Heat prevention and insulation structure of aircraft base body and aircraft base body

Abstract

The invention provides a heat prevention and insulation structure of an aircraft base body and the aircraft base body, and belongs to the technical field of aircraft heat prevention and insulation. The heat insulation structure comprises a flexible connecting layer covering the surface of the aircraft base body; the heat insulation units are located on the flexible connecting layer, the first ends of the heat insulation units are connected with the flexible connecting layer, and the heat insulation units are arranged at intervals; the plurality of armor flakes are positioned on the heat insulation units and are in one-to-one correspondence with the plurality of heat insulation units, and the second ends of the heat insulation units are connected with the armor flakes; the reflecting coating covers the upper surfaces and the side surfaces of the armor flakes; the armor flakes on the adjacent heat insulation units are partially overlapped in a one-by-one pressing mode, and the tail portion of the front armor flake in every two adjacent armor flakes is in lap joint with the head portion of the rear armor flake, so that a stacked structure of the flakes is formed. According to the heat prevention and insulation structure, a labyrinth type heat flow transfer path is constructed, heat resistance is increased, and heat insulation efficiency is improved.

Description

Technical Field

[0001] This invention relates to the field of aircraft heat insulation technology, specifically to a heat insulation structure for an aircraft substrate and an aircraft substrate. Background Technology

[0002] Traditional aircraft thermal insulation structures are gradually revealing their inherent limitations when facing increasingly complex force-thermal coupling conditions, mainly in the following aspects: (1) The heat insulation mechanism is simple and difficult to cope with complex and ever-changing thermal environments. Existing solutions often focus on utilizing single or limited thermal protection principles. For example, reflective insulation primarily targets radiative heat, with limited effectiveness against conductive and convective heat; ablation insulation only works at ultra-high temperatures and is a one-time consumption; thermal insulation (such as using ceramic fiber felt) relies on the low thermal conductivity of the material, but is easily broken down under high heat flux impacts; active cooling systems are complex in structure and energy-intensive. More commonly, one or more of the above mechanisms are simply combined with heat sink structures. This "each fighting its own battle" design approach makes it difficult for existing structures to achieve full-spectrum, high-efficiency thermal management when facing complex thermal loads (such as high radiation, strong aerodynamic heating, and alternating or simultaneous ultra-high temperatures, or alternating force thermal coupling loads). Under strict weight and thickness limitations, their overall thermal insulation performance has approached theoretical limits.

[0003] (2) The structure is highly integrated, but local damage can lead to the failure of the entire system, resulting in poor economic efficiency. Currently widely used heat insulation structures, such as integral heat insulation tiles, sintered integral ablation bodies, or one-piece molded heat insulation linings, are essentially inseparable functional units. In practical use, due to foreign object impacts, installation stress, concentrated thermal stress, or localized overheating, certain areas of the structure are prone to ablation, cracking, or peeling. Such minor localized damage necessitates the replacement of the entire heat insulation structure. This not only results in significant material waste and high maintenance costs but also makes this type of structure essentially a "disposable" or "short-life" design, severely limiting its life-cycle economics and restricting its application prospects in reusable equipment.

[0004] (3) The configuration is rigid and fixed, lacking scene adaptability and design flexibility. Traditional monolithic thermal insulation structures typically have their shape and dimensions fixed after manufacturing. When applied to equipment with complex curved surfaces (such as irregularly shaped aircraft sections or engine components), they often suffer from poor fit and numerous seams. This not only affects the aerodynamic shape but also creates thermal short-circuit paths at the seams, posing safety hazards. Furthermore, for different mission requirements or equipment platforms, almost always a "tailor-made" redesign and manufacturing is required. There is a lack of a universal, modular solution that can be flexibly assembled to adapt to various application scenarios, greatly limiting its ability to expand its application scope and deploy rapidly.

