Aircraft head cabin for hypersonic environment

Abstract

The invention provides an aircraft head cabin for a hypersonic speed environment, and relates to the technical field of aircraft heat insulation, a heat protection assembly is arranged outside the aircraft head cabin, the aircraft head cabin comprises a bearing layer and a heat protection layer, the bearing layer is provided with a bottom plate, and a lattice structure is arranged on the side, away from the head cabin, of the bottom plate and is composed of a plurality of lattice units; first gaps are formed among the dot matrix units; the heat-proof layer is arranged on the side, away from the head cabin body, of the bearing layer, and the first gap is filled with the heat-proof layer; in the preparation process, the heat-proof layer and the bearing layer are prepared together, and the two layers are in gapless connection to form an integrated heat-proof system, so that the maintainability of the heat protection assembly is improved; meanwhile, the lattice structure can reduce the mass while ensuring the strength, and when the heat-proof layer and the bearing layer are integrally prepared, additional connecting structures and supporting parts can be avoided, so that the overall mass of the head cabin is further reduced, the waste of space is reduced, and the performance of the aircraft is improved.

Description

Technical Field

[0001] The present application generally relates to the field of aircraft thermal insulation technology, and specifically to an aircraft head cabin for use in a hypersonic environment. Background Art

[0002] When an aircraft is flying at high speed, a bow-shaped appendage shock wave will be formed on the warhead, which will have a strong compression effect on the incoming flow. At the same time, there will be severe friction between the head and the incoming flow, causing the air temperature to rise sharply. Therefore, during the flight, the head cabin experiences a high-speed, high-pressure and high-temperature environment, which will cause severe ablation of the surface material of the head cabin, destroying the aircraft structure or causing the internal temperature of the aircraft to rise, posing a threat to the safety analysis of the aircraft.

[0003] In order to prevent the head of the aircraft from being burned, thermal protection measures need to be adopted; the thermal protection structure itself has a low mechanical bearing capacity and cannot share the load of the head cabin; therefore, existing aircraft usually set up a load-bearing structure between the thermal protection structure and the head cabin to share the load of the fuselage structure; but such a design will increase the weight of the aircraft and affect the performance of the aircraft; and the load-bearing structure and the thermal protection structure are usually bonded, which has poor maintainability. Summary of the invention

[0004] In view of the above-mentioned defects or deficiencies in the prior art, it is desired to provide an aircraft head cabin for use in a hypersonic environment that can solve the above-mentioned technical problems.

[0005] The present application provides an aircraft head cabin for use in a hypersonic environment, comprising: The head cabin body; the exterior of the head cabin body is provided with a heat protection component, the heat protection component is an integrated heat protection system; the heat protection component comprises: A bearing layer, the bearing layer is connected to the head cabin; the bearing layer comprises: a bottom plate, a lattice structure is arranged on a side of the bottom plate away from the head cabin, the lattice structure is composed of a plurality of lattice units, and a first gap is provided between the lattice units; A heat protection layer is provided on a side of the bearing layer away from the head compartment, and the heat protection layer is filled in the first gap.

[0006] According to the technical solution provided in the present application, the lattice unit is an octahedral lattice unit, and a second gap is provided inside the octahedral lattice unit; the octahedral lattice unit has eight planes, each of which is an equilateral triangle frame, and a vertex of one plane is fixedly connected to the base plate; the heat protection layer is filled in the second gap.

[0007] According to the technical solution provided in the present application, the lattice unit is made of titanium alloy, high-temperature alloy, aluminum alloy or stainless steel.

[0008] According to the technical solution provided in the present application, a cooling layer is further provided between the bottom plate and the head cabin.

[0009] According to the technical solution provided in the present application, the cooling layer is a grid heat dissipation structure, and the grid heat dissipation structure includes: a grid body, a pipeline is arranged in the grid body, and a cooling medium circulates inside the pipeline.

