Thermal control system of Mars lander

Abstract

The invention relates to a thermal control system of a Mars lander, and belongs to the technical field of thermal management of deep space exploration spacecrafts. The system comprises a mobile in-situ water extractor, a spectrum selective photo-thermal / photoelectric conversion heat collection plate, a water-ice phase change energy storage device, a flowing working medium pipeline and the like, the mobile in-situ water extractor is used for collecting a water-ice phase change material, and the spectrum selective photo-thermal / photoelectric conversion heat collection plate is used for collecting solar energy and converting, utilizing and storing the solar energy; the water-ice phase change energy storage device is used for storing and releasing heat energy. By adopting a mode of combining the spectral selective photo-thermal / photoelectric conversion heat collection plate and the water-ice phase change energy storage device, the utilization efficiency of solar energy is effectively improved, the launching load and cost of the lander are reduced, and a powerful guarantee is provided for long-term detection of the Mars lander.

Description

Technical Field

[0001] This invention belongs to the field of deep space exploration spacecraft thermal management technology, specifically a thermal control system for a Mars lander. By integrating technologies such as solar energy collection, thermal energy storage and release, and in-situ water ice utilization, this system addresses the challenges of temperature control and energy supply for the lander in environments such as Mars, where large day-night temperature swings and intermittent solar energy supply are common. Background Art

[0002] Mars, one of the key targets of human space exploration, faces significant challenges in its unique environmental conditions, posing significant challenges to the design and operation of Mars landers. Mars, located approximately 1.5 AU from the Sun, receives only about one-third the solar radiation received by Earth's surface, resulting in extremely cold surface temperatures, averaging approximately -60°C. Furthermore, Mars' atmosphere, with a density of only 1% of Earth's, is extremely thin, resulting in an extremely harsh thermal environment, with daytime and nighttime temperature fluctuations exceeding 100°C. In this extreme environment, the thermal control system of a Mars lander is crucial, as it directly impacts the proper functioning of the lander's electronic components and the stable operation of its instruments and equipment.

[0003] Currently, successful Mars landers abroad primarily utilize two thermal control methods: isotope heat sources and electric heating. While isotope heat sources can provide stable thermal energy, they also present numerous challenges, such as increased complexity and mass of the thermal control subsystem. Furthermore, nuclear safety concerns are crucial, as an accident could severely impact the Martian environment and the exploration mission. Electric heating consumes significant amounts of electricity, which is extremely detrimental to the long-term operation of the lander. This is because the power supply on Mars landers is inherently limited, and excessive reliance on electric heating would consume valuable energy resources, impacting the normal operation of other instruments and equipment.

[0004] In addition to the above-mentioned thermal control methods, traditional spacecraft often use photovoltaic or solar thermal technology to utilize solar energy alone. However, both methods have obvious shortcomings. Although photovoltaic technology alone can convert sunlight into electrical energy, its conversion efficiency is limited, and it cannot effectively utilize the part of solar radiation heat energy that is not converted into electrical energy, resulting in energy waste. Although solar thermal technology alone can collect solar radiation heat energy, its exergy efficiency is low, making it difficult to meet the high demand for electricity from the lander. In addition, in the process of converting sunlight into electrical energy, traditional photovoltaic panels will lose a considerable amount of energy in the form of heat. If not effectively utilized, this heat will be dissipated in the Martian atmosphere, further reducing the overall efficiency of solar energy utilization.

[0005] Existing spacecraft typically use phase-change materials (PCMs) such as paraffin, hydrates, and organic polymers for heat storage. These materials must be launched from Earth, increasing the launch payload and costs. Furthermore, these PCMs have relatively low latent heat of change and large temperature fluctuations. For the same amount of heat storage, they require more material mass and space.

[0006] To address these issues, this paper proposes a Mars lander thermal control system based on spectrally selective photothermal / photoelectric conversion technology and water-ice phase-change energy storage. This system aims to fully utilize Mars' solar energy resources and the abundant Martian water ice as a phase-change energy storage material. This system addresses the shortcomings of existing Mars lander thermal control systems and provides an efficient, reliable, and cost-effective thermal control solution for Mars exploration missions. Summary of the Invention

[0007] The purpose of the present invention is to provide an efficient thermal control system for a Mars lander to solve the problem existing in the prior art, namely that the existing thermal control method is difficult to meet the energy efficiency and long-term stable operation requirements of the Mars lander.