[0005] (4) It is difficult to balance thermal protection performance and mechanical load-bearing performance, and the adaptability to the force-thermal coupling environment is insufficient. High-performance thermal insulation materials (such as lightweight porous ceramics and aerogels) typically have weak mechanical properties and inherent brittleness. The metal or composite material skeletons introduced to enhance structural rigidity often become "highways" for heat conduction, creating thermal bridging effects. Existing structures often compromise between these two: either sacrificing mechanical strength and impact toughness to ensure insulation efficiency, leading to structural damage under vibration, overload, or mechanical impact; or sacrificing some insulation performance to meet load-bearing requirements. Alternatively, thermal insulation and mechanical properties are designed separately, with each requirement met individually before mechanical integration. This increases system complexity and leads to increased weight and size. This contradiction between thermo-mechanical properties makes existing thermal insulation structures the weakest link and a major technical challenge in extreme force-thermal coupling environments that simultaneously demand high strength, high toughness, and superior insulation capabilities. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to provide a heat insulation structure for an aircraft substrate and an aircraft substrate, which increases thermal resistance and improves heat insulation efficiency by constructing a labyrinthine heat flow transfer path.

[0007] To solve the above-mentioned technical problems, the technical solution of the present invention is as follows: This invention provides a layered composite thermal management armor heat insulation structure for an aircraft substrate, comprising: A flexible connection layer covering the surface of the aircraft substrate; Multiple heat insulation units are located on the flexible connecting layer, with the first end of each heat insulation unit connected to the flexible connecting layer, and the multiple heat insulation units are arranged with gaps between them; Multiple armor scales are located on the heat insulation unit and correspond one-to-one with the multiple heat insulation units. The second end of the heat insulation unit is integrally connected to the armor scales, and the armor scales are made of ablative material. A reflective coating covers the upper surface and visible side surfaces of the armor scales; The armor scales on adjacent insulation units partially overlap one on top of the other, with the tail of the first armor scale overlapping the head of the second armor scale in two adjacent armor scales, forming a layered structure of scales.

[0008] Optionally, the flexible connection layer is a continuous flexible connection plate or a distributed flexible connector.

[0009] Optionally, the flexible connecting layer is at least one of silicone rubber, flexible ceramic fiber felt, metal spring mesh, and elastic support.

[0010] Optionally, the insulation unit is a vacuum cavity or a non-vacuum insulation body.

[0011] Optionally, the vacuum cavity is at least one of a vacuum cylinder, a vacuum square cylinder, a vacuum hexagonal prism, and a vacuum cylinder with an irregular cross-section.

[0012] Optionally, the non-vacuum insulation body is a column whose inner cavity is filled with nanoporous aerogel blocks or microbubble glass as the insulation core.

[0013] Optionally, the armor scales are at least one of elongated ellipse, hexagon, fan-shaped, and rounded rectangle.

[0014] Optionally, the ablation material is a carbon / phenolic composite material or a ceramic / phenolic composite material.

[0015] Optionally, the reflective coating is at least one of aluminum foil, silver coating, and ceramic coating.

[0016] Secondly, the present invention provides an aircraft substrate, the surface of which is covered with the above-mentioned heat insulation structure.

[0017] The above-described solution of the present invention has at least the following beneficial effects: The above-described solution of the present invention utilizes a flexible connecting layer applied to the surface of the aircraft substrate; multiple heat insulation units located on the flexible connecting layer, with the first end of each heat insulation unit connected to the flexible connecting layer and the multiple heat insulation units arranged with gaps between them; multiple armor scales located on the heat insulation units and corresponding one-to-one with each heat insulation unit, with the second end of each heat insulation unit integrally connected to the armor scales, the armor scales being made of ablative material; a reflective coating covering the upper and side surfaces of the armor scales; and the armor scales on adjacent heat insulation units partially overlapping in a one-on-one manner, with the tail of the preceding armor scale overlapping the head of the following armor scale in two adjacent armor scales, forming a layered structure of scales that constructs a labyrinthine heat flow transfer path, increasing thermal resistance and improving heat insulation efficiency. Attached Figure Description

[0018] Figure 1This is a schematic diagram of the heat insulation structure of the aircraft substrate of the present invention; Figure 2 This is a cross-sectional view of the heat insulation structure of the aircraft substrate of the present invention.