[0010] According to the technical solution provided in the present application, an aluminum foil layer is arranged between the cooling layer and the bottom plate, and the aluminum foil layer is used to reduce thermal radiation energy.

[0011] According to the technical solution provided in the present application, an asbestos cushion layer is provided between the cooling layer and the head cabin.

[0012] According to the technical solution provided in the present application, the pipeline is connected to a cooling system, and the cooling system is used to circulate the cooling medium into the pipeline.

[0013] The beneficial effects of this application are: The present application provides a head cabin of an aircraft for use in a hypersonic environment, wherein a thermal protection component is arranged on the outside, and the thermal protection component comprises: a bearing layer and a thermal protection layer, wherein the bearing layer has a bottom plate, and a lattice structure is arranged on a side of the bottom plate away from the head cabin, wherein the lattice structure is composed of a plurality of lattice units, and a first gap is provided between the lattice units; the thermal protection layer is arranged on a side of the bearing layer away from the head cabin, and the thermal protection layer is filled in the first gap; so that during the preparation process, the thermal protection layer and the bearing layer are prepared together, and the two layers are connected without a gap to form a continuous and integrated thermal protection system, thereby improving the maintainability of the thermal protection component and preventing the thermal protection layer from falling off under high-speed airflow scouring and drastic temperature changes; at the same time, the lattice structure can reduce the weight while ensuring the strength, and when the thermal protection layer and the bearing layer are prepared as an integrated whole, additional connection structures and supporting components can be avoided, thereby further reducing the overall weight of the head cabin, reducing space waste, and improving the performance of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Other features, objects and advantages of the present application will become more apparent by reading the detailed description of non-limiting embodiments made with reference to the following drawings: Figure 1 is a cross-sectional view of a head cabin of an aircraft for use in a hypersonic environment provided by the present application; Figure 2 It is a schematic diagram of the octahedral lattice unit provided in this application.

[0015] In the figure: 1, bottom plate; 2, heat protection layer; 3, cooling layer; 4, asbestos cushion layer; 5, lattice unit; 51, rod; 52, second gap; 6, aluminum foil layer; 7, head cabin. DETAILED DESCRIPTION

[0016] The present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the relevant invention, rather than to limit the invention. It is also necessary to explain that, for ease of description, only the parts related to the invention are shown in the accompanying drawings.

[0017] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0018] Example 1 Please refer to Figure 1-Figure 2 The present application provides a head cabin of an aircraft for use in a hypersonic environment, comprising: The head cabin 7; the outside of the head cabin 7 is provided with a heat protection component, and the heat protection component is an integrated heat protection system; the heat protection component includes: A bearing layer, the bearing layer is connected to the head cabin 7; the bearing layer comprises: a bottom plate 1, a side of the bottom plate 1 away from the head cabin 7 is provided with a lattice structure, the lattice structure is composed of a plurality of lattice units 5, and a first gap is provided between the lattice units 5; The heat protection layer 2 is arranged on a side of the bearing layer away from the head compartment 7, and the heat protection layer 2 is filled in the first gap.

