Self-adaptive heat insulation assembly based on electrostatic suspension and graphene aerogel

Abstract

The invention discloses an intelligent self-adaptive multi-layer heat insulation assembly applied to spacecraft heat control and based on electrostatic suspension and graphene aerogel. The intelligent self-adaptive multi-layer heat insulation assembly comprises an intelligent color-changing outer protection layer, a stacked reflection layer, an electrostatic suspension control system and other core structures. Interlayer non-contact suspension of the assembly is realized through electrostatic repulsion, and solid contact heat conduction is eliminated; the graphene aerogel supporting frame is used as a standby support and has ultralow thermal conductivity; the intelligent color changing layer can dynamically switch heat preservation / heat dissipation states, the fiber grating sensor monitors temperature change and strain in real time, and the sensing and control system regulates and controls all the systems in a coordinated mode according to the temperature change and the strain. Compared with a traditional heat insulation assembly, the heat insulation performance of the heat insulation assembly is improved by nearly 90%, the heat insulation assembly is still far superior to a traditional product during electrostatic failure, the heat insulation assembly further has the active heat management capacity and can adapt to the deep space extreme heat environment, efficient intelligent heat management of spacecrafts is achieved, and related assemblies can also be applied to various spacecrafts.

Description

Technical Field

[0001] This invention relates to the field of spacecraft thermal control, and more particularly to an adaptive thermal insulation component based on electrostatic levitation and graphene aerogel. Background Technology

[0002] With advancements in technology, humanity is now able to launch spacecraft into space to perform various exploration missions. In deep space exploration and geostationary orbit (GEO) missions, spacecraft need to cope with extremely harsh thermal environments: temperatures on the sun-facing side can exceed 150°C, while temperatures on the shaded side can drop below -180°C. Traditional multilayer thermal insulation (MLI) modules primarily rely on passive radiation reflection and physical spacing to block heat flow.

[0003] However, existing technologies have some significant shortcomings: Interlayer contact thermal conduction: Traditional MLI typically uses solid materials such as polyester mesh or glass fiber paper as spacers. Due to the effects of emission vibration, thermal deformation, or electrostatic adsorption, a large number of physical contact points are inevitably generated between layers, forming numerous "solid thermal bridges." In extremely high vacuum environments, when radiative heat transfer is effectively suppressed, this solid contact thermal conduction becomes a key obstacle limiting further improvements in MLI performance.

[0004] Fixed optical properties: The optical properties (absorption / emissivity) of traditional MLI outer layer materials (such as aluminized Kapton or Beta fabric) are determined during manufacturing. This prevents dynamic adjustments based on whether the spacecraft is in a state of "high-temperature heat dissipation requirements" (e.g., high-power operation) or "low-temperature insulation requirements" (e.g., hibernation), thus limiting the flexibility of the thermal control system.

[0005] Unknown status and low reliability: Traditional components lack internal monitoring functions, making it difficult for ground control centers to grasp the real-time temperature gradient or aging damage status inside the insulation layer. Furthermore, once the spacer fails and causes interlayer adhesion, the insulation performance will drop significantly, and there is no backup mechanism. Summary of the Invention

[0006] The technical problem to be solved by this invention is: how to reduce the contact conduction between the heat insulation layer and the spacecraft itself, so as to achieve more efficient and intelligent thermal management in the space environment.

[0007] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is as follows: An adaptive thermal insulation component based on electrostatic levitation and graphene aerogel includes: an intelligent color-changing outer protective layer, several stacked reflective layers, an electrostatic levitation control system, a sensing and control system, a graphene aerogel support frame, and an outer frame. The intelligent color-changing outer protective layer is located on the outermost side and has an actively adjustable thermal emissivity; The reflective layer comprises several layers, which are stacked sequentially. The electrostatic levitation control system is electrically connected to each reflective layer and the intelligent color-changing outer protective layer to provide electrostatic charge so that the reflective layers of adjacent layers and the intelligent color-changing outer protective layer generate electrostatic repulsion forces of the same polarity with the adjacent reflective layers, so that the adjacent layers remain in a non-contact levitation state within a preset distance. The graphene aerogel support frame is located at the edge of the reflective layer and the smart color-changing outer protective layer, and is situated between adjacent reflective layers and between the smart color-changing outer protective layer and adjacent reflective layers. It is used to define the minimum physical distance between layers and to provide low thermal conductivity support between the reflective layers of adjacent layers in the event of electrostatic levitation failure.