[0019] Explanation of reference numerals in the attached figures: 1-Flexible connecting layer; 2-Insulation unit; 3-Armor scales; 4-Reflective coating. Detailed Implementation

[0020] Exemplary embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0021] like Figure 1 and Figure 2 As shown, an embodiment of the present invention proposes a heat-insulating structure for an aircraft substrate, comprising: The flexible connection layer 1, which is applied to the surface of the aircraft substrate, is used to contact or connect with the surface of the equipment substrate that needs to be protected. The equipment substrate refers to any load-bearing structure whose structural integrity or internal function may be threatened by the external high temperature environment, such as the skin and frame of a hypersonic vehicle, the rocket engine section, and the bulkhead of a space return capsule. Multiple heat insulation units 2 are located on the flexible connecting layer 1, with the first end of each heat insulation unit 2 connected to the flexible connecting layer 1, and the multiple heat insulation units 2 are arranged with gaps between them; Multiple armor scales 3 are located on the heat insulation unit 2 and correspond one-to-one with the multiple heat insulation units 2. The second end of the heat insulation unit 2 is integrally connected to the armor scales 3. The armor scales 3 are made of ablation material. One heat insulation unit 2 is integrally connected with one corresponding armor scale 3 to form a heat insulation module. The flexible connection layer 1 includes multiple such heat insulation modules. A reflective coating 4 is applied to the upper surface and visible side surfaces of the armor scales 3. In this embodiment, a heat insulation unit 2 and a corresponding armor scale 3 and its reflective coating 4 form a single independent heat insulation unit. Multiple such independent heat insulation units exist on the flexible connecting layer 1. The multiple independent heat insulation units are arranged in a gap on the flexible connecting layer 1. The heat insulation units are interconnected through the flexible connecting layer 1 to form a discontinuous structural whole. The armor scales 3 on adjacent heat insulation units 2 partially overlap one on top of the other, with the tail of the first armor scale 3 overlapping the head of the second armor scale in two adjacent armor scales 3, forming a layered structure of scales.

[0022] For example, the flexible connection layer 1 is a continuous flexible connection plate or a distributed flexible connector. The continuous flexible connection plate connects multiple heat insulation units 2 to one flexible connection plate; the distributed flexible connector provides a flexible connector for each heat insulation unit 2, and the flexible connector acts like an "anchor point" to directly connect each heat insulation unit 2 to the substrate.

[0023] The flexible connecting layer 1 serves as the mounting base for the entire structure and is made of a high-temperature resistant and highly elastic flexible material. For example, the flexible connecting layer 1 is at least one of silicone rubber, flexible ceramic fiber felt, metal spring mesh, and elastic bracket.

[0024] For example, the heat insulation unit 2 is a vacuum cavity or a non-vacuum heat insulation body, preferably a vacuum cavity. This invention flexibly connects multiple independent heat insulation units in a discontinuous manner, and integrates reflection, ablation, and vacuum insulation mechanisms in each heat insulation unit to collaboratively cope with thermal loads.

[0025] For example, the vacuum cavity is at least one of a vacuum cylinder, a vacuum square cylinder, a vacuum hexagonal prism, and a vacuum cylinder with an irregular cross-section, preferably a vacuum cylinder, i.e. a cylindrical vacuum cavity.

[0026] For example, the vacuum cylinder is made by evacuating a high-barrier metal or ceramic encapsulation film, and its interior can be filled with a porous core material. The heat insulation unit 2 is regularly fixed to the flexible connecting layer 1 in a predetermined manner with gaps, and each heat insulation unit 2 constitutes an independent miniature high-efficiency heat insulation support.

[0027] For example, the non-vacuum insulation body is a column filled with nanoporous aerogel blocks or microbubble glass as the insulation core.

[0028] For example, the plurality of the heat insulation units 2 are arranged in a matrix.

