Heat insulation device suitable for surface storage, take-off and rising of Mars

Abstract

The invention provides a heat insulation device suitable for surface storage and takeoff and rising of Mars. An outer carbon fiber skin serves as a secondary outer layer structure of the heat insulation device; the heat insulation assembly is arranged on the outer surface of the outer carbon fiber skin and serves as the outermost layer structure of the heat insulation device. The inner carbon fiber skin serves as the innermost layer structure of the heat insulation device. The network framework is arranged between the outer carbon fiber skin and the inner carbon fiber skin; the nano aerogel structure and the network skeleton are mutually nested and are jointly arranged between the outer carbon fiber skin and the inner carbon fiber skin; the nano aerogel structure is prepared from nano aerogel and mechanical enhanced foam, and the nano aerogel is aerogel based on silsesquioxane as a matrix. The thermal insulation device solves the problem of thermal insulation of the detector under the conditions of low air pressure, convective heat transfer conditions and seriously limited resources on the surface of Mars, and has the advantages of light weight, high thermal insulation efficiency, strong adaptability and low power consumption.

Description

Technical Field

[0001] This invention relates to the field of spacecraft thermal control technology, specifically to a thermal insulation device suitable for storage and takeoff on the surface of Mars, and more particularly to a super thermal insulation device suitable for storage and takeoff on the surface of Mars. Background Technology

[0002] With the development of aerospace technology, the breadth and depth of human deep space exploration have been continuously increasing. Mars exploration has become a popular target for extraterrestrial planet exploration. Compared with near-Earth space, Mars exploration is farther away, more difficult, and more resource-intensive.

[0003] Compared to near-Earth orbit spacecraft, the conditions for takeoff and ascent exploration on the Martian surface are far more severe. Mars possesses a gravitational field, a low-pressure atmosphere, wind speeds of up to approximately 20 m / s, and forced convection heat transfer, significantly increasing the difficulty of takeoff and ascent exploration. Constrained by stringent limitations in weight and power, Martian surface takeoff and ascent exploration requires efficient thermal insulation and temperature control within the Martian atmosphere while maintaining relatively low weight and power. Traditional multi-layered thermal insulation components and satellite module insulation methods are unsuitable for the Martian atmosphere, necessitating the development of a novel super-thermal insulation system to achieve high-precision temperature control during Martian surface takeoff and ascent. To this end, a super-thermal insulation device suitable for storage and takeoff / ascent on the Martian surface is proposed.

[0004] Patent document CN109004335A discloses a thermal control method for a large-aperture antenna suitable for Mars exploration, mainly describing the thermal control design measures for large-aperture antennas, belonging to the thermal control design of probes in Mars orbit. However, the technical solution of this patent document differs significantly from the technical solution of this invention.

[0005] Patent document CN114476139A discloses a thermal control design method for a Mars traveling wave tube assembly, focusing on the temperature control method for traveling wave tubes, which pertains to temperature control methods for probes in Mars orbit. However, the technical solution in this patent document differs significantly from the technical solution of this invention.

[0006] Patent document CN103482087A discloses a thermal control device for a Mars lander. This device mainly includes a thermal switch, electronic module, thermal insulation pad, phase change device, and heat dissipation surface, and is primarily used on landers. However, the thermal control device in this patent document differs significantly from the thermal insulation device of this invention.

[0007] Patent document CN108804836B discloses a thermal control design method for Mars exploration propulsion pipelines, mainly describing the thermal control design principles of Mars orbiter propulsion pipelines, the zoned heating design of the pipelines, the heating power of the pipelines, and the number of multi-layer coating layers of the pipelines. However, the technical solution of this patent document differs significantly from the technical solution of this invention.

[0008] Patent document CN107985629B discloses a Mars exploration method, including the orbital flight process of the probe from Earth to Mars and the monitoring of dust storms on Mars in different orbits. However, the technical solution of this patent document differs significantly from the technical solution of this invention. Summary of the Invention

[0009] In view of the deficiencies in the prior art, the purpose of this invention is to provide a heat insulation device suitable for storage and takeoff on the surface of Mars.

[0010] A thermal insulation device suitable for storage and takeoff on the surface of Mars, provided by the present invention, comprises:

[0011] The outer carbon fiber skin serves as the secondary outer layer structure of the thermal insulation device.

[0012] A thermal insulation component is disposed on the outer surface of the outer carbon fiber skin, serving as the outermost structure of the thermal insulation device.

[0013] The inner carbon fiber skin serves as the innermost layer of the thermal insulation device.

[0014] A network skeleton is disposed between the outer carbon fiber skin and the inner carbon fiber skin;

[0015] The nano-aerogel structure is nested with the network skeleton and is disposed together between the outer carbon fiber skin and the inner carbon fiber skin.