[0008] A sensing and control system is used to monitor the temperature status of the components and coordinate the control of the intelligent color-changing outer protective layer and the electrostatic levitation control system. The outer frame, through the physical geometric boundary formed by its inner wall, forcibly limits the movement range of the intelligent color-changing outer protective layer and each reflective layer at the four edges and in the stacking direction. When the electrostatic levitation control system is activated, the electrostatic Coulomb repulsion force experienced by each layer is much greater than the residual acceleration interference force of the spacecraft in the orbital environment, thereby driving each layer to expand outward until it is blocked by the limiting boundary of the outer frame, thus forming a uniform and stable non-contact vacuum insulation gap between each layer.

[0009] Compared with the prior art, the present invention has the following technical effects: This invention proposes an adaptive thermal insulation component that combines electrostatic levitation technology with graphene aerogel materials. By applying a high-voltage DC of the same polarity to the conductive surfaces of each reflective layer, a Coulomb repulsion force is generated between the layers using the principle of charge repulsion. The designed energy level of this Coulomb repulsion force is much greater than the residual acceleration disturbance force and interlayer van der Waals force of the spacecraft in orbital environment, thereby driving each reflective layer to actively expand outward until it reaches the geometric limit of the outer frame. Through the synergistic effect of 'strong repulsion force' and 'hard constraint', it ensures that each reflective layer, regardless of its installation orientation on the surface of a cylindrical spacecraft, can overcome the uneven and weak gravitational components, maintaining a uniform and stable non-contact vacuum insulation gap, bringing the thermal insulation performance close to the theoretical limit of radiative heat transfer.

[0010] Based on the above technical solution, the present invention can be further improved as follows.

[0011] Preferably, the intelligent color-changing outer protective layer includes a flexible substrate and an electrochromic film or a thermochromic film composited on the substrate. The sensing and control system adjusts the voltage applied to the film according to the received temperature signal or utilizes the ambient temperature to switch it between a "high reflectivity and low emissivity" heat preservation state and a "low reflectivity and high emissivity" heat dissipation state. High reflectivity and low emissivity refers to having high reflectivity in the visible and near-infrared bands to reduce solar radiation absorption, while having low emissivity in the far-infrared band to suppress its own heat radiation loss. "Low reflectivity and high emissivity" refers to reducing the reflectivity in the visible and near-infrared bands to allow some solar radiation to pass through or be absorbed, while increasing the emissivity in the far-infrared band to enhance heat radiation dissipation to the outside. For example, when the spacecraft is on the sunny side and the external ambient temperature is too high, the sensing and control system controls the electrochromic film to apply a specific voltage, causing it to switch to a "high reflection, low emission" state, reflecting a large amount of sunlight, reducing heat input and suppressing internal heat leakage, and maintaining stable internal temperature of the components; when the spacecraft is on the shaded side or when there is a lot of internal heat accumulation, the film switches to a "low reflection, high emission" state, dissipating internal heat through efficient far-infrared radiation, achieving dynamic thermal balance regulation.

[0012] Furthermore, the reflective layer comprises a flexible polymer substrate (such as a polyimide film) and a conductive reflective layer deposited on its surface. The intelligent color-changing outer protective layer also includes a transparent conductive layer made of indium tin oxide (ITO) or a conductive polymer, which ensures high visible light transmittance while possessing excellent conductivity.