[0029] For example, the armor scales 3 are slightly curved sheet-like structures, formed by molding or machining from high-strength ablation material. The armor scales 3 are connected to the top of the heat insulation unit 2 below through specific connection points on their lower surface. Adjacent armor scales 3 overlap partially to form a layered structure. This partially overlapping overlap creates a long and tortuous heat flow path to increase thermal resistance. Simultaneously, this partially overlapping overlap also forms a mechanical load transmission path to diffuse localized loads into overall load-bearing capacity.

[0030] The overlap area between adjacent armor scales 3 is optimized for thermal performance while ensuring minimum structural strength. The method for determining the overlap area between adjacent armor scales 3 is as follows: ① Calculate the minimum mechanical area A.min Based on the ultimate load borne by armor scale 3 and the allowable stress of the material, calculate the minimum required overlap area A to ensure structural integrity. min A min = Ultimate load / Allowable material stress; ② Optimize effective heat flow path L eff : During the design, the shape of the overlapping area should force the heat flow to detour. For example, the overlapping area between adjacent armor scales 3 is preferably a long and thin strip, forming a path that is as long and tortuous as possible; ③ Determine the final overlapping area A over In A over ≥A min Within the range, select the one that enables L eff / A over The design with the highest ratio.

[0031] For example, the armor scales 3 are at least one of elongated ellipse, hexagon, fan shape and rectangle with rounded corners, preferably elongated ellipse.

[0032] The overlapping form between the armor scales 3 can be adaptively changed according to the situation. For example, the armor scales 3 can be intelligent adaptive scales. Specifically, a driving element made of shape memory alloy is integrated at the connection of the armor scales 3. As long as the design can achieve the overlapping of "one scale on top of another" to form a heat flow labyrinth and load diffusion path, it is acceptable.

[0033] The driving element is made of shape memory alloy. Its function is as follows: when the ambient temperature is below the phase transition point of the shape memory alloy, the driving element is in the first state, and the armor scales 3 remain tightly overlapped; when the ambient temperature rises and exceeds the phase transition point of the shape memory alloy, the driving element is stimulated to recover its shape, transforming into the second state, and driving the armor scales 3 to displace, thus forming a heat dissipation gap between adjacent armor scales 3. The driving element enables the overall structure to have adaptive thermal management capabilities.

[0034] For example, the ablation material is a carbon / phenolic composite material or a ceramic / phenolic composite material.

[0035] The reflective coating 4 is a functional layer with high reflectivity. For example, the reflective coating 4 is at least one of aluminum foil, silver coating and ceramic coating.

[0036] The armor scales 3 and reflective coating 4 of the present invention can be functionally integrated composite scales, specifically, the armor scales 3 themselves are composed of "metal substrate + surface reflective coating".

[0037] The heat insulation structure of the aircraft substrate of this invention is a clearly layered structure consisting of a reflective coating 4, an ablation layer of armor scales 3, and a vacuum heat insulation layer of the heat insulation unit 2. It can be a two-level or multi-level modular combination. Two-level modular combination: first, the reflective coating 4 and armor scales 3 are combined into an "outer shell module", and then it is connected to the heat insulation unit 2 and the flexible connecting layer 1. Multi-level modular combination: first, the flexible connecting layer 1, the heat insulation unit 2, the armor scales 3 and the reflective coating 4 are combined into small unit modules, multiple small unit modules are assembled into a standard medium unit module, and multiple medium unit modules are assembled into a larger area.

[0038] This invention achieves a synergistic improvement in thermal protection and mechanical load-bearing performance through the aforementioned specific structure. Its working principle is as follows: 1. Thermal management principle (labyrinth-type heat flow channel): (1) First line of defense (reflection): The radiant heat from the outside is first reflected back in large quantities by the reflective coating 4 on the surface of the armor scales 3; (2) Second line of defense (ablation and thermal resistance): The residual heat that is not reflected is conducted to the ablation material body of the armor scale 3. The material undergoes endothermic reactions such as decomposition and carbonization at extreme high temperatures, consuming a large amount of heat. At the same time, when the heat is conducted inside the scale body, it is forced to go through a longer and more tortuous path due to the overlapping interface between the scales, forming a "maze-like" heat flow channel, which significantly increases the thermal resistance.