[0016] The nano-aerogel structure is made of nano-aerogel and mechanically reinforced foam, wherein the mechanically reinforced foam can be polyurethane foam or other similar materials. The nano-aerogel is an aerogel with silsesquioxane as the matrix, which is made by using silsesquioxane as raw material and forming a gel through a hydrolysis reaction.

[0017] Preferably, the interior of the nano-aerogel structure is shielded from infrared radiation by a gold-plated polyimide film.

[0018] Preferably, the density of the nano-aerogel structure is less than or equal to 10 kg / m³. 3 .

[0019] Preferably, the porosity of the nano-aerogel structure is greater than or equal to 99%.

[0020] Preferably, the thickness of the nano-aerogel structure is 20 mm.

[0021] Preferably, the thermal insulation component is a multi-layer thermal insulation component;

[0022] The two outermost layers of the multilayer thermal insulation component are nano-thermal control films, and each layer between the two outermost layers consists of a polyimide film and a high-silica cloth.

[0023] Preferably, the polyimide film is a double-sided aluminized polyester film, and the high-silica cloth is a nylon mesh.

[0024] Preferably, the thickness of the double-sided aluminized polyester film is 6μm, and the nylon mesh is T20-A nylon mesh.

[0025] Preferably, the outer carbon fiber skin and the inner carbon fiber skin are made of high-temperature resistant carbon fiber, which can withstand a high temperature of 200°C.

[0026] Preferably, the network skeleton is composed of magnesium alloy honeycomb.

[0027] The magnesium alloy honeycomb is filled with the nano-aerogel structure, and the magnesium alloy honeycomb is a through-hole structure.

[0028] Compared with the prior art, the present invention has the following beneficial effects:

[0029] 1. The heat insulation device of the present invention can block the convective and conductive heat transfer of the atmosphere, and is particularly suitable for heat insulation of Mars surface probes with atmosphere. It can be used not only for heat insulation on the surface of Mars, but also for heat insulation on the surface of other exoplanets.

[0030] 2. The heat insulation device of the present invention can adapt to the aerodynamic heating environment during the take-off and ascent process on the surface of Mars, and can withstand aerodynamic heating temperatures up to 200°C.

[0031] 3. The heat insulation device of the present invention has the advantages of excellent heat insulation effect, light weight, no slag shedding, and low power consumption. It can meet the temperature control requirements of detectors of different shapes, and the super heat insulation device is easy to manufacture.

[0032] 4. The heat insulation device of the present invention can adjust the surface emissivity according to the selection of different surface films, effectively adjust the heat leakage of the heat insulation device, achieve precise heat insulation effect, and effectively save heating resources. Attached Figure Description

[0033] 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:

[0034] Figure 1 This is a schematic diagram of the heat insulation device.

[0035] Figure 2 This is a schematic diagram of the nano-aerogel structure.

[0036] Figure 3 This is a schematic diagram of the network skeleton.

[0037] The diagram shows:

[0038] Thermal insulation component 1, mesh frame 4

[0039] Nano-aerogel structure 2, outer carbon fiber skin 5

[0040] Inner carbon fiber skin 3 Thermal insulation device 6 Detailed Implementation

[0041] 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.

[0042] Example 1

[0043] like Figures 1 to 3 As shown, this embodiment provides a heat insulation device suitable for storage and takeoff on the Martian surface, comprising: an outer carbon fiber skin 3, a heat insulation component 1, an inner carbon fiber skin 5, a network skeleton 4, and a nano-aerogel structure 2. The outer carbon fiber skin 3 serves as the second outermost layer structure of the heat insulation device 6; the heat insulation component 1 is disposed on the outer surface of the outer carbon fiber skin 3, serving as the outermost layer structure of the heat insulation device 6; the inner carbon fiber skin 5 serves as the innermost layer structure of the heat insulation device 6; the network skeleton 4 is disposed between the outer carbon fiber skin 3 and the inner carbon fiber skin 5; the nano-aerogel structure 2 is nested with the network skeleton 4 and is disposed together between the outer carbon fiber skin 3 and the inner carbon fiber skin 5; the nano-aerogel structure 2 is made of nano-aerogel 22 and mechanically reinforced foam 33, wherein the nano-aerogel 22 is an aerogel with silsesquioxane as the matrix.

[0044] Thermal insulation component 1 is a multi-layer thermal insulation component; the two outermost layers of the multi-layer thermal insulation component are nano-thermal control films, and each layer between the two outermost layers consists of a polyimide film and a high-silica fabric. The polyimide film is a double-sided aluminized polyester film, and the high-silica fabric is a nylon mesh. The thickness of the double-sided aluminized polyester film is 6μm, and the nylon mesh is T20-A nylon mesh.