[0013] The electrostatic levitation control system is connected to the transparent conductive layer of the intelligent color-changing outer protective layer and the conductive reflective layer of each reflective layer via high-voltage wires to apply DC high voltage of the same polarity. By generating a Coulomb repulsion force between adjacent layers (including between the outer protective layer and the first reflective layer) sufficient to overcome interlayer van der Waals forces and residual gravity, the entire system achieves non-contact levitation.

[0014] Furthermore, the graphene aerogel support frame is made of graphene aerogel. The graphene aerogel material has a three-dimensional porous network structure with a density of less than 10 mg / cm³, a room temperature vacuum thermal conductivity of less than 0.005 W / (m·K), and a porosity better than 99%. It serves as a backup solution in case of electrostatic levitation system failure and as edge support for different layer structures. This material has extremely low density and near-vacuum ultra-low thermal conductivity, which can reduce solid heat leakage to a very low level even when physical contact occurs between layers due to power failure, thus ensuring safety.

[0015] Furthermore, at least one of the reflective layer and the intelligent color-changing outer protective layer is equipped with a fiber Bragg grating sensor. The fiber Bragg grating sensor is communicatively connected to the sensing and control system for real-time acquisition of temperature distribution and strain data of the measured layer. The fiber Bragg grating sensor can monitor the temperature state of the measured layer structure and the stress state caused by changes in interlayer spacing in real time, and the data is transmitted back to the sensing and control system in real time.

[0016] The sensing and control system actively adjusts the emissivity of the intelligent color-changing outer protective layer based on the returned data, and dynamically regulates the electrostatic voltage conducted to the conductive surfaces of each layer to generate a Coulomb repulsive force sufficient to overcome residual gravity and van der Waals forces. This Coulomb repulsive force drives each layer to expand outward until it reaches the geometric limit boundary of the outer frame, thereby achieving a dynamic mechanical balance with the mechanical constraint force provided by the outer frame and the local elastic resistance of the support frame. This ensures that each layer maintains a stable non-contact levitation distance under different installation orientations of the spacecraft.

[0017] Furthermore, the sensing and control system adaptively adjusts itself based on the monitored thermal environment conditions: Low-temperature insulation mode: When the component is detected to be in a low-temperature environment, the intelligent color-changing outer protective layer is controlled to switch to a low emissivity state and maintain electrostatic levitation to block heat conduction; External heat insulation mode: When enhanced external environmental radiation is detected (such as when facing the sun) causing the outer layer temperature to rise, the intelligent color-changing outer protective layer is controlled to switch to a low absorption (high reflection) state to reduce external heat input. Active heat dissipation mode: When high-power heat generation of internal load is detected or the load is in the shade and requires auxiliary heat dissipation, the intelligent color-changing outer protective layer is controlled to switch to a high emissivity state and maintain the electrostatic suspension state between each layer. The non-contact gap is used to completely eliminate solid contact conduction, and the high emissivity of the outer protective layer is used to efficiently dissipate the residual heat transferred to the surface by radiation to the deep space heat sink.

[0018] A spacecraft comprising the aforementioned adaptive thermal insulation assembly based on electrostatic levitation and graphene aerogel. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the electrostatic levitation state of the intelligent adaptive multilayer thermal insulation component of the present invention; Figure 2 for Figure 1 Enlarged view of point A in the middle; Figure 3 This is a schematic diagram of the intelligent adaptive multilayer thermal insulation component of the present invention after the levitation function is turned off; Figure 4 for Figure 3 Enlarged view at point B in the middle; Figure 5This is a microscopic cross-sectional diagram illustrating the electrostatic levitation principle and interlayer structure. Figure 6 This is a block diagram of the module control logic of a sensing and control system.