[0039] (3) The third line of defense (vacuum insulation): The small amount of heat that finally penetrates the armor scales 3 reaches the insulation unit 2. Through the vacuum environment inside the unit, the convective and conductive heat transfer of the gas is almost completely eliminated, thus achieving the ultimate blockage of heat.

[0040] Through the multi-principle synergy and step-by-step attenuation of the above three lines of defense, efficient management of the entire thermal load spectrum is achieved.

[0041] 2. Principle of mechanical bearing capacity (overall bearing capacity of force): (1) Load diffusion: When an external mechanical load (such as impact or shear force) is applied to a certain armor scale 3, the load will be quickly transferred to multiple adjacent armor scales through its overlapping relationship of "one scale pressing on another".

[0042] (2) Stress homogenization: This force transmission path transforms the local concentrated load into a distributed load borne by multiple insulation units 2, and finally diffuses it to the entire equipment substrate through the flexible connection layer 1. This design greatly improves the overall load-bearing efficiency and impact resistance of the structure.

[0043] (3) Functional decoupling: The thermal insulation unit 2 mainly bears compressive stress, while the armor scales 3 mainly bear out-of-plane impact and shear force, realizing a reasonable distribution of mechanical functions and avoiding a single component to cope with complex stress at the same time.

[0044] The thermal insulation structure of the aircraft substrate of the present invention exhibits excellent adaptive characteristics under dynamic operating conditions: (1) Adaptive thermal deformation: When the structure is heated unevenly, the components in different areas will expand thermally. The overlapping surfaces between adjacent armor scales 3 allow for slight relative sliding between them. At the same time, the flexible connection layer 1 can absorb this part of the differential thermal stress through its own elastic deformation, thereby effectively preventing the entire structure from warping, cracking or debonding due to uneven thermal expansion, and ensuring the integrity of the thermal seal.

[0045] (2) Adaptive Curved Surface Fit: When this layered composite thermal management armor insulation structure needs to be installed on a complex curved surface, the flexible connecting layer 1 can undergo a large range of bending deformation. At the same time, the gap between each independent insulation unit provides space for this deformation, allowing the insulation unit 2 of each unit to adaptively adjust its angle, ensuring that all armor scales 3 can still maintain the preset overlapping relationship, tightly fit the substrate surface, and will not have protective gaps due to bending.

[0046] (3) Damage isolation and maintainability: Any independent heat insulation unit (such as one damaged by ultra-high temperature ablation or external impact) can be regarded as an isolated module. During maintenance, it is only necessary to disconnect the damaged unit from its connection with the flexible connection layer 1 and replace it with a new heat insulation unit, without having to replace the entire heat insulation system, thus achieving low-cost and high-efficiency maintenance.

[0047] The modular, reusable, high-performance thermal management armor heat insulation structure provided by the above-described solution of the present invention is as follows: (1) In terms of functional integration and thermal management efficiency, this invention adopts a multi-principle dynamic synergy mode: by combining reflective coating, armor scales and thermal insulation unit, reflection, ablation and vacuum insulation are integrated into one, forming an orderly and synergistic active thermal management defense system. It achieves the performance of "active thermal management", has a strong ability to cope with the full spectrum of dynamic heat loads, and has a high limit of comprehensive thermal insulation efficiency.

[0048] (2) In terms of maintainability and economy, the present invention adopts a modular design and partial replacement: multiple independent heat insulation units composed of armor scales and heat insulation units allow for quick and low-cost partial replacement without scrapping the overall structure, which greatly improves reusability and significantly reduces the cost throughout the life cycle, laying a technical foundation for reusable equipment.

[0049] (3) In terms of environmental adaptability and reliability, the present invention adopts a flexible connection with strong self-adaptability: through the discontinuous design of the flexible connection layer and the thermal insulation unit, it can absorb thermal stress, fit complex curved surfaces, and greatly improve reliability. It fundamentally solves the problem of thermal stress, expands the application range, and can maintain stable and reliable performance under dynamic deformation and complex interfaces.