[0019] Specifically, the lattice structure has unique mechanical properties, which can reduce the structural mass while ensuring strength. When the heat protection layer 2 and the bearing layer with the lattice structure are prepared together, the heat protection layer 2 can play an auxiliary supporting role to a certain extent, and form a synergistic enhancement effect with the lattice structure. When the lattice structure is subjected to external loads, the heat protection layer 2 can help disperse local stress and prevent the lattice structure from being damaged due to excessive local stress, thereby improving the bearing capacity of the entire structure, so that the thermal protection component has a strong bearing capacity while having heat protection performance; Specifically, the heat protection layer 2 is directly filled in the first gap of the lattice structure to form a continuous and integrated heat protection system. In the present embodiment, the heat protection layer 2 is made of an anti-oxidation C / C composite material. The heat protection layer made of the C / C composite material is seamlessly filled in the lattice structure by using 3D printing technology, so that the heat protection layer 2 and the bearing layer form an integrated heat protection system, providing excellent thermal protection performance. When the aircraft faces a high temperature environment, the heat protection layer 2 can effectively block the heat from being transferred to the inside of the head cabin 7, reducing heat conduction. At the same time, compared with the traditional method of pasting or hanging the heat protection layer 2, this integrated structure can prevent the heat protection layer 2 from falling off under the impact of high-speed airflow and drastic temperature changes, greatly improving the stability of the heat protection layer 2. At the same time, the lattice structure itself is a lightweight structural form, which can reduce the mass while ensuring strength; when the heat protection layer 2 is integrated with the lattice structure, the mass of the head cabin 7 is further reduced to increase the effective load of the aircraft and reduce the launch cost; Working principle: During the preparation process, the heat protection layer 2 and the bearing layer are prepared together, and the two layers are connected without a gap, forming a continuous, integrated heat protection system, which improves the maintainability of the thermal protection component and prevents the heat protection layer 2 from falling off under high-speed airflow and drastic temperature changes; at the same time, the lattice structure can reduce the weight while ensuring strength. When the heat protection layer 2 and the bearing layer are prepared in an integrated manner, additional connecting structures and supporting components can be avoided, further reducing the overall weight of the head cabin 7, reducing space waste, and improving the performance of the aircraft.

[0020] In some embodiments, the lattice unit 5 is an octahedral lattice unit, and a second gap 52 is provided inside the octahedral lattice unit; the octahedral lattice unit has eight planes, each of which is an equilateral triangle frame, and a vertex of one plane is fixedly connected to the base plate 1; the heat protection layer 2 is filled in the second gap 52.

[0021] Specifically, Figure 2 As shown, the lattice unit 5 is an octahedral lattice unit; wherein the octahedral lattice unit has good geometric symmetry, and when subjected to external force, the stress can be relatively evenly distributed on each rod 51 and the node, and this uniform stress distribution helps to improve the overall strength and stability of the structure and avoid structural failure caused by local stress concentration; At the same time, the octahedral lattice unit in the present application has eight planes, each of which is an equilateral triangle frame; that is, the octahedral lattice unit is composed of six vertices and twelve rods 51, and by arranging the rods 51 and connecting the vertices, a higher structural strength can be achieved while using less material; multiple octahedral lattice units are connected together by sharing vertices or rods 51 to form a lattice structure; There are a large number of first gaps and second gaps 52 inside the lattice structure composed of octahedral lattice units, and the air in these gaps plays a role of heat insulation, so that the structure has a lower thermal conductivity; this low thermal conductivity property is very important in application scenarios that require heat insulation; and in the present application, the heat-proof layer 2 is used to fill all the first gaps and second gaps 52 to further increase the heat insulation effect; Specifically, in the present embodiment, a vertex of a plane of the octahedral lattice unit is fixedly connected to the base plate 1, and the base plate 1 provides a solid supporting foundation for the lattice structure. When the entire structure is subjected to external force, the base plate 1 can evenly disperse the force borne by the lattice unit 5 to a larger contact area, thereby preventing the lattice unit 5 from being damaged due to excessive local force. At the same time, when the lattice unit 5 undergoes thermal expansion or contraction due to temperature changes, the base plate 1 can suppress its excessive deformation.

[0022] In some embodiments, the lattice unit 5 is made of titanium alloy, high-temperature alloy, aluminum alloy or stainless steel.

[0023] Specifically, in this embodiment, the base plate 1 and the lattice structure are manufactured by 3D printing. During the 3D printing process, the shape of the octahedral lattice unit can be achieved through precise model design and printing parameter control, thereby reducing defects in the manufacturing process. Specifically, the lattice unit 5 is made of titanium alloy, high-temperature alloy, aluminum alloy or stainless steel, and has the advantages of light weight, high temperature resistance, corrosion resistance and strong creep resistance; it has high strength and rigidity while maintaining light weight.

[0024] In some embodiments, a cooling layer 3 is further provided between the bottom plate 1 and the head compartment 7 .

[0025] Specifically, since the heat protection layer 2 and the bearing layer are integrated in the present application, the thickness of the heat protection component is reduced, thereby reducing the waste of space. Therefore, in order to further provide heat insulation protection for the head cabin 7, as shown in FIG. Figure 1 As shown, a cooling layer 3 is further provided between the bottom plate 1 and the head cabin 7. The cooling layer 3 effectively blocks the transfer of external high temperature to the inside of the head cabin 7 by controlling heat transfer, so that the temperature inside the cabin is kept within the range that the equipment and personnel can bear, ensuring the stability of the internal temperature, avoiding the internal structure deformation and material aging caused by high temperature, and protecting the structural integrity of the head cabin 7; Specifically, the cooling layer 3 works in coordination with the heat protection layer 2 to form a more reliable thermal protection system; when heat flux concentration occurs locally in the heat protection layer 2, the cooling layer 3 can perform heat regulation in a timely manner to avoid local overheating that may cause damage to the heat protection layer 2, thereby ensuring the safety of the internal equipment and structure of the head cabin 7.

[0026] In some embodiments, the cooling layer 3 is a grid heat dissipation structure, which includes a grid body, a pipeline is arranged in the grid body, and a cooling medium circulates inside the pipeline. In some embodiments, the pipeline is connected to a cooling system, and the cooling system is used to circulate the cooling medium into the pipeline.

[0027] Specifically, the cooling layer 3 is a grid heat dissipation structure, which has a larger surface area and can significantly improve the heat dissipation efficiency; a pipeline is arranged in the grid body, and the pipeline is connected to a cooling system, and the cooling system is used to circulate the cooling medium into the pipeline, so that the cooling medium takes away the heat transferred from the heat protection layer 2 to the cooling layer 3; Specifically, in this embodiment, the cooling layer 3 is produced by 3D printing, and the cooling layer 3 is usually made of materials with high thermal conductivity, such as aluminum alloy, nickel-based alloy and other materials; 3D printing technology can further optimize the shape and wall thickness of the structure, while ensuring the heat dissipation performance, while reducing the weight to the greatest extent.

[0028] In some embodiments, an aluminum foil layer 6 is provided between the cooling layer 3 and the bottom plate 1 , and the aluminum foil layer 6 is used to reduce heat radiation energy.

[0029] Specifically, thermal radiation is a way of heat transfer, which refers to the phenomenon that an object emits electromagnetic waves outward due to its own temperature; since the bottom plate 1 is made of metal material, in a high-temperature metal object, the outer electrons of the metal atoms will transition between different energy levels under the influence of thermal motion, thereby emitting thermal radiation; therefore, an aluminum foil layer 6 is arranged between the cooling layer 3 and the bottom plate 1, and the aluminum foil layer 6 has a high reflectivity to thermal radiation. When the thermal radiation energy is emitted from the bottom plate 1 toward the cooling layer 3, the aluminum foil layer 6 reflects most of the thermal radiation back like a mirror, thereby reducing the thermal radiation energy that can reach the cooling layer 3, effectively limiting the heat to one side of the cooling layer 3, and reducing the heat transfer toward the head cabin 7.

[0030] In some embodiments, an asbestos cushion layer 4 is provided between the cooling layer 3 and the head cabin 7 .

[0031] Specifically, in this embodiment, asbestos is an excellent heat-insulating material with a very low thermal conductivity, generally between 0.1-0.25W / (m·K); an asbestos cushion layer 4 is provided between the cooling layer 3 and the head cabin 7, which can further prevent heat from being transferred from the cooling layer 3 to the head cabin 7; at the same time, asbestos can maintain its heat-insulating performance at higher temperatures; it can withstand temperatures of up to thousands of degrees Celsius, which enables it to still play a heat-insulating role in the face of extremely high temperature environments, and can stably prevent heat from damaging the internal structure; Specifically, in this embodiment, according to the test simulation results, in this application, the thickness of the bottom plate 1 is set to 1 mm, the thickness of the lattice structure is set to 4 mm (the heat protection layer 2 is filled inside, so the thickness of the heat protection layer 2 is 4 mm), the thickness of the aluminum foil layer 6 is set to 0.2 mm, and the thickness of the cooling layer 3 is set to 4 mm, which can produce a good isolation effect for a general thermal environment; at the same time, an asbestos cushion layer 4 of more than 3 mm is set between the head cabin 7 and the cooling layer 3 to further enhance thermal isolation; if space permits, the heat insulation effect can be further enhanced by increasing the thickness of the heat protection layer 2 or increasing the circulation capacity of the cooling layer 3; Specifically, since the heat protection layer 2 and the bearing layer are prepared together in the present application to form an integrated heat protection system, the mass of the structure is reduced compared to the prior art, because the present application further provides a cooling layer 3, an aluminum foil layer 6 and an asbestos pad 4 to further enhance the heat insulation effect; at the same time, compared to the prior art, the overall mass is not increased, and while the heat insulation effect of the head cabin 7 is enhanced, the bearing capacity of the head cabin 7 is guaranteed.

[0032] The above description is only a preferred embodiment of the present application and an explanation of the technical principles used. Those skilled in the art should understand that the scope of the invention involved in the present application is not limited to the technical solution formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the inventive concept. For example, the above features are replaced with (but not limited to) technical features with similar functions disclosed in the present application.

Claims

1. A head cabin of an aircraft for use in a hypersonic environment, characterized in that: include: Head cabin (7); A heat protection component is provided on the outside of the head cabin (7), and the heat protection component is an integrated heat protection system; The thermal protection assembly comprises: A bearing layer, the bearing layer being connected to the head cabin (7); the bearing layer comprising: a bottom plate (1), a lattice structure being arranged on a side of the bottom plate (1) away from the head cabin (7), the lattice structure being composed of a plurality of lattice units (5), and first gaps being provided between the lattice units (5); A heat protection layer (2), the heat protection layer (2) being arranged on a side of the bearing layer away from the head cabin (7), and the heat protection layer (2) filling the first gap.

2. The aircraft head cabin for use in a hypersonic environment according to claim 1, characterized in that: The lattice unit (5) is an octahedral lattice unit, and a second gap (52) is provided inside the octahedral lattice unit; the octahedral lattice unit has eight planes, each plane is an equilateral triangle frame, and a vertex of one plane is fixedly connected to the bottom plate (1); the heat protection layer (2) is filled in the second gap (52).

3. The aircraft head cabin for use in a hypersonic environment according to claim 2, characterized in that: The lattice unit (5) is made of titanium alloy, high-temperature alloy, aluminum alloy or stainless steel.

4. The aircraft head cabin for use in a hypersonic environment according to claim 1, characterized in that: A cooling layer (3) is also provided between the bottom plate (1) and the head cabin (7).

5. The aircraft head cabin for use in a hypersonic environment according to claim 4, characterized in that: The cooling layer (3) is a grid heat dissipation structure, which comprises a grid body, a pipeline is arranged in the grid body, and a cooling medium circulates inside the pipeline.

6. The aircraft head cabin for use in a hypersonic environment according to claim 4, characterized in that: An aluminum foil layer (6) is provided between the cooling layer (3) and the bottom plate (1), and the aluminum foil layer (6) is used to reduce heat radiation energy.

7. The aircraft head cabin for use in a hypersonic environment according to claim 4, characterized in that: An asbestos cushion layer (4) is provided between the cooling layer (3) and the head cabin (7).

8. The aircraft head cabin for use in a hypersonic environment according to claim 5, characterized in that: The pipeline is connected to a cooling system, and the cooling system is used to circulate and transport the cooling medium into the pipeline.

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