[0020] The following is a list of component names represented by the reference numerals in the attached diagram: 1. Intelligent color-changing outer protective layer; 2. Reflective layer; 3. Graphene aerogel support frame; 4. Sensing and control system; 5. Fiber optic grating sensor; 6. Outer frame; 7. Transparent conductive layer; 8. Aluminum mold conductive layer. Detailed Implementation

[0021] The principles and features of the present invention are described below with reference to the accompanying drawings. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0022] Please refer to Figures 1 to 5 As shown, the adaptive thermal insulation component based on electrostatic levitation and graphene aerogel of the present invention mainly consists of an outermost intelligent color-changing outer protective layer 1, several reflective layers 2, a graphene aerogel support frame 3, a sensing and control system 4 integrating a high-voltage power supply and a signal processor, and an outer frame 6.

[0023] The intelligent color-changing outer protective layer 1 employs an electrochromic thin-film device based on flexible polyimide (PI). This thin film comprises a transparent conductive layer 7 (such as indium tin oxide ITO), an ion storage layer, an electrolyte layer, and an electrochromic layer (such as WO3). By applying a low voltage from -2V to +2V, its thermal emissivity ε can be continuously adjusted between 0.15 (bleached state, high reflectivity and heat preservation) and 0.75 (colored state, high emissivity and heat dissipation).

[0024] The reflective layer 2 is composed of a 6μm thick double-sided aluminized polyester film (VDA-PET). The aluminum conductive layer 8 is approximately 100nm thick with a sheet resistance of less than 1Ω / □, ensuring good conductivity to distribute static charge. Each film layer has a microelectrode interface.

[0025] The sensing and control system 4 contains a miniature high-voltage DC-DC boost module, which connects all aluminum layers of the reflective layer 2 to the same positive high-voltage output terminal (e.g., +1000V) via high-voltage insulated wires. The ground wire of the boost module is connected to the structural ground of the spacecraft. In a vacuum environment, according to Coulomb's law, electrostatic repulsion is generated between adjacent layers, maintaining a uniform spacing of approximately 0.5mm-1.0mm between each layer.

[0026] The graphene aerogel support frame 3 is made of ultralight graphene aerogel through precision cutting. The support frame is preferably a closed rectangular frame structure surrounding the edges of the reflective layer 2 and the intelligent color-changing outer protective layer 1. Through the circumferential tension support provided by the closed frame, combined with the uniform Coulomb repulsion force generated by the conductive surfaces of each layer, the flexible film can maintain a highly flat planar state in a suspended state.

[0027] In large-size modules, staggered spacers or support columns can be added in non-effective radiation areas to further enhance the structural rigidity of the film center. The thickness of the support frame and spacers is set slightly smaller than the preset interlayer spacing of electrostatic levitation (for example, when the levitation spacing is designed to be 0.8 mm, the thickness of the support frame and spacers is designed to be 0.4 mm), ensuring a completely non-contact state during normal operation of the electrostatic system. Figure 1 and Figure 2 As shown; while in system hibernation or failure, the interlayer can rely on the support frame and spacers to provide physical spacing support with ultra-low thermal conductivity, such as... Figure 3 and Figure 4 As shown.

[0028] The outer frame 6 constrains and limits the displacement of the intelligent color-changing outer protective layer 1 and each reflective layer 2 in the circumferential edge and stacking direction through the geometric limiting boundary formed by its inner wall.

[0029] When the electrostatic levitation system is working, the Coulomb repulsion force generated between adjacent layers drives each membrane layer to expand outward until it touches the limiting boundary of the outer frame 6, such as... Figure 1 and Figure 2 As shown. Through the synergistic effect of 'active repulsion' and 'mechanical hard restraint', the reflective layer 2 can maintain the preset interlayer spacing and surface flatness under different installation orientations and stress conditions of the spacecraft, thereby eliminating heat conduction through solid contact between layers.

[0030] The fiber optic sensing network uses polyimide-coated fiber Bragg grating (FBG) sensors with a diameter of approximately 125 μm, which are arranged in a serpentine pattern and bonded to the surface of key layers, such as the outermost smart color-changing outer protective layer 1, the middle reflective layer 2, and the innermost reflective layer 2. Alternatively, they can be directly embedded in an aerogel frame for precise measurement of temperature fields.