[0045] The interior of nano-aerogel structure 2 is shielded from infrared radiation by a gold-plated polyimide film. The density of nano-aerogel structure 2 is less than or equal to 10 kg / m³. 3The porosity of nanoaerogel structure 2 is greater than or equal to 99%. The thickness of nanoaerogel structure 2 is 20 mm.

[0046] The outer carbon fiber skin 3 and the inner carbon fiber skin 5 are made of high-temperature resistant carbon fiber, which can withstand temperatures up to 200℃. The network skeleton 4 is composed of magnesium alloy honeycomb 44; the magnesium alloy honeycomb 44 is filled with nano-aerogel structure 2, and the magnesium alloy honeycomb 44 is through-pore.

[0047] This embodiment provides a super thermal insulation device suitable for storage and takeoff on the Martian surface. The device comprises a nano-aerogel metamaterial, a high-temperature resistant carbon fiber skin, multi-layer thermal insulation components, and a network skeleton. The novel nano-aerogel metamaterial is composed of micro-adjustable, ultra-lightweight nano-aerogel material, achieving super thermal insulation under the low atmospheric pressure of the Martian surface. The high-temperature resistant carbon fiber skin primarily protects against Martian dust and provides aerodynamic thermal protection. The multi-layer thermal insulation components allow for adjustment of the surface optical properties of the super thermal insulation device, and the network skeleton provides mechanical support. This embodiment solves the problem of thermal insulation for probes under conditions of low atmospheric pressure, convective heat transfer, and severely limited resources on the Martian surface, offering advantages such as light weight, high thermal insulation efficiency, strong adaptability, and low power consumption.

[0048] Example 2

[0049] Those skilled in the art can understand this embodiment as a more specific description of Embodiment 1.

[0050] This embodiment provides a super thermal insulation device suitable for storage and takeoff on the Martian surface, which is composed of nano-aerogel metamaterials, high-temperature resistant carbon fiber skin, multi-layer thermal insulation components and network skeleton.

[0051] Furthermore, the nanoaerogel metamaterial is composed of micro-tuned, ultra-lightweight nanoaerogel materials.

[0052] Furthermore, the surface of the nano-aerogel metamaterial is micro-adjusted to prevent flaking.

[0053] Furthermore, the interior of the nano-aerogel metamaterial is protected against infrared radiation by a gold-plated polyimide film.

[0054] Furthermore, the density of the nano-aerogel metamaterial is no greater than 10 kg / m³. 3 .

[0055] Furthermore, the porosity of the nano-aerogel material is not less than 99%.

[0056] Furthermore, the high-temperature resistant carbon fiber skin can be designed in a cylindrical shape, or other shapes.

[0057] Furthermore, the high-temperature resistant carbon fiber skin is installed in 32 sections, and the number of sections can be varied.

[0058] Furthermore, the high-temperature resistant carbon fiber skin can withstand temperatures up to 200°C.

[0059] Furthermore, the number of layers in the multilayer thermal insulation component can be designed as needed. The outermost layer of the multilayer is a white nanofilm, and each of the middle layers consists of a polyimide film and a high-silica cloth.

[0060] Furthermore, the network skeleton is constructed using an optimized high-temperature resistant cellular network, which can reduce local heat leakage.

[0061] This embodiment addresses the challenge of achieving high-precision temperature control for Mars surface-launching probes, which face constraints such as harsh Martian environment, light weight, low power consumption, short development cycle, and high temperature control accuracy. Traditional thermal insulation methods are difficult to implement, yet the thermal control system still requires high precision. To solve this problem, this embodiment proposes a super-insulated device suitable for storage and launch / ascent on the Martian surface.

[0062] Nano-aerogel metamaterials are installed in the spacer layer of a high-temperature resistant carbon fiber skin, embedded in the middle of a network skeleton. The high-temperature resistant carbon fiber skin consists of two layers, an inner layer installed inside the network skeleton, and an outer layer installed outside the network skeleton. Multi-layer thermal insulation components are installed on the outer surface of the outer layer of the high-temperature resistant carbon fiber skin. The network skeleton, as the main load-bearing component, is installed between the two layers of high-temperature resistant carbon fiber skin.

[0063] Example 3

[0064] Those skilled in the art can understand this embodiment as a more specific description of Embodiment 1 and Embodiment 2.

[0065] like Figure 1 As shown, this embodiment provides a super thermal insulation device suitable for storage and takeoff on the surface of Mars, including nano-aerogel metamaterials, high-temperature resistant carbon fiber skin, multi-layer thermal insulation components and network skeleton 4.

