Automatic temperature control system of lunar surface equipment

Abstract

The automatic temperature control system comprises an equipment mounting plane, a soft magnet, a permanent magnet and a deformable heat dissipation surface, the soft magnet and the equipment mounting plane are mounted in a heat conduction manner, an elastic body and the deformable heat dissipation surface are arranged between the permanent magnet and the soft magnet, the automatic temperature control system has an unfolded state and a folded state, and a flexible heat conduction part is mounted in the automatic temperature control system; according to the temperature of the lunar surface equipment, the magnetism of the soft magnet is changed, the elastic body is converted between a compressed state and a loosened state, and the deformable heat dissipation surface is changed from a folded state to an unfolded state in a self-adaptive manner by combining the gravity of the lunar surface, so that heat of the lunar surface equipment is transferred to the deformable heat dissipation surface to radiate and dissipate heat outwards; or the deformable heat dissipation surface is changed into a folded state from an unfolded state, the lunar surface equipment is wrapped in the deformable heat dissipation surface, and heat preservation is conducted on the equipment. The method can give consideration to the energy utilization rate and the system reliability, and plays an important role in the lunar exploration task.

Description

Technical Field

[0001] This invention relates to the field of lunar surface thermal control, and in particular to an automatic temperature control system for lunar surface equipment. Background Technology

[0002] In a vacuum environment, radiative heat dissipation is a common heat dissipation method in the aerospace field. Providing heat dissipation surfaces for equipment can cool it under high temperatures, but requires more thermal compensation under low temperatures, wasting more energy. Common deployable heat dissipation surfaces generally require a control system, including wiring, software, and control units, significantly increasing the complexity of the equipment. Therefore, while passive thermal control and heaters offer high reliability, they also lead to greater energy waste. Deployable structures save energy but introduce more complex control systems, reducing system reliability. As lunar exploration missions develop further, there will inevitably be higher demands on both energy efficiency and system reliability.

[0003] Existing thermal control solutions struggle to simultaneously meet the demands for high energy efficiency and system reliability, significantly hindering the development of long-duration, high-power lunar exploration missions. Therefore, there is an urgent need for a novel automatic temperature control system that balances energy efficiency and system reliability to meet the requirements of future lunar exploration missions. Summary of the Invention

[0004] The technical problem solved by this invention is to provide an automatic temperature control system for lunar surface equipment, which addresses the issue that existing heat dissipation equipment cannot simultaneously achieve both high energy efficiency and high equipment complexity.

[0005] The technical solution of this invention is: to provide an automatic temperature control system for lunar surface equipment, comprising:

[0006] The equipment mounting surface is used to install lunar surface equipment to be temperature-controlled.

[0007] Soft magnets are thermally conductively mounted to the equipment mounting surface.

[0008] A permanent magnet with an elastic body between it and a soft magnet;

[0009] The deformable heat dissipation surface has an unfolded state and a retracted state, and a flexible heat-conducting part is installed inside;

[0010] When the temperature of the lunar surface device is greater than or equal to the magnetic critical point of the soft magnet, the soft magnet loses its magnetism, the elastic body changes from a compressed state to a relaxed state, and the lunar surface gravity causes the deformable heat dissipation surface to adapt from a contracted state to an unfolded state, and drives the internal flexible heat conduction part to deform to a horizontal state. The flexible heat conduction part transfers the heat of the lunar surface device to the deformable heat dissipation surface to radiate heat outward.

[0011] When the temperature of the lunar surface equipment is less than the magnetic critical point of the soft magnet, the soft magnet acquires magnetism, the elastic body changes from a relaxed state to a compressed state, the deformable heat dissipation surface is driven by the elastic body to change from an unfolded state to a retracted state, and the internal flexible heat-conducting part is deformed to an upright state, enclosing the lunar surface equipment inside. The flexible heat-conducting part stops heat transfer and keeps the equipment warm.

[0012] Furthermore, the deformable heat dissipation surface includes:

[0013] The heat insulation substrate is located on the lower surface of the deformable heat dissipation surface;

[0014] Several heat dissipation units are arranged side by side on the heat insulation substrate, and there is a connection point between two adjacent heat dissipation units.

[0015] The heat dissipation unit has a first fitting portion located below the connection point and a second fitting portion located above the connection point;

[0016] When the deformable heat dissipation surface is in the unfolded state, the heat dissipation unit rotates around the connection point to the first position, so that the first contacting part of the adjacent heat dissipation unit contacts and presses against each other, and the deformable heat dissipation surface deforms into a horizontal state.

[0017] When the deformable heat dissipation surface is in a folded state, the heat dissipation unit rotates around the connection point to a second position, so that the second contact parts of the adjacent heat dissipation units come into contact and press against each other, and the deformable heat dissipation surface deforms into an upright state.

