Active thermal control method for lunar surface equipment under lunar extreme environment

Abstract

The application discloses a kind of lunar surface equipment active heat control methods under lunar polar extreme environment, belongs to spacecraft thermal control technical field.The application aims at the problem of complex structure and poor reliability of spacecraft active heat switch.The application comprises setting L-shaped heat-conducting film, the outer surface of one fold surface of L-shaped heat-conducting film is fixedly connected with lunar surface equipment circuit board, and the outer surface of another fold surface is arranged corresponding to the glass fiber contact surface of lunar surface equipment;During lunar day, another fold surface of L-shaped heat-conducting film is controlled to contact with the glass fiber contact surface of lunar surface equipment, so that the heat generated by lunar surface equipment circuit board during operation is transferred to the glass fiber contact surface of lunar surface equipment through L-shaped heat-conducting film;During lunar night, another fold surface of L-shaped heat-conducting film is controlled to be separated from the glass fiber contact surface of lunar surface equipment, to reduce the rate of heat transfer from lunar surface equipment circuit board to outside.The application actively controls the on-off of heat transfer path, and the control precision is high.

Description

Technical Field

[0001] This invention relates to an active thermal control method for lunar surface equipment in extreme lunar environments, belonging to the field of spacecraft thermal control technology. Background Technology

[0002] Existing spacecraft contact thermal switches mainly fall into two categories: passive thermal switches and active thermal switches.

[0003] Passive thermal switches do not rely on external driving mechanisms; they are triggered by changes in ambient temperature. Based on their driving mechanisms and principles, passive thermal switches can be categorized into bimetallic strip driven thermal switches, micro-expansion thermal switches, phase change driven thermal switches, and shape memory alloy thermal switches. Bimetallic strip driven thermal switches utilize the bending deformation of the bimetallic strip caused by changes in ambient temperature to move the contact components, thereby controlling the opening or closing of the thermal switch and establishing or cutting off the heat conduction path. However, because heat conduction through the bimetallic strip takes time, the thermal switch exhibits a response lag, and high-strength contact is not suitable due to its relatively high contact thermal resistance. Micro-expansion thermal switches utilize the difference in the linear expansion coefficients of the material at different temperatures to create a stroke difference, thereby controlling the opening or closing of the thermal switch and controlling heat conduction. Because the difference in the linear expansion coefficients of the material at different temperatures is small, the stroke of the thermal switch is short (typically on the order of tens of micrometers), requiring extremely high processing precision, and has a complex structure, resulting in large mass and volume. They are mostly used in low-temperature optical systems with large temperature differences. Phase change driven thermal switches use the volume change generated during the phase change of a phase change material to drive the contact component, controlling the opening and closing of the thermal switch. However, since the phase change point of the phase change material is fixed, the operating temperature of the thermal switch is difficult to adjust flexibly, and the phase change material has the risk of leakage, often resulting in operating temperature limitations. Furthermore, they suffer from large structural dimensions and weight. Shape memory alloy thermal switches utilize the change in spring stiffness during the phase change of the shape memory alloy material to drive the movement of the contact component, thereby controlling the on / off state of the thermal switch. Shape memory alloy thermal switches are a relatively new type of thermal switch in recent years, with a relatively simple structure. However, shape memory alloy materials may experience fatigue and material performance degradation after repeated thermal cycling, and most existing designs use rigid contacts, where unevenness and roughness of the contact surface introduce significant thermal resistance.

[0004] Active thermal switches rely on external drives and can be precisely controlled as needed. Active thermal switches can be divided into air-gap thermal switches and magnetically driven thermal switches. Air-gap thermal switches change the heat transfer characteristics by adding or removing gas between the heat-conducting plates, causing a change in thermal conductivity and thus opening or closing the thermal switch. When gas is added to the chamber, the heat transfer between the heat-conducting plates is enhanced through gas convection, turning the thermal switch on; when gas is evacuated to a vacuum, only thermal radiation exists between the heat-conducting plates, effectively reducing heat transfer and turning the thermal switch off. This type of thermal switch is mostly used in the cryogenic cooling systems of spacecraft infrared detectors. Its charging and discharging requires a long time, has a slow response speed, and its complex structure requires the use of air pumps, resulting in a large size and weight. Magnetically driven thermal switches use changes in the magnetic field to induce magnetostriction in the magnetically sensitive material, driving the magnetically sensitive material rod to extend or contract, thus controlling the opening and closing of the thermal switch. Because the elongation of the magnetically sensitive material rod requires a continuous magnetic field, this type of thermal switch requires numerous components and a continuous power supply to generate such a field, resulting in high energy consumption. For spacecraft, the magnetic field it generates may interfere with the normal operation of the spacecraft, and the external magnetic field environment can also affect the operation of the thermal switch. Summary of the Invention

[0005] To address the issues of complex structures and poor reliability of active thermal switches in spacecraft, this invention provides an active thermal control method for lunar surface equipment in the extreme lunar environment.

[0006] The present invention provides an active thermal control method for lunar surface equipment under extreme lunar environments, comprising:

[0007] An L-shaped thermal conductive film is set up so that the outer surface of one fold of the L-shaped thermal conductive film is fixedly connected to the circuit board of the lunar surface equipment, and the outer surface of the other fold is set to correspond to the glass fiber contact surface of the lunar surface equipment.

[0008] During lunar daytime, another fold of the L-shaped heat-conducting film is controlled to contact the glass fiber contact surface of the lunar surface equipment, so that the heat generated by the circuit board of the lunar surface equipment during operation is transferred through the L-shaped heat-conducting film to the glass fiber contact surface of the lunar surface equipment, and then transferred out through the glass fiber contact surface of the lunar surface equipment via the subsequent heat transfer path.

[0009] During the lunar night, the other fold of the L-shaped heat-conducting film separates from the glass fiber contact surface of the lunar surface equipment, reducing the rate at which heat is transferred outward from the circuit board of the lunar surface equipment, thereby reducing the heat preservation power consumption of the circuit board of the lunar surface equipment.

[0010] According to the active thermal control method for lunar surface equipment in extreme lunar environments of the present invention, a flexible pad and a transmission connecting piece are sequentially arranged on the inner surface of the other fold.

[0011] The linear motor screw passes through the transmission connecting plate and is driven by the flexible pad to achieve contact and separation with the glass fiber contact surface of the lunar surface equipment.

[0012] According to the active thermal control method for lunar surface equipment in extreme lunar environments of the present invention, the transmission connecting piece includes a centralized end and a transmission end, the thrust of the linear motor is transmitted from the centralized end to the transmission end, and then to the flexible pad; the centralized end and the transmission end are connected by bolts.

[0013] According to the active thermal control method for lunar surface equipment in extreme lunar environments of the present invention, the contour of the transmission end is the same as another fold of the flexible pad and the L-shaped thermal conductive film, and the concentration end is disc-shaped.

[0014] According to the active thermal control method for lunar surface equipment in extreme lunar environments of the present invention, through holes are correspondingly provided at the center of the central end, the transmission end, and the flexible pad;

[0015] The motor screw end is threaded. After passing through the through hole of the transmission connecting piece, the motor screw end is connected to the nut set in the through hole of the flexible pad. The motor screw end does not protrude from the flexible pad.

[0016] According to the active thermal control method for lunar surface equipment in extreme lunar environments of the present invention, the linear motor has a motor screw diameter of 3.5 mm, a thread lead of 0.6096 mm, and an effective stroke of 9 mm.

[0017] The initial distance between the other fold of the L-shaped thermal conductive film and the glass fiber contact surface of the lunar surface device is 8 mm.

[0018] According to the active thermal control method for lunar surface equipment under extreme lunar environments of the present invention, when the other folded surface comes into contact with the glass fiber contact surface of the lunar surface equipment, the flexible pad compensates for the unevenness of the glass fiber contact surface of the lunar surface equipment and the other folded surface by compression deformation, thereby reducing the contact thermal resistance.

[0019] According to the active thermal control method for lunar surface equipment in extreme lunar environments of the present invention, the L-shaped thermal conductive film is a graphene thermal conductive film with a thickness of 250 μm.

[0020] According to the active thermal control method for lunar surface equipment in extreme lunar environments of the present invention, the bending part of the L-shaped thermal conductive film is encapsulated with a thin metal plate, with a minimum bending radius of 3mm.

[0021] According to the active thermal control method for lunar surface equipment in extreme lunar environments of the present invention, a low-emissivity aluminized polyimide film is respectively pasted on the glass fiber contact surface of the lunar surface equipment and the two phase contact surfaces of the other fold.