[0031] To verify the performance of the present invention, prototype samples and comparative sample samples were prepared and compared in a hot vacuum chamber simulating a deep space environment.

[0032] Example (Components of the Invention): A 300mm × 300mm square sample was prepared, comprising one intelligent color-changing outer protective layer 1 and nineteen reflective layers 2, for a total of twenty layers. Each layer has a 10mm wide and 0.4mm thick graphene aerogel support frame 3 along its edge. All reflective layers 2 and the outer protective layer are connected to an external high-voltage power supply via wires.

[0033] The twenty-layer structure is housed within a rigid outer frame 6, with the inner cavity of the frame 6 having a dimension of 19 mm in the stacking direction. When electrostatic levitation is disabled, each layer is supported by a graphene aerogel support frame 3, resulting in a total thickness of approximately 7.6 mm. Upon activation of the electrostatic levitation system, the coulombic repulsion between the layers drives the twenty-layer structure to expand outwards until the outermost and innermost layers abut against the inner cavity boundaries of the frame 6, automatically maintaining a uniform 1.0 mm levitation gap between each layer (corresponding to the 19 mm total travel limit of the frame 6). This 'active expansion + hard boundary constraint' design ensures that the components remain locked within a predetermined geometric space in different orientations of the spacecraft, maintaining a stable vacuum and thermal insulation state.

[0034] Comparative example (traditional MLI components): A conventional MLI sample of the same size was prepared. It consisted of one outer layer and nineteen reflective layers 2. The outer layer was made of aluminized Beta fabric with a fixed emissivity of approximately 0.8. The reflective layers 2 were made of double-sided aluminized polyester film. Traditional polyester mesh was used as spacer between the layers, maintaining physical contact. The polyester mesh was approximately 0.15 mm thick with a thermal conductivity of approximately 0.05 W / (m·K). The total number of layers was also twenty.

[0035] Test methods and operating conditions The equivalent heat leakage, i.e. heat flux density, of the sample was tested using steady-state calorimetry. The sample was installed in a hot vacuum chamber with one side facing a temperature-controlled heat sink to simulate the sun-facing side of outer space, and the other side was in close contact with a cold plate equipped with a heat flux meter and heating element to simulate the spacecraft wall. The control objective was to pursue a constant cold plate temperature.

[0036] Test environment vacuum level: better than 1.0 x 10 -5 Pa.

[0037] Test Condition 1: Deep Space Low Temperature Insulation Condition, which simulates the state of the shaded side of a spacecraft.

[0038] The external heat sink temperature is set to -196℃ (liquid nitrogen temperature), and the internal cold plate temperature is maintained at 20℃.

[0039] Example sample settings: electrostatic voltage is turned on to 1000V to achieve levitation; intelligent color-changing outer protective layer 1 is adjusted to "thermal insulation state", that is, adjusted to a low emissivity of ε≈0.15.

[0040] Test Condition 2: Test the insulation performance under the electrostatic levitation function failure mode.

[0041] Temperature conditions are the same as in operating condition one. In the example sample, the electrostatic voltage is turned off, and the interlayer electrostatic Coulomb repulsion disappears. Under the combined action of the environmental gravitational component, interlayer van der Waals forces, and the elastic stress of the film itself, the layered structure shifts and collapses until it physically contacts the graphene aerogel support frame 3, entering the 'contact thermal conduction' failure protection mode. At this time, the intelligent color-changing outer protective layer 1 maintains a 'thermal insulation state'.

[0042] Test Condition 3: Simulating the spacecraft's ability to regulate heat dissipation when it needs to do so.