[0066] Each layer of the multi-layer thermal insulation component includes a double-sided aluminized polyester film and a nylon mesh, with the outermost layer being a nano-thermal control film. The nano-aerogel metamaterial is composed of micro-adjustable ultra-lightweight nano-aerogel material and mechanically reinforced foam 33. The high-temperature resistant carbon fiber skin is the innermost supporting structure. The network skeleton 4 and the nano-aerogel metamaterial are nested together and installed between the multi-layer thermal insulation component and the high-temperature resistant carbon fiber skin.

[0067] The multi-layer thermal insulation component consists of 15 layers, each consisting of a top layer of 6μm double-sided aluminized polyester film and a bottom layer of T20-A nylon mesh, with the outermost layer being a nano-thermal control film.

[0068] The nano-aerogel metamaterial is composed of micro-adjustable ultra-lightweight nano-aerogel material and mechanically reinforced foam 33, with a thickness of 20mm. The micro-adjustable ultra-lightweight nano-aerogel material uses aerogel based on silsesquioxane as the matrix to achieve the effects of lightweight, ultra-low thermal conductivity and no flaking, thus achieving ultra-high thermal insulation performance.

[0069] The high-temperature resistant carbon fiber skin is made of high-temperature resistant carbon fiber and has the characteristics of high temperature resistance, mild temperature and low thermal conductivity.

[0070] The network skeleton 4 is composed of magnesium alloy honeycomb 44, which is filled with a new type of nano-aerogel metamaterial. The magnesium alloy honeycomb is through-hole to ensure that air can be released, thereby providing mechanical support for the entire super thermal insulation material.

[0071] This invention solves the problem of heat insulation for probes under conditions of low atmospheric pressure, convective heat transfer, and severe resource constraints on the Martian surface. It has the advantages of being lightweight, having high heat insulation efficiency, strong adaptability, and low power consumption.

[0072] 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.

[0073] 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-insulating device suitable for storage and takeoff on the surface of Mars, characterized in that, include: The outer carbon fiber skin (3) serves as the outermost layer structure of the thermal insulation device; The heat insulation component (1) is disposed on the outer surface of the outer carbon fiber skin (3) as the outermost structure of the heat insulation device; Inner carbon fiber skin (5) serves as the innermost layer of the insulation device; A network skeleton (4) is disposed between the outer carbon fiber skin (3) and the inner carbon fiber skin (5); The nano-aerogel structure (2) is nested with the network skeleton (4) and is disposed between the outer carbon fiber skin (3) and the inner carbon fiber skin (5); The nano-aerogel structure (2) is made of nano-aerogel (22) and mechanically reinforced foam (33), wherein the nano-aerogel (22) is an aerogel with sesquioxane as the matrix.

2. The heat insulation device suitable for storage and takeoff on the Martian surface according to claim 1, characterized in that, The interior of the nano-aerogel structure (2) is shielded from infrared radiation by a gold-plated polyimide film.

3. The heat insulation device for storage and takeoff on the Martian surface according to claim 1, characterized in that, The density of the nano-aerogel structure (2) is less than or equal to 10 kg / m³. 3 .

4. The heat insulation device suitable for storage and takeoff on the surface of Mars according to claim 1, characterized in that, The porosity of the nano-aerogel structure (2) is greater than or equal to 99%.

5. The heat insulation device for storage and takeoff on the surface of Mars according to claim 1, characterized in that, The thickness of the nanoaerogel structure (2) is 20 mm.

6. The heat insulation device for storage and takeoff on the surface of Mars according to claim 1, characterized in that, The thermal insulation component (1) is a multi-layer thermal insulation component; The two outermost layers of the multilayer thermal insulation component are nano-thermal control films, and each layer between the two outermost layers consists of a polyimide film and a high-silica cloth.

7. The thermal insulation device for storage and takeoff on the Martian surface according to claim 6, characterized in that, The polyimide film is a double-sided aluminized polyester film, and the high-silica cloth is a nylon mesh.

8. The thermal insulation device for storage and takeoff on the Martian surface according to claim 7, characterized in that, The thickness of the double-sided aluminized polyester film is 6μm, and the nylon mesh is T20-A nylon mesh.

9. The heat insulation device for storage and takeoff on the surface of Mars according to claim 1, characterized in that, The outer carbon fiber skin (3) and the inner carbon fiber skin (5) are made of high-temperature resistant carbon fiber, which can withstand a high temperature of 200°C.

10. The thermal insulation device for storage and takeoff on the surface of Mars according to claim 1, characterized in that, The network skeleton (4) is composed of magnesium alloy honeycomb (44); The magnesium alloy honeycomb (44) is filled with the nano aerogel structure (2), and the magnesium alloy honeycomb (44) is a through-hole structure.

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