[0050] (4) In terms of balancing mechanical and thermal insulation performance, the present invention can achieve “integrated win-win”: the armor scales are responsible for bearing and diffusing loads, and the thermal insulation unit (such as the vacuum thermal insulation unit) is responsible for thermal insulation. The structure avoids the direct overlap of the bearing and thermal insulation paths, solves the thermal bridge problem, and achieves the unity of excellent mechanical bearing and ultra-efficient thermal insulation at the structural level for the first time, rather than a simple compromise and trade-off. It is particularly suitable for extreme force and heat coupling environments.

[0051] (5) In terms of damage tolerance, the local damage of the present invention can be isolated: any damage is strictly limited to a single independent unit composed of armor scales and heat insulation unit, and cannot be expanded, which ensures the safety of the overall structure, greatly improves the damage tolerance and safety reliability of the structure, and realizes the robust design of "small damage does not break, and damage does not paralyze".

[0052] The thermal management method of the above-mentioned heat-insulating structure of the present invention includes: The incoming radiant heat is first largely reflected back by the reflective coating 4 on the surface of the armor scales 3; The residual heat that is not reflected is conducted to the ablation material body of the armor scale 3. The ablation material undergoes decomposition and carbonization endothermic reaction at extreme high temperature, consuming a large amount of heat. At the same time, when the heat is conducted inside the body of the armor scale 3, it is forced to go through a long and tortuous path due to the overlapping interface between the armor scales 3, forming a "maze-like" heat flow channel. The small amount of heat that eventually penetrates the armor scales 3 reaches the heat insulation unit 2. The heat insulation unit 2 eliminates convective and conductive heat transfer of the gas through its internal vacuum environment or heat insulation core, thus achieving the ultimate blockage of heat.

[0053] This invention provides a modular, reusable, high-performance thermal management armor structure. Its core lies in a rigid-flexible, multi-principle synergistic modular architecture. This structure aims to achieve efficient thermal management across the entire spectrum through a multi-principle synergistic integrated hierarchical design; to achieve partial replaceability and high reusability through miniaturized, modular independent thermal insulation units; to provide an intelligent thermal insulation system with flexible shape and adaptive working surface through the combination of flexible connecting layer 1 and independent units; and to achieve both excellent thermal barrier properties and outstanding mechanical protection capabilities through a layered armor configuration of "one piece on top of another," thus enabling reliable application in complex, variable, and harsh force-thermal coupling environments.

[0054] This invention provides a novel heat-insulating structure suitable for aircraft substrates from three levels: design concept, structural form, and system integration. Specifically, it is embodied in: (1) Multi-principle synergistic systematic thermal management architecture: An orderly and synergistic defense system is constructed by using a reflective coating 4, a stacked armor scale 3, and interspersed thermal insulation units 2, which consists of a "reflective layer" (for radiative heat), an "ablation layer" (for ultra-high temperature), and a "vacuum array layer" (for isolating conduction and convection heat). This system can adaptively cope with the full spectrum of dynamically changing thermal loads and achieve the performance of "active thermal management".

[0055] (2) Modular and discontinuous structural form: Breaking away from the traditional mindset of integral structure, the armor scales 3 are not fixedly connected, but adopt a layered overlapping structure, with the heat insulation units 2 arranged in gaps. This decomposes the heat insulation function into multiple independent and unitized heat insulation units composed of heat insulation units 2, armor scales 3 and reflective coating 4. This discontinuous design is one of the core features of the present invention. It provides a physical basis for local damage repair and local replacement, thereby greatly improving the maintainability, reusability and life-cycle economy of the structure.

[0056] (3) The rigid-flexible mechanical-thermal decoupling design: By introducing a flexible connecting layer 1, the independent rigid heat insulation units composed of heat insulation unit 2, armor scales 3 and reflective coating 4 are connected into a whole. This design cleverly decouples thermal stress and mechanical constraints, giving the overall structure excellent shape self-adaptability, enabling it to conform to complex curved surfaces, while effectively buffering external impacts.