[0043] Test environment setup: To verify the component's ability to assist in heat dissipation when internal equipment generates excessive heat, the external heat sink temperature was set to -196℃ (simulating the cold and heat sink environment of the shaded side of deep space), and the internal cold plate temperature was maintained in the high temperature range of 50℃ to 70℃ by heating elements to simulate the peak heat generation of internal key loads under high load operation.

[0044] Test process and purpose: Under the premise of activating electrostatic levitation (eliminating solid conduction), the intelligent color-changing outer protective layer 1 was tested in the "thermal insulation state" ( ≈0.15) and "heat dissipation state" ( Performance at ≈0.75). By comparing the electrical heating power required to maintain a constant high temperature of the cold plate, the heat dissipation resources that the active switching radiation characteristics of the component can save for the spacecraft are quantified.

[0045] Expected results: When the outer layer switches to heat dissipation mode, the heat flux to deep space increases significantly due to the opening of the radiation window. The temperature of the cold plate can quickly drop back to the safe operating range while maintaining the same power output, which proves that the component has the ability to actively adjust thermal balance and cope with sudden high heat loads.

[0046] Example Sample Setup: Electrostatic levitation enabled; Test the change in outward heat dissipation flux of the intelligent color-changing outer protective layer 1 under two conditions: "heat preservation state" (ε≈0.15) and "heat dissipation state" (ε≈0.75).

[0047] The test results are as follows:

[0048] As can be seen from the above experimental data, under the cryogenic conditions of deep space, after activating the electrostatic levitation function and adjusting the intelligent color-changing outer protective layer 1 to a low emission state, the steady-state heat leakage of this embodiment is only 0.12 W / m², which is nearly 90% higher than the 1.15 W / m² of the traditional MLI. This is mainly due to the fact that electrostatic levitation completely eliminates solid heat conduction in the central region between the layers, making the thermal insulation performance close to the theoretical limit of only radiative heat transfer.

[0049] Furthermore, the experimental data above demonstrates that, even in the event of electrostatic system failure, this embodiment, relying on ultra-low thermal conductivity graphene aerogel as interlayer support, exhibits a heat leakage of only 0.35 W / m², which is still far superior to traditional polyester mesh MLI. This proves the value of graphene aerogel as a high-performance spacer material.

[0050] Furthermore, through three-condition verification, this invention actively adjusts the optical properties of the intelligent color-changing outer protective layer 1 based on the data from the fiber optic grating sensor 5, and actively switches between "heat preservation" and "heat dissipation" modes, which is something that traditional MLI cannot achieve.

[0051] In summary, this invention achieves efficient and intelligent management of the extreme thermal environment in deep space by eliminating contact thermal resistance through electrostatic levitation, actively adjusting radiation thermal resistance through a color-changing outer layer, and reducing solid thermal resistance through graphene materials.

[0052] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. An adaptive thermal insulation component based on electrostatic levitation and graphene aerogel, characterized in that, include: The system consists of an intelligent color-changing outer protective layer, several layers of reflective layers, an electrostatic levitation control system, a sensing and control system, a graphene aerogel support frame, and an outer frame. The outer frame is disposed on the circumferential edge of the intelligent color-changing outer protective layer and several reflective layers, and the maximum displacement range of each layer is defined by the geometric boundary of its inner cavity. When the electrostatic levitation control system is working, the Coulomb repulsion force generated between adjacent layers drives each layer to expand outward until each layer is blocked by the limiting boundary of the outer frame, thereby achieving a stable non-contact levitation gap between each layer. The intelligent color-changing outer protective layer is located on the outermost side and has an actively adjustable thermal emissivity; The reflective layer comprises several layers, which are stacked sequentially. The electrostatic levitation control system is electrically connected to each reflective layer and the intelligent color-changing outer protective layer to provide electrostatic charge so that the reflective layers of adjacent layers and the intelligent color-changing outer protective layer generate electrostatic repulsion forces of the same polarity with the adjacent reflective layers, so that the adjacent layers remain in a non-contact levitation state within a preset distance. The graphene aerogel support frame is located at the edge of the reflective layer and the smart color-changing outer protective layer, and is situated between adjacent reflective layers and between the smart color-changing outer protective layer and adjacent reflective layers. It is used to define the minimum physical distance between layers and to provide low thermal conductivity support between the reflective layers of adjacent layers in the event of electrostatic levitation failure. The sensing and control system is used to monitor the temperature status of the components and coordinate the control of the intelligent color-changing outer protective layer and the electrostatic levitation control system.