[0022] The beneficial effects of this invention are: This invention addresses the needs of high-temperature heat dissipation and low-temperature insulation for equipment on the lunar surface.

[0023] The lunar surface environment is extremely harsh. During the lunar day, when exposed to sunlight, the surface temperature can reach 120°C; however, due to the lack of an atmosphere to provide insulation, the temperature plummets to -180°C during the lunar night. To address this extreme temperature difference, this invention proposes an active thermal control method for lunar surface equipment in this extreme environment.

[0024] Compared to traditional designs, this invention uses a motor to actively drive the on / off state of the heat transfer path, achieving high control precision. Simultaneously, it replaces traditional rigid contact components with a thermally conductive film and adds a flexible pad to compensate for unevenness and roughness of the contact surface, reducing contact thermal resistance. This invention effectively solves the problems of high contact thermal resistance, complex structure, and heavy weight in existing designs when in the conductive state.

[0025] This invention features low thermal resistance and high heat dissipation efficiency in the on-state, and strong radiation suppression and good heat preservation in the off-state. By adding a flexible pad, the contact thermal resistance in the on-state is reduced. At the same time, a low-emissivity aluminized polyimide film is adhered to the contact surface, further reducing radiative heat leakage and effectively improving heat dissipation efficiency.

[0026] Easy to implement and easy to assemble: By adding flexible pads to compensate for the parallelism and unevenness errors of the contact surfaces, the processing accuracy and assembly accuracy requirements of structural components can be effectively reduced, making processing, manufacturing and assembly easier.

[0027] The implementation components are simple in structure, lightweight, and highly reliable: using a thermally conductive film as the heat transfer component, the overall moving parts are few, the structure is simple, and it meets the lightweight requirements of spacecraft; at the same time, using a linear motor as the drive component, the response speed is fast and the reliability is high. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the implementation device for the active thermal control method for lunar surface equipment under extreme lunar environments described in this invention.

[0029] Figure 2 This is a schematic diagram of the split structure of the transmission connecting plate. Detailed Implementation

[0030] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] Specific Implementation Method 1: Combination Figure 1 and Figure 2 As shown, this invention provides an active thermal control method for lunar surface equipment under extreme lunar environments, comprising:

[0032] An L-shaped thermal conductive film is set up so that the outer surface of one fold of the L-shaped thermal conductive film is fixedly connected to the circuit board of the lunar surface equipment, and the outer surface of the other fold is set to correspond to the glass fiber contact surface of the lunar surface equipment.

[0033] During lunar daytime, another fold of the L-shaped heat-conducting film is controlled to contact the glass fiber contact surface of the lunar surface equipment, so that the heat generated by the circuit board of the lunar surface equipment during operation is transferred through the L-shaped heat-conducting film to the glass fiber contact surface of the lunar surface equipment, and then transferred out through the glass fiber contact surface of the lunar surface equipment via the subsequent heat transfer path.

[0034] During the lunar night, the other fold of the L-shaped heat-conducting film separates from the glass fiber contact surface of the lunar surface equipment, reducing the rate at which heat is transferred outward from the circuit board of the lunar surface equipment, thereby reducing the heat preservation power consumption of the circuit board of the lunar surface equipment.

[0035] Furthermore, combined with Figure 1 As shown, the outer surface of one fold of the L-shaped thermal conductive film 1 is fixedly connected to the circuit board of the lunar surface device, and the inner surface of the other fold is sequentially provided with a flexible pad 4 and a transmission connecting piece 3.

[0036] The motor screw of the linear motor 2 passes through the transmission connecting piece 3 and is driven by the flexible pad 4 to achieve contact and separation with the glass fiber contact surface 5 of the lunar surface equipment;

[0037] During lunar daytime, the linear motor drives another fold of the L-shaped heat-conducting film to contact the glass fiber contact surface of the lunar surface device. This allows the heat generated by the circuit board of the lunar surface device during lunar daytime operation to be conducted to the L-shaped heat-conducting film, and then transferred out through the glass fiber contact surface of the lunar surface device via the subsequent heat transfer path. During lunar nighttime, the linear motor drives the other fold of the L-shaped heat-conducting film to separate from the glass fiber contact surface of the lunar surface device, reducing the heat preservation power consumption of the circuit board of the lunar surface device.