[0018] Furthermore, the top of the heat dissipation unit is coated with a radiation coating; when the deformable heat dissipation surface is deformed into a horizontal state, the radiation coating dissipates heat to the sky, and the heat insulation substrate isolates the lunar surface from heat radiation; when the deformable heat dissipation surface is deformed into an upright state, the radiation coating reflects the radiation energy of the lunar surface equipment, and the heat insulation substrate reduces the radiative heat dissipation from the inside to the outside.

[0019] Furthermore, the contour of the heat dissipation unit is such that when it is in the folded state, adjacent heat dissipation units fold towards the working side around the connection point.

[0020] Furthermore, the first bonding portion has a rectangular cross-section, and the second bonding portion has a trapezoidal cross-section.

[0021] Furthermore, the deformable heat dissipation surface is composed of multiple blades.

[0022] Furthermore, the flexible heat-conducting part inside the blade is a flexible heat pipe.

[0023] Furthermore, the leaves are petal-shaped.

[0024] Furthermore, the blade is connected to the equipment mounting plane and the base for mounting the elastomer via hinges.

[0025] Furthermore, the blades are arc-shaped when they are folded up.

[0026] The advantages of this invention compared to the prior art are:

[0027] This invention innovatively proposes an automatic temperature control system for lunar surface equipment. This automatic temperature control system utilizes lunar gravity to achieve adaptive state switching based on changes in equipment temperature. It can autonomously deform the heat dissipation surface without using an additional active control system, achieving the same result while greatly reducing the complexity of the equipment. Combining the characteristics of heat pipes that cannot work when placed vertically with the characteristics of deformable heat dissipation surfaces, the system's heat dissipation and heat preservation performance in both heat dissipation and heat preservation modes is greatly enhanced. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the structure of the present invention;

[0029] Figure 2 This is a schematic diagram of the flexible heat pipe structure of the present invention;

[0030] Figure 3 This is a schematic diagram of a modified version of the present invention;

[0031] Figure 4 This is a schematic diagram of the cross-sectional structure and deformation principle of the deformable heat dissipation surface of the present invention. Detailed Implementation

[0032] To better understand the technical solution of the present invention, the specific embodiments of the present invention are described below.

[0033] See Figures 1-2 As shown, an automatic temperature control system for lunar surface equipment includes an equipment mounting plane 1, a deformable heat dissipation surface 2, a soft magnet 3, an elastic body 4, a permanent magnet 5, and a flexible heat pipe 6. The equipment mounting plane 1 is used to mount the lunar surface equipment to be temperature controlled; the soft magnet 3 is thermally conductively mounted to the equipment mounting plane 1; the permanent magnet 5 is connected to the soft magnet 3 via the elastic body 4; the deformable heat dissipation surface 2 has an extended state and a retracted state; the flexible heat pipe 6 is thermally conductively mounted inside the deformable heat dissipation surface 2; and the deformable heat dissipation surface 2 is connected to the equipment mounting plane 1 and the base of the elastic body 4 via hinges.

[0034] See Figure 3As shown, when the temperature of the lunar surface equipment is higher than the Curie point temperature of the soft magnet 3, the soft magnet 3 loses its magnetism, the elastic body 4 changes from a compressed state to a relaxed state, and the deformable heat dissipation surface 2, under the influence of lunar gravity, changes from a contracted state to an unfolded state, causing the internal flexible heat pipe 6 to deform to a horizontal state; when the temperature of the equipment is lower than the Curie point temperature of the soft magnet 3, the soft magnet 3 gains magnetism, the elastic body 4 changes from a relaxed state to a compressed state, and the deformable heat dissipation surface 2, driven by the elastic body, changes from an unfolded state to a contracted state, causing the internal flexible heat pipe 6 to deform to a contracted state.

[0035] The flexible heat pipe 6 is in a horizontal state when the equipment temperature is higher than the Curie point temperature of the soft magnet. At this time, the function of the heat pipe is not affected by gravity and can transfer the heat of the equipment to the heat dissipation surface to increase the heat exchange efficiency. When the equipment temperature is lower than the Curie point temperature of the soft magnet, it is in a contracted state. At this time, the function of the heat pipe is affected by gravity and cannot transfer heat to the heat dissipation surface, which can keep the equipment warm.

[0036] In one possible implementation, such as Figure 4 As shown, one heat dissipation unit of the deformable heat dissipation surface 2 has a trapezoidal side and a rectangular side. The surface of the trapezoidal side is a white-painted heat dissipation surface 7, and the bottom of the rectangular side is a multi-layered covering surface 8. When the deformable heat dissipation surface is in a horizontal state, the rectangular side modules are pressed together by gravity, causing the deformable heat dissipation surface to deform into a horizontal state. At this time, the white-painted heat dissipation surface 7 dissipates heat to the sky, and the multi-layered covering surface 8 isolates the infrared radiation from the lunar surface, improving heat dissipation efficiency. When the deformable heat dissipation surface is upright, the trapezoidal side modules are pressed together by gravity, causing the deformable heat dissipation surface to deform into a contracted state. At this time, the heat dissipation surface deforms into an arc surface that wraps the equipment inside. The white-painted surface reflects the infrared radiation emitted by the equipment, and the multi-layered structure reduces the radiative heat dissipation from the inside to the outside, giving the equipment better heat preservation capabilities.