2. The adaptive thermal insulation component based on electrostatic levitation and graphene aerogel according to claim 1, characterized in that, The intelligent color-changing outer protective layer includes a flexible substrate and an electrochromic film or a thermochromic film composited on the substrate. The sensing and control system adjusts the voltage applied to the film according to the received temperature signal or uses the ambient temperature to switch it between a "high reflection and low emission" heat preservation state and a "low reflection and high emission" heat dissipation state.

3. The adaptive thermal insulation component based on electrostatic levitation and graphene aerogel according to claim 1, characterized in that, The reflective layer comprises a flexible polymer substrate and conductive reflective layers plated on both sides of the substrate; the electrostatic levitation control system is connected to each of the conductive reflective layers via high-voltage wires to apply a DC high voltage of the same polarity, generating Coulomb repulsion between adjacent layers.

4. The adaptive thermal insulation component based on electrostatic levitation and graphene aerogel according to claim 1, characterized in that, The graphene aerogel support frame is made of graphene aerogel.

5. The adaptive thermal insulation component based on electrostatic levitation and graphene aerogel according to claim 1, characterized in that, At least one of the reflective layers and the intelligent color-changing outer protective layer is provided with a fiber optic grating sensor. The fiber optic grating sensor is communicatively connected to the sensing and control system and is used to collect the temperature distribution and strain data of the measured layer in real time.

6. The adaptive thermal insulation component based on electrostatic levitation and graphene aerogel according to claim 1, characterized in that, The sensing and control system adaptively adjusts itself based on the monitored thermal environment conditions, switching between low-temperature insulation mode, external heat insulation mode, and active heat dissipation mode. Low-temperature insulation mode: When the component is detected to be in a low-temperature environment, the intelligent color-changing outer protective layer is controlled to switch to a low emissivity state and maintain electrostatic levitation to block heat conduction; External heat insulation mode: When enhanced external environmental radiation is detected, causing the outer layer temperature to rise, the intelligent color-changing outer protective layer is controlled to switch to a low absorption state to reduce the entry of external radiant heat. Active heat dissipation mode: When the internal equipment is detected to be generating too much heat or is located on the shaded side and needs to dissipate excess heat, the intelligent color-changing outer protective layer is controlled to switch to a high emissivity state, and the electrostatic voltage between the corresponding layers is automatically increased to increase the interlayer spacing. The expansion of the vacuum interlayer gap and the high emissivity characteristics are used to accelerate the radiation and dissipation of heat into deep space.

7. The adaptive thermal insulation component based on electrostatic levitation and graphene aerogel according to claim 4, characterized in that, The graphene aerogel has a density of less than 10 mg / cm³, a room temperature vacuum thermal conductivity of less than 0.005 W / (m·K), and a porosity of better than 99%.

8. The adaptive thermal insulation component based on electrostatic levitation and graphene aerogel according to claim 1, characterized in that, The reflective layer is composed of a double-sided aluminum-coated polyester film (VDA-PET) with a thickness of 6μm, an aluminum layer thickness of approximately 100nm, and a sheet resistance of less than 1Ω / □.

9. The adaptive thermal insulation component based on electrostatic levitation and graphene aerogel according to claim 1, characterized in that, The thickness of the graphene aerogel support frame is between 0.1 mm and 0.5 mm.

10. A spacecraft, characterized in that, Including the adaptive thermal insulation components based on electrostatic suspension and graphene aerogel as described in claims 1-9.

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