[0038] This embodiment proposes an active control method for heat source equipment in the extreme temperature difference environment of the moon. The flexible pad in the method compensates for the contact thermal resistance caused by unevenness of the contact surface. An L-shaped thermal conductive film 1 serves as a heat transfer component, conducting heat from the circuit board of the equipment on the lunar surface away. A linear motor is the main drive mechanism, actively controlling its extension and retraction to achieve the opening and closing of contact between the L-shaped thermal conductive film and the glass fiber contact surface of the lunar surface equipment. A transmission connecting plate serves as a transmission component, transmitting the concentrated thrust of the linear motor to the contact surface for efficient contact.

[0039] The fiberglass contact surface is a structural component of equipment on the lunar surface. It is fixed in place and can transfer heat through subsequent heat transfer paths.

[0040] As an example, combined Figure 2 As shown, the transmission connecting piece 3 includes a central end and a transmission end. The thrust of the linear motor 2 is transmitted from the central end to the transmission end and then to the flexible pad 4.

[0041] The contour of the transfer end is the same as the other fold of the flexible pad 4 and the L-shaped thermal conductive film 1, and the concentrated end is disc-shaped.

[0042] The central end and the transmission end are connected by bolts.

[0043] Through holes are provided at the center of the central end, the transmission end, and the center of the flexible pad 4;

[0044] The motor screw end is threaded. After passing through the through hole of the transmission connecting piece 3, the motor screw end is connected to the nut set in the through hole of the flexible pad 4. The motor screw end does not protrude from the flexible pad 4.

[0045] As an example, the linear motor 2 has a motor screw diameter of 3.5 mm, a thread lead of 0.6096 mm, and an effective stroke of 9 mm.

[0046] The initial distance between the other fold of the L-shaped thermal conductive film 1 and the glass fiber contact surface of the lunar surface device is 8 mm.

[0047] Assembly Relationship: Linear motor 2 can be fixedly connected to the mounting bracket via four M2 screws. The end of the linear motor screw is designed with an M2.5 thread, and the transmission connecting plate has a corresponding through hole. After passing through the transmission connecting plate, the motor screw can be fixedly installed with the M2.5 nut in the through hole of the flexible pad 4. The flexible pad 4 is bonded and fixed to the transmission end of the transmission connecting plate 3. One end of the L-shaped thermal conductive film is fixedly connected to the circuit board of the lunar surface equipment, and the other end is bonded and fixed to the side of the flexible pad opposite to the linear motor.

[0048] In this embodiment, when the other folded surface comes into contact with the glass fiber contact surface of the lunar surface device, the flexible pad 4 compensates for the unevenness of the glass fiber contact surface of the lunar surface device and the other folded surface through its own compression deformation, thereby further reducing the contact thermal resistance.

[0049] As an example, the L-shaped thermal conductive film 1 is a graphene thermal conductive film with a thickness of 250 μm.

[0050] As an example, the bending section of the L-shaped thermal conductive film 1 is encapsulated with a thin metal plate, with a minimum bending radius of 3mm.

[0051] As an example, the glass fiber contact surface of the lunar surface device and the two phase contact surfaces of the other fold are respectively bonded with a low emissivity aluminized polyimide film, which can further reduce heat leakage from radiation in the disconnected state and improve thermal conductivity.

[0052] Working Process and Principle: During the lunar day, a linear motor is driven to bring the thermally conductive film into contact with the glass fiber interface, at which point the heat transfer path is open. During the lunar day, the circuit board generates heat, which is conducted to the thermally conductive film. Since the thermally conductive film is in contact with the glass fiber interface, the heat is transferred to the glass fiber interface via thermal conduction, and then dissipated through subsequent heat transfer paths to the heat dissipation surface. During the lunar night, the linear motor is driven to separate the thermally conductive film from the glass fiber interface, at which point the heat transfer path is closed. During the lunar night, the circuit board is not operating, but due to the lower ambient temperature, the temperature of the glass fiber interface is also lower. With the thermally conductive film separated from the glass fiber interface, heat can only be transferred through thermal radiation, reducing the outward heat transfer rate and effectively reducing the circuit board's heat preservation power consumption. Specific implementation examples:

[0054] Detailed design and parameter selection:

[0055] L-shaped thermal conductive film 1: The L-shaped thermal conductive film uses graphene as its material, which has the characteristics of good thermal conductivity, low density, and good flexibility. The selected graphene thermal conductive film can be 250μm thick, with an in-plane thermal conductivity of 1500W / (m·K), far exceeding that of copper (400W / (m·K); a vertical thermal conductivity of 10W / (m·K), and a density of approximately 2g / cm³. 3 The thermal conductive film is made of flexible material with good flexibility, which facilitates the movement of the contact surface of the thermal conductive film driven by a linear motor. For the weak structure at the 90° bend of the thermal conductive film, a thin metal plate can be used for encapsulation, with a minimum bending radius of 3mm.

[0056] Based on the temperature conditions of individual devices on the lunar surface and the design requirements of the structural thermal control system, the contact surface size of the heat-conducting film can be designed as follows: In order to further reduce radiative heat leakage when the heat transfer path is broken, aluminized polyimide films with an emissivity of approximately 0.2 are attached to the contact surfaces of the thermally conductive film and the glass fiber.

[0057] Linear Motor 2: Linear motors can be selected from the series of products of Shenzhen Shanshe Motor Co., Ltd. The selected linear motor size is... The screw diameter is 3.5mm, the thread lead is 0.6096mm, and the effective screw stroke is 9mm. The driving force of the linear motor is related to the thread lead and the screw elongation rate; for this linear motor, the driving force is approximately 40N. In the power-off state, the screw end thread has a self-locking function with a self-locking force of approximately 30N. The linear motor weighs approximately 60g, has an operating temperature range of -20 to +50℃, and its storage temperature can be measured to reach -40℃ to +100℃.

[0058] Transmission connecting piece 3: Transmission connecting piece 3 consists of two pieces, and its structure is shown in the figure below. Figure 2 As shown. The left transmission end converts the driving force of the linear motor into uniform pressure on the contact plane, and its dimensions are... Because the left-side transmission end is fixedly connected to the motor via nuts and screws, its contact area is very small, resulting in high local pressure. This can easily cause deformation, affecting the contact between the heat-conducting film and the glass fiber. Therefore, a right-side concentrator end is added to improve the connection rigidity with the motor and reduce the deformation of the transmission connecting plate itself. Its dimensions are... .

[0059] Both transmission connecting plates have through holes in their centers, which facilitates the connection of the screw rod through which the connection is secured by the thread and nut.

[0060] In addition, the transmission connecting piece 3 has four through holes distributed around the periphery of the central end, which are used for fixing the central end and the transmission end with M2 screws and nuts.

[0061] Flexible Pad 4: The flexible pad needs to convert the motor thrust into uniform surface pressure through its own compression deformation, while compensating for the contact thermal resistance caused by non-parallel or uneven contact surfaces. In addition, the flexible pad must meet the requirements of vacuum environment adaptability, have mature technology, and have precedents in aerospace applications. It should also have good thermal insulation properties to reduce heat leakage paths. Based on these functional requirements, the flexible pad material selected is silicone pad TGP 1500, with a density of 2.1 g / cm³. 3 The Young's modulus is 310 kPa, and the thermal conductivity is 1.5 W / (m·K). The specific dimensions are selected as follows: .

[0062] To ensure effective contact of the L-shaped thermal conductive film, an interference fit design is adopted to compress the film. Considering the linear motor's 9mm stroke and the difficulty in controlling its specific position, the initial design spacing between the thermal conductive film and the glass fiber contact surface is 8mm. In the heat transfer path conduction state, the parallelism and unevenness errors of the two contact surfaces caused by machining and assembly are eliminated through the flexible pad and the 1mm deformation of the glass fiber contact surface. Simultaneously, the motor driving force is applied to the thermal conductive film contact surface to ensure effective contact.

[0063] A thermal vacuum test was conducted, testing both the on-state and off-state of the heat transfer path under the same conditions. The test results showed that the temperature difference at the internal unit was 21°C. This demonstrates that the principle of the present invention is feasible and can achieve high heat dissipation efficiency.

[0064] In summary, this invention features a low thermal resistance heat conduction path design in the conductive state of the heat transfer path. A flexible pad is added between the heat conduction film and the transmission connecting piece. The compression deformation of the flexible pad compensates for the parallelism and unevenness errors of the contact surface between the heat conduction film and the glass fiber, enabling better contact between the heat conduction film and the glass fiber, increasing the effective contact area, and reducing the contact thermal resistance.