[0037] It is understood that this invention has been described through embodiments, and those skilled in the art will recognize that various changes or equivalent substitutions can be made to these features and embodiments without departing from the spirit and scope of this invention. Furthermore, under the teachings of this invention, these features and embodiments can be modified to adapt to specific circumstances without departing from the spirit and scope of this invention. Therefore, this invention is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are protected by this invention.

[0038] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A lunar surface facility automatic temperature control system, characterized by, The device comprises: a device mounting plane (1) for mounting a lunar surface device to be temperature-controlled; a soft magnet (3) mounted in thermal contact with the device mounting plane (1); a permanent magnet (5) with an elastomer (4) between the soft magnet (3); a deformable heat dissipation surface (2) having an unfolded state and a folded state, and internally provided with a flexible heat conducting part; when the temperature of the lunar surface device is higher than the magnetic critical point of the soft magnet (3), the soft magnet (3) loses magnetism, the elastomer (4) changes from a compressed state to a relaxed state, and the lunar surface gravity causes the deformable heat dissipation surface (2) to change from the folded state to the unfolded state, and the flexible heat conducting part inside the deformable heat dissipation surface (2) deforms to a horizontal state, and the flexible heat conducting part transfers the heat of the lunar surface device to the deformable heat dissipation surface (2) to radiate heat outward; when the temperature of the lunar surface device is lower than the magnetic critical point of the soft magnet (3), the soft magnet (3) obtains magnetism, the elastomer (4) changes from the relaxed state to the compressed state, and the deformable heat dissipation surface (2) is driven by the elastomer to change from the unfolded state to the folded state, and the flexible heat conducting part inside the deformable heat dissipation surface (2) deforms to a vertical state, and the flexible heat conducting part stops heat transfer, and the lunar surface device is wrapped inside.

2. The lunar surface equipment automatic temperature control system according to claim 1, characterized in that: The deformable heat dissipation surface (2) comprises: a heat insulation base (8) located on the lower surface of the deformable heat dissipation surface (2); a plurality of heat dissipation units arranged side by side on the heat insulation base (8), and each heat dissipation unit has a connection point between adjacent two heat dissipation units; the heat dissipation unit has a first fitting part located below the connection point and a second fitting part located above the connection point; when the deformable heat dissipation surface (2) is in the unfolded state, the heat dissipation unit rotates around the connection point to a first position, so that the first fitting parts of adjacent heat dissipation units are in contact and compressed with each other, and the deformable heat dissipation surface deforms to a horizontal state; when the deformable heat dissipation surface (2) is in the folded state, the heat dissipation unit rotates around the connection point to a second position, so that the second fitting parts of adjacent heat dissipation units are in contact and compressed with each other, and the deformable heat dissipation surface deforms to a vertical state.

3. The lunar surface equipment automatic temperature control system according to claim 2, characterized in that: The top of the heat dissipation unit is coated with a radiation coating; when the deformable heat dissipation surface deforms to a horizontal state, the radiation coating radiates heat to the sky, and the heat insulation base (8) insulates the lunar heat radiation; when the deformable heat dissipation surface deforms to a vertical state, the radiation coating reflects the radiant energy of the lunar surface device, and the heat insulation base (8) reduces the radiant heat from the inside to the outside.

4. The lunar surface equipment automatic temperature control system according to claim 2, characterized in that: The profile of the heat dissipation unit is such that when it is in the folded state, the adjacent heat dissipation units are folded to one side around the connection point.

5. The lunar surface equipment automatic temperature control system according to claim 4, characterized in that: The first fitting part is rectangular in cross section, and the second fitting part is trapezoidal in cross section.

6. The automatic temperature control system for lunar surface equipment according to any one of claims 1 to 5, characterized in that: The deformable heat dissipation surface (2) is composed of a plurality of blades.

7. The lunar surface equipment automatic temperature control system according to claim 6, characterized in that: The flexible heat conducting part in the blade is a flexible heat pipe (6).

8. The lunar surface equipment automatic temperature control system according to claim 6, characterized in that: The blade is petal-shaped.

9. The lunar surface equipment automatic temperature control system according to claim 6, characterized in that: The blade is connected to the device mounting plane and the base for mounting the elastomer by a hinge.

10. The lunar surface equipment automatic temperature control system according to claim 6, characterized in that: The blade is circular arc-shaped when it reaches the folded state.

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