[0008] To achieve the above objectives, the present invention provides a Mars lander thermal control system, comprising:

[0009] A mobile in-situ water extractor, mounted vertically on the exterior of the lander, is used to collect water ice from the Martian environment and transport it to the water-ice phase-change energy storage device;

[0010] The water-ice phase-change energy storage device is installed inside the lander and is attached to the heating load inside the lander through a partition, and is used to store and supply heat to the heating load;

[0011] Spectrally selective photothermal / photovoltaic conversion collectors, covered on top of the lander via a backplane, are used to collect solar energy and convert it into electrical and thermal energy;

[0012] A fluid pipeline connects the spectrally selective photothermal / photoelectric conversion heat collecting plate and the water-ice phase change energy storage device.

[0013] In one embodiment, the mobile in-situ water extractor is mounted on the rear surface of the lander and includes a deep groove auger, a cylindrical heat exchanger, a water collector, and a telescopic cylinder;

[0014] The cylindrical heat exchanger is hollow inside and has an inner wall with electric heating wires arranged spirally along the height direction. The cylindrical heat exchanger is fixedly connected to the rear surface of the lander;

[0015] The deep groove spiral drill is coaxially installed inside the cylindrical heat exchanger and includes a drill rod and a motor for driving the drill rod to rotate;

[0016] The telescopic cylinder is fixedly mounted on the end of the cylindrical heat exchanger, and the telescopic end of the telescopic cylinder extends into the interior of the cylindrical heat exchanger and is fixedly connected to the motor;

[0017] The water collector is fixedly mounted on the outside of the cylindrical heat exchanger, one side of which is in communication with the inner cavity of the cylindrical heat exchanger, and the other side of which is in communication with the water-ice phase change energy storage device through a pipeline. The water collector is used to collect the steam generated by the fire soil containing water ice drilled by the deep groove auger after being heated by the electric heating wire, liquefy the steam, and then introduce it into the water-ice phase change energy storage device.

[0018] In one embodiment, an inlet is formed at an upper end of the water collector close to the cylindrical heat exchanger, and the inlet extends to the inner cavity of the cylindrical heat exchanger through a pipe;

[0019] An outlet is provided at the lower end of the water collector away from the cylindrical heat exchanger, and the outlet is connected to the water-ice phase change energy storage device through a pipeline;

[0020] A first one-way valve is installed at the inlet, and a second one-way valve is installed at the outlet.

[0021] In one embodiment, the opening and closing pressures of the first one-way valve and the second one-way valve are adjustable, so as to always keep the liquid level of the liquid water in the water collector at one quarter of the height of the inner cavity of the water collector.

[0022] In one embodiment, it further includes an optical window, which is installed to cover the top of the spectrally selective photothermal / photoelectric conversion collector plate.

[0023] In one embodiment, the optical window is made of a material having a transmittance greater than 0.90 in the solar band, and the material includes quartz glass.

[0024] In one embodiment, the water-ice phase change energy storage device includes an energy storage box, which contains liquid water and is fixed above the heating load through a partition;

[0025] A through hole is provided on a side of the energy storage box close to the mobile in-situ water extractor for introducing liquid water;

[0026] The energy storage box and the heating load are filled and wrapped with an aerogel insulation layer.

[0027] In one embodiment, the fluid flow pipe is a capillary heat pipe;

[0028] One end of the capillary heat pipe is fixed to the back of the back plate, and the other end is immersed in the water-ice phase change material contained in the water-ice phase change energy storage device.

[0029] In one embodiment, the fluid medium filled in the fluid medium pipeline is ammonia water.

[0030] In one embodiment, the spectrally selective photothermal / photoelectric conversion heat collector comprises a laminated structure, which includes an encapsulation layer, a transparent electrode layer, a photoelectric / photothermal conversion layer, and a back electrode layer in sequence;

[0031] The transparent electrode layer is a metal nano-grid structure, and the photoelectric conversion layer is a semiconductor material.

[0032] Compared with traditional spacecraft thermal control systems, the present invention has the following advantages:

[0033] 1. Radiative heat loss on Mars is the primary component of device heat loss. This invention uses spectrally selective photothermal / photovoltaic conversion collectors to collect solar energy. Their absorptivity in the solar spectrum (0.3-3μm) is extremely high (ideally 1) and their emissivity in the infrared spectrum (5-15μm) is extremely low (ideally 0). These panels can collect virtually all solar radiation and are less likely to lose heat through infrared radiation. Their absorption-emission ratio can reach over 4.0, significantly suppressing radiative heat loss. This allows the thermal control system to achieve an overall efficiency of over 70%. Compared to traditional integrated photovoltaic and photothermal systems, this improves utilization efficiency by 20%, making it more conducive to maintaining the lander's survival in the harsh Martian environment.

[0034] 2. This invention utilizes water-ice phase-change materials for energy storage. Because water-ice has a latent heat of change of 334 J / kg, significantly higher than other materials (e.g., paraffin wax, 250 J / kg, and n-undecane, 141 J / kg), temperature fluctuations are minimal. Furthermore, water-ice's high density reduces the required mass and space for storing the same amount of heat. For a Mars lander, using water-ice for heat storage reduces the mass of phase-change material required by 33% compared to using paraffin wax.

[0035] 3. Mars itself has water ice resources. Compared with phase change materials such as polymer organics used in traditional spacecraft, the water ice phase change material in this invention directly utilizes local in-situ resources without having to be launched and carried from Earth. This can significantly reduce the spacecraft's load and lower launch costs. At the same time, because the phase change material can be obtained continuously from Mars, its long-term stability and reliability are higher than other phase change materials. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 Spectrum diagram for ideal spectrally selective photothermal / photoelectric conversion;

[0037] Figure 2 2 is a cross-sectional structural diagram of the spectrally selective photothermal / photoelectric conversion heat collector panel of the present invention;

[0038] Figure 3 Schematic diagram of the thermal control system structure of the present invention;

[0039] Figure 4 Schematic diagram of the working principle of the thermal control system of the present invention;

[0040] In the figure: 1. Mobile in-situ water extractor; 11. Deep groove auger; 111. Drill rod; 112. Motor; 12. Cylindrical heat exchanger; 13. Water collector; 131. First one-way valve; 132. Second one-way valve; 14. Telescopic cylinder; 2. Optical window; 3. Spectrally selective photothermal / photoelectric conversion collector; 31. Encapsulation layer; 32. Transparent electrode; 33. Photoelectric-photothermal conversion layer; 34. Back electrode; 35. Back plate; 4. Water-ice phase change energy storage device; 41. Energy storage box; 42. Partition; 5. Flowing medium pipeline; 6. Aerogel insulation layer; 8. Heating load; 9. Photovoltaic panel; 10. Lander. DETAILED DESCRIPTION

[0041] To further elaborate on the technical solutions and advantages of the present invention, Figure 1 To the attached Figure 4 The Mars lander thermal control system of the present invention is described in detail in the following specific embodiments.

[0042] 1. Composition and specific structure of thermal control system

[0043] 1. Mobile in-situ water extractor 1:

[0044] The mobile in-situ water extractor 1 includes a deep groove auger 11 , a cylindrical heat exchanger 12 , a telescopic cylinder 14 and a water collector 13 .

[0045] The cylindrical heat exchanger 12 can be made of heat-resistant ceramic and has a cylindrical shape. Its interior is hollow and is used to accommodate the deep-groove auger 11. Specifically, it can be fixed vertically to the rear surface of the lander 10 using a clamp, a U-shaped saddle clip, or other fastening methods.

[0046] like Figure 4 As shown, telescopic cylinder 14 is fixedly mounted on top of cylindrical heat exchanger 12, with its telescopic end located inside cylindrical heat exchanger 12 and fixedly connected to motor 112 in deep-groove auger 11. Thus, when lander 10 reaches a designated position, the controller can control telescopic cylinder 14 to operate, using its telescopic end to push motor 112, along with drill rod 111, to which the motor 112 output shaft is fixedly connected, downward along the height direction of cylindrical heat exchanger 12.

[0047] At this point, motor 112, also under the control of the controller, starts to drive drill rod 111 to rotate, drilling into the Martian regolith. When the drilling depth, i.e., the stroke of telescopic cylinder 14, exceeds 50 cm, motor 112 shuts down. When drill rod 111 completely stops rotating within the borehole, telescopic cylinder 14 retracts, slowly pulling motor 112 and drill rod 111 back into cylindrical heat exchanger 12. At this point, regolith containing water ice will remain in the spiral grooves on the surface of drill rod 111. At this point, the battery on lander 10 can be used to energize the electric heating wires spirally arranged along the height of cylindrical heat exchanger 12 on the inner wall of cylindrical heat exchanger 12. This raises the temperature inside cylindrical heat exchanger 12 to above 30°C, heating the regolith carried in the spiral grooves on drill rod 111 to sublime steam. Upon reaching the top of the cylindrical heat exchanger, the steam passes through first one-way valve 131 and enters water collector 13.

[0048] Optionally, to prevent steam pressure from escaping and to improve the heating efficiency of the cylindrical heat exchanger 12, the diameter of the drill rod 111 can be designed to match the inner diameter of the cylindrical heat exchanger. Optionally, the inner diameter of the cylindrical heat exchanger 12 can be ensured to be 1 cm longer than the diameter of the drill rod 111. This can not only reduce the accidental fall of the fire soil from the spiral deep groove, but also form a narrow heat transfer space between the drill rod 111 and the cylindrical heat exchanger 12, reducing the power consumption required by the electric heating wire.

[0049] Water collector 13 is securely attached to the top and exterior of cylindrical heat exchanger 12, shielded from the heated environment within cylindrical heat exchanger 12. However, its proximity to the heat source, such as cylindrical heat exchanger 12, keeps the temperature within water collector 13 lower than that within cylindrical heat exchanger 12, but higher than the Martian atmosphere. After passing through first one-way valve 131 and entering water collector 13, hot steam liquefies into liquid water due to the drop in ambient temperature and accumulates at the bottom of water collector 13. As liquid water accumulates, the liquid level rises and exceeds one-quarter the height of water collector 13's interior. The hydraulic pressure and the pressure of the steam that has yet to liquefy exceed the opening threshold of second one-way valve 132, causing liquid water to flow through second one-way valve 132 and the pipeline into energy storage tank 41 within water-ice phase change energy storage device 4. The second one-way valve 132 closes again when the liquid level returns to one-quarter the height of water collector 13's interior.

[0050] The inlet of the water collector 13, where the first one-way valve 131 is located, is located at the upper end of the water collector 13, while the outlet of the water collector 13, where the second one-way valve 132 is located, is located at the lower end of the water collector 13, thereby creating a height difference. When the initial water vapor condenses and liquefies, this height difference creates a liquid seal around the outlet of the second one-way valve 132. This liquid seal prevents the water vapor from directly passing through the second one-way valve 132 and entering the energy storage tank 41. More importantly, this prevents greenhouse gases such as carbon dioxide from entering the energy storage tank 41 along with the water vapor, which would affect the heat transfer efficiency of the water-ice phase change energy storage device 4 and occupy the available storage space of the energy storage tank 41.

[0051] 2. Spectrally selective photothermal / photoelectric conversion collector 3:

[0052] The spectrally selective photothermal / photoelectric conversion heat collecting plate 3 is one of the core components of the thermal control system, which has special spectral selectivity. Figure 1 As shown, the absorptivity in the solar band of 0.3-3 μm is greater than 0.84, and the emissivity in the mid-infrared band of 5-15 μm is less than 0.2. This spectral selectivity allows the spectrally selective photothermal / photoelectric conversion collector 3 to efficiently absorb solar energy when collecting solar energy, while effectively reducing heat loss in the form of infrared radiation, thereby improving the utilization efficiency of solar energy.

[0053] like Figure 2 As shown, the spectrally selective photothermal / photoelectric conversion collector plate 3 adopts a rigid laminate structure, consisting of an encapsulation layer 31, a transparent electrode 32, a photoelectric-photothermal conversion layer 33, and a back electrode 34, connected in sequence from top to bottom. The encapsulation layer 31 is made of a 0.05mm thick polyethylene film with an average transmittance of 0.97 over the entire 0.3-25μm band. It is applied to the transparent electrode 32 by hot embossing.

[0054] The transparent electrode 32 is made of a metallic silver nanomesh with a thickness of 30 nm and a grid arrangement period of 50 nm. It has an average transmittance of 0.78 in the solar radiation band and an average emissivity of 0.15 in the mid-infrared band. It is grown on the front of the photovoltaic-thermal conversion layer 33 by nanoimprinting or electron beam lithography.

[0055] The photoelectric-thermal conversion layer 33 is made of a 500 μm thick n-type silicon wafer. The front side is plasma-etched to form a pyramid structure and doped with boron to form a pn junction. The average absorptivity in the solar radