge region of the tip of the heat protection sleeve. The shell separates the deformable wing from the equipment. A dovetail groove is formed on the surface of the deformable wing, and a flexible dynamic sealing rope is installed in the dovetail groove.

[0006] Preferably, the variable density temperature-resistant and ablation-resistant composite material heat shield includes a low-density temperature-resistant and ablation-resistant composite material heat shield and a high-density temperature-resistant and ablation-resistant composite material heat shield. The high-density temperature-resistant and ablation-resistant composite material heat shield is disposed on the side of the shell near the deformable wing, and the low-density temperature-resistant and ablation-resistant composite material heat shield is disposed on the side of the shell away from the deformable wing.

[0007] Preferably, the low-density, heat-resistant, and ablation-resistant composite heat shield includes glass fiber reinforced phenolic resin-based composite material or aramid fiber reinforced phenolic resin-based composite material.

[0008] Preferably, the high-density, temperature-resistant, and ablation-resistant composite heat shield includes quartz phenolic material or quartz ceramic material.

[0009] Preferably, the high-temperature alloy edge strip is fixed to the heat-resistant sleeve and the housing by riveting or screwing.

[0010] Preferably, the flexible dynamic sealing rope has a high-temperature alloy braided spring as its skeleton, is filled with high-performance heat insulation material, and is wrapped with a ceramic fiber braided sleeve on the outside.

[0011] Preferably, the high-performance thermal insulation material includes a ceramic fiber cotton core or an aerogel felt.

[0012] Preferably, during the movement of the wing surface, the flexible dynamic sealing rope remains within the gap between the shell and the deformable wing.

[0013] Preferably, the outer diameter of the high-temperature alloy braided spring is 6mm, the thickness of the ceramic fiber braided sleeve is 1mm, the gap between the shell and the deformable wing is 2mm, and the depth of the dovetail groove is 3mm.

[0014] According to the present invention, a deformable wing aircraft adopts the above-described heat protection structure suitable for deformable wing aircraft.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] This invention improves local temperature resistance and local thermal structural strength by laying variable-density, temperature-resistant, and ablation-resistant composite material heat shields in different areas on the outer side of the shell, and installing high-temperature alloy edge strips at the leading edge of the heat shield tip, thus achieving lightweight heat shield structure. The shell separates the equipment from the deformable wing inside and out. Dovetail grooves are opened on the surface of the deformable wing, and wear-resistant, high-temperature-resistant flexible dynamic sealing ropes are installed in the dovetail grooves. During the movement of the wing surface, the flexible dynamic sealing ropes are within the gap between the shell and the wing surface throughout the process, which solves the problem of the elasticity of the spring tube seals decreasing in high-temperature environments, making it difficult to achieve high-temperature dynamic heat sealing. This invention can meet the requirements of lightweight and high-temperature dynamic heat sealing for deformable wing aircraft. Attached Figure Description

[0017] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0018] Figure 1 This is a schematic diagram illustrating the heat protection structure of the deformable wing aircraft, which is the main feature of this invention.

[0019] Figure 2 This invention is mainly embodied in Figure 1 A magnified view of part A in the middle;

[0020] Figure 3 This is a schematic diagram illustrating the structure of the flexible dynamic sealing rope, which is the main feature of this invention.

[0021] As shown in the figure:

[0022] High-density, high-temperature, and ablation-resistant composite material 1; High-temperature alloy edge strip 2

[0023] 3. High-temperature alloy edge strip; 4. High-density, high-temperature and ablation-resistant composite material.

[0024] 5. Low-density, high-temperature, and ablation-resistant composite material on the shell 6

[0025] Flexible dynamic sealing rope 7 Deformable wing 8

[0026] Low-density, high-temperature, and ablation-resistant composite material 9 Ceramic fiber braided sleeve 701

[0027] High-temperature alloy braided spring 702; High-performance thermal insulation material 703 Detailed Implementation

[0028] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0029] Example 1

[0030] like Figure 1-3 As shown, a heat protection structure for deformable wing aircraft provided by the present invention includes a shell 5 and a deformable wing 8. A heat protection sleeve of variable density, temperature-resistant and ablation-resistant composite material is laid on the outer side of the shell 5. A high-temperature alloy edge strip is installed in the leading edge area of ​​the tip of the heat protection sleeve. The shell 5 separates the deformable wing 8 from the equipment. A dovetail groove is opened on the surface of the deformable wing 8. A wear-resistant and high-temperature-resistant flexible dynamic sealing rope 7 is installed in the dovetail groove. During the movement of the wing surface, the flexible dynamic sealing rope 7 is in the gap between the shell 5 and the wing surface throughout the entire process.

[0031] This application meets the requirements for lightweight design and high-temperature dynamic heat sealing in deformable wing aircraft. A variable-density, high-temperature, and ablation-resistant composite material heat shield is laid in sections on the outer side of the shell 5. A high-temperature alloy edge strip is installed at the leading edge of the heat shield tip to improve local temperature resistance and local thermal structural strength, achieving lightweight design of the heat shield structure. The shell 5 separates the equipment from the deformable wing 8. A dovetail groove is cut on the surface of the deformable wing 8, and a wear-resistant, high-temperature resistant flexible dynamic sealing rope 7 is installed within the dovetail groove 8. During wing movement, the flexible dynamic sealing rope 7 remains within the gap between the shell 5 and the wing surface, solving the problem of reduced elasticity of the spring tube seal in high-temperature environments, which makes high-temperature dynamic heat sealing difficult.

[0032] The variable-density, temperature- and ablation-resistant composite material heat shield includes a low-density and high-density heat shield. The high-density heat shield is located on the side of the shell 5 closest to the deformable wing 8, while the low-density heat shield is located on the side of the shell 5 furthest from the deformable wing 8. Specifically, the aircraft surface is divided into zones based on heat flux density: the lower low-density heat- and ablation-resistant composite material 9 and the upper low-density heat- and ablation-resistant composite material 6 are low heat flux density areas, while the lower high-density heat- and ablation-resistant composite material 1 and the upper high-density heat- and ablation-resistant composite material 4 are high heat flux density areas.

[0033] In most areas, the heat shield uses a low-density, temperature- and ablation-resistant composite material to achieve a lightweight structure. In areas with harsh local thermal environments near the deformable wing 8, a higher-performance, high-density, temperature- and ablation-resistant material is used to ensure reliable thermal protection. Preferably, the low-density, temperature- and ablation-resistant composite material heat shield includes glass fiber reinforced phenolic resin-based composite material or aramid fiber reinforced phenolic resin-based composite material. The high-density, temperature- and ablation-resistant composite material heat shield includes quartz phenolic material or quartz ceramic material.

[0034] The high-temperature alloy edge strips are fixed to the heat-resistant sleeve and shell 5 by riveting or screwing, thereby improving the local temperature resistance and local thermal structural strength. Preferably, the high-temperature alloy edge strip material is GH4049 or GH4099. Specifically, to fix the heat-resistant sleeve and improve the local temperature resistance and thermal structural strength, the upper high-temperature alloy edge strip 3 and the lower high-temperature alloy edge strip 2, made of GH4049, are fixed to the heat-resistant sleeve and shell 5 respectively by M5 screws.

[0035] The flexible dynamic sealing rope 7 uses a high-temperature alloy braided spring 702 as its skeleton, is filled with a high-performance heat insulation material 703, and is wrapped with a temperature-resistant and fire-resistant ceramic fiber braided sleeve 701. Preferably, the high-performance heat insulation material 703 includes a ceramic fiber cotton core or an aerogel felt.

[0036] The flexible dynamic sealing rope 7 is embedded in the dovetail groove on the surface of the deformable wing 8. During the movement of the wing surface, the flexible dynamic sealing rope 7 moves within the gap between the shell 5 and the deformable wing 8 due to the dovetail groove.

[0037] This application is further illustrated by the following data. The flexible dynamic sealing rope 7 comprises three layers: a ceramic fiber braided sleeve 701, a high-temperature alloy braided spring 702, and a high-performance heat insulation material 703. The high-temperature alloy braided spring 702, made of GH4099, has a diameter of 6 mm, is internally filled with high-performance heat insulation material 703, and is externally wrapped with a 1 mm thick temperature-resistant and fire-resistant ceramic fiber braided sleeve 701. Under no-compression conditions, the diameter of the flexible dynamic sealing rope 7 is 8 mm. At a high temperature of 500 degrees Celsius, when compressed by 1 mm, the rebound rate is greater than 90%, and the rebound amount is greater than 0.9 mm; when compressed by 3 mm, the rebound rate is greater than 70%, and the rebound amount is greater than 2.1 mm.

[0038] The equipment is separated from the deformable wing 8 by the housing 5, with a 2mm gap between the upper and lower parts of the housing 5 and the deformable wing 8. A 3mm deep dovetail groove is cut on the surface of the deformable wing 8, and the flexible dynamic sealing rope 7 is embedded in the dovetail groove on the surface of the deformable wing 8. When the wing surface moves in a high-temperature environment of 500 degrees Celsius, the flexible dynamic sealing rope 7 is compressed by the housing 5 and the deformable wing 8 throughout the process. Due to the dovetail groove, it reciprocates within the gap, and the compression varies within 1mm to 3mm, always maintaining its elasticity.

[0039] By designing a heat shield structure using variable-density, temperature-resistant, and ablation-resistant composite materials, the weight of the heat shield was reduced from 5 kg when using a single high-density, temperature-resistant, and ablation-resistant composite material to 4 kg, achieving a significant weight reduction of 20%, while still meeting the heat protection requirements.

[0040] This application solves the problem of the reduced elasticity of spring tube seals in high-temperature environments, which makes it difficult to achieve dynamic heat sealing at high temperatures, by using wear-resistant and high-temperature resistant flexible dynamic sealing rope 7 and a heat-resistant jacket of variable density, high temperature and ablation resistant composite material. This reduces the weight of the heat-resistant structure and provides technical support for the design of heat-resistant structures for deformable wing aircraft.

[0041] Example 2

[0042] According to the present invention, a deformable wing aircraft adopts the heat-resistant structure of embodiment 1 suitable for deformable wing aircraft, which effectively solves the problem that the elasticity of the spring tube seal decreases in a high-temperature environment, making it difficult to achieve high-temperature dynamic heat sealing. It can meet the requirements of lightweight and high-temperature dynamic heat sealing of deformable wing aircraft.

[0043] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They 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. Therefore, they should not be construed as limitations on this application.

[0044] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A heat protection structure suitable for use in a morphing wing aircraft, characterized in that, It includes a shell (5) and a deformable wing (8). The outer side of the shell (5) is covered with a heat-resistant jacket made of variable density, temperature-resistant and ablation-resistant composite material. A high-temperature alloy edge strip is installed in the leading edge area of ​​the tip of the heat-resistant jacket. The shell (5) separates the deformable wing (8) from the equipment. A dovetail groove is opened on the surface of the deformable wing (8). A flexible dynamic sealing rope (7) is installed in the dovetail groove. The variable density temperature-resistant and ablation-resistant composite material heat shield includes a low density temperature-resistant and ablation-resistant composite material heat shield and a high density temperature-resistant and ablation-resistant composite material heat shield. The high density temperature-resistant and ablation-resistant composite material heat shield is disposed on the side of the shell (5) close to the deformable wing (8), and the low density temperature-resistant and ablation-resistant composite material heat shield is disposed on the side of the shell (5) away from the deformable wing (8). The flexible dynamic sealing rope (7) has a high-temperature alloy braided spring (702) as its skeleton, is filled with high-performance heat insulation material (703) inside, and is wrapped with ceramic fiber braided sleeve (701) outside.

2. The heat protection structure for deformable wing aircraft as described in claim 1, characterized in that, The low-density, heat-resistant, and ablation-resistant composite heat shield includes glass fiber reinforced phenolic resin-based composite material or aramid fiber reinforced phenolic resin-based composite material.

3. The heat protection structure for deformable wing aircraft as described in claim 1, characterized in that, The high-density, temperature-resistant, and ablation-resistant composite heat shield includes quartz phenolic material or quartz ceramic material.

4. The heat protection structure for deformable wing aircraft as described in claim 1, characterized in that, The high-temperature alloy edge strip is fixed to the heat-resistant sleeve and the shell (5) by riveting or screwing.

5. The heat protection structure for deformable wing aircraft as described in claim 1, characterized in that, The high-performance thermal insulation material (703) includes ceramic fiber cotton core or aerogel felt.

6. The heat protection structure for deformable wing aircraft as described in claim 1, characterized in that, During the movement of the wing surface, the flexible dynamic sealing rope (7) remains within the gap between the shell (5) and the deformable wing (8).

7. The heat protection structure for deformable wing aircraft as described in claim 6, characterized in that, The outer diameter of the high-temperature alloy braided spring (702) is 6mm, the thickness of the ceramic fiber braided sleeve (701) is 1mm, the gap between the shell (5) and the deformable wing (8) is 2mm, and the depth of the dovetail groove is 3mm.

8. A deformable wing aircraft, characterized in that, The heat-resistant structure suitable for deformable wing aircraft as described in any one of claims 1-7 is adopted.

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