[0065] Radiation heat leakage is suppressed by adhering to the thermal conductive film contact surface and the glass fiber contact surface with a low emissivity aluminum-plated polyimide film to further reduce thermal radiation heat leakage.

[0066] While the invention has been described herein with reference to specific embodiments, it should be understood that these embodiments are merely examples of the principles and applications of the invention. Therefore, it should be understood that many modifications can be made to the exemplary embodiments, and other arrangements can be designed without departing from the spirit and scope of the invention as defined by the appended claims. It should be understood that different dependent claims and features described herein can be combined in ways different from those described in the original claims. It is also understood that features described in conjunction with individual embodiments can be used in other described embodiments.

Claims

1. A method for active thermal control of lunar surface equipment under extreme lunar environments, characterized in that... include: An L-shaped thermal conductive film is set up so that the outer surface of one fold of the L-shaped thermal conductive film is fixedly connected to the circuit board of the lunar surface equipment, and the outer surface of the other fold is set to correspond to the glass fiber contact surface of the lunar surface equipment. During lunar daytime, another fold of the L-shaped heat-conducting film is controlled to contact the glass fiber contact surface of the lunar surface equipment, so that the heat generated by the circuit board of the lunar surface equipment during operation is transferred through the L-shaped heat-conducting film to the glass fiber contact surface of the lunar surface equipment, and then transferred out through the glass fiber contact surface of the lunar surface equipment via the subsequent heat transfer path. During the lunar night, the other fold of the L-shaped heat-conducting film separates from the glass fiber contact surface of the lunar surface equipment, reducing the rate at which heat is transferred outward from the circuit board of the lunar surface equipment, thereby reducing the heat preservation power consumption of the circuit board of the lunar surface equipment. The inner surface of the other fold is sequentially provided with a flexible pad and a transmission connecting piece; The linear motor screw passes through the transmission connecting piece and is driven by the flexible pad to achieve contact and separation with the glass fiber contact surface of the lunar surface equipment; the end of the motor screw is threaded, and the thread at the end of the motor screw has a self-locking function in the power-off state; When the other folded surface comes into contact with the glass fiber contact surface of the lunar surface equipment, the flexible pad compensates for the unevenness of the glass fiber contact surface of the lunar surface equipment and the other folded surface through compression deformation, thereby reducing the contact thermal resistance. Low-emissivity aluminized polyimide films are respectively adhered to the glass fiber contact surface of the lunar surface device and the two phase contact surfaces of the other fold.

2. The active thermal control method for lunar surface equipment under extreme lunar environments according to claim 1, characterized in that, The transmission connecting piece includes a central end and a transmission end. The thrust of the linear motor is transmitted from the central end to the transmission end and then to the flexible pad. The central end and the transmission end are connected by bolts.

3. The active thermal control method for lunar surface equipment under extreme lunar environments according to claim 2, characterized in that, The contour of the transfer end is the same as another fold of the flexible pad and the L-shaped thermal conductive film, and the concentration end is disc-shaped.

4. The active thermal control method for lunar surface equipment under extreme lunar environments according to claim 2, characterized in that, Through holes are provided at the center of the central end, the transmission end, and the flexible pad, respectively; After the end of the motor screw passes through the through hole of the transmission connecting plate, it is connected to the nut set in the through hole of the flexible pad, and the end of the motor screw does not protrude from the flexible pad.

5. The active thermal control method for lunar surface equipment under extreme lunar environments according to claim 4, characterized in that, The linear motor has a screw diameter of 3.5 mm, a thread lead of 0.6096 mm, and an effective stroke of 9 mm. The initial distance between the other fold of the L-shaped thermal conductive film and the glass fiber contact surface of the lunar surface device is 8 mm.

6. The active thermal control method for lunar surface equipment under extreme lunar environments according to claim 1, characterized in that, The L-shaped thermal conductive film is a graphene thermal conductive film with a thickness of 250 μm.

7. The active thermal control method for lunar surface equipment under extreme lunar environments according to claim 1, characterized in that, The bending points of the L-shaped thermal conductive film are encapsulated with thin metal plates, with a minimum bending radius of 3mm.

Images