[0057] (4) Armor-like configuration with integrated structure and function: The original "one piece pressing on another piece" layered armor configuration is proposed, which not only constructs a maze-like heat flow transfer path, increases thermal resistance, and improves heat insulation efficiency, but also provides an efficient mechanical design mode: the armor scales 3 adopt a "one piece pressing on another piece" layered structure. When an external mechanical load is applied to a certain armor scale 3, the load will be quickly transferred to multiple adjacent armor scales 3 through its "one piece pressing on another piece" overlapping relationship, effectively dispersing the local impact load into overall stress. Thus, without introducing independent thermal bridge components, excellent mechanical protection performance and extraordinary heat insulation effect are achieved simultaneously, fundamentally solving the contradiction between mechanical load-bearing capacity and heat insulation performance.

[0058] The "modular, discontinuous, multi-principle synergy, and rigid-flexible" design concept of this invention represents a fundamental breakthrough from the traditional "integral, continuous, and functionally composite" sandwich structure design paradigm. It not only excels in individual performance aspects (such as thermal insulation and load-bearing capacity), but more importantly, it achieves a qualitative leap in key indicators that determine the practical and commercial value of the technology, including maintainability, economy, environmental adaptability, and safety. This provides a disruptive solution for next-generation reusable aerospace equipment and high-end thermal protection.

[0059] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A heat-insulating structure for an aircraft substrate, characterized in that, include: A flexible connection layer (1) is applied to the surface of the aircraft substrate. Multiple heat insulation units (2) are located on the flexible connecting layer (1), with the first end of each heat insulation unit (2) connected to the flexible connecting layer (1), and the multiple heat insulation units (2) are arranged with gaps between them; Multiple armor scales (3) are located on the heat insulation unit (2) and correspond one-to-one with the multiple heat insulation units (2). The second end of the heat insulation unit (2) is integrally connected to the armor scales (3). The armor scales (3) are made of ablation material. A reflective coating (4) is applied to the upper and side surfaces of the armor scales (3); The armor scales (3) on adjacent heat insulation units (2) partially overlap one on top of the other, and the tail of the first armor scale (3) overlaps the head of the second armor scale in two adjacent armor scales (3), forming a layered structure of scales.

2. The heat-insulating structure of the aircraft substrate according to claim 1, characterized in that, The flexible connection layer (1) is a continuous flexible connection plate or a distributed flexible connector.

3. The heat-insulating structure of the aircraft substrate according to claim 1, characterized in that, The flexible connecting layer (1) is at least one of silicone rubber, flexible ceramic fiber felt, metal spring mesh, and elastic support.

4. The heat-insulating structure of the aircraft substrate according to claim 1, characterized in that, The heat insulation unit (2) is a vacuum cavity or a non-vacuum heat insulation body.

5. The heat-insulating structure of the aircraft substrate according to claim 4, characterized in that, The vacuum cavity is at least one of the following: a vacuum cylinder, a vacuum square cylinder, a vacuum hexagonal prism, and a vacuum cylinder with an irregular cross-section.

6. The heat-insulating structure of the aircraft substrate according to claim 4, characterized in that, The non-vacuum insulation material consists of nanoporous aerogel blocks or microbubble glass filling the inner cavity of the column as the insulation core.

7. The heat-insulating structure of the aircraft substrate according to claim 1, characterized in that, The armor scales (3) are at least one of the following: elongated ellipse, hexagon, fan-shaped, and rounded rectangle.

8. The heat-insulating structure of the aircraft substrate according to claim 1, characterized in that, The ablation material is a carbon / phenolic composite material or a ceramic / phenolic composite material.

9. The layered composite thermal management armor heat insulation structure according to claim 1, characterized in that, The reflective coating (4) is at least one of aluminum foil, silver coating and ceramic coating.

10. An aircraft base, characterized in that, The surface of the aircraft substrate is covered with a heat-insulating structure as described in any one of claims 1 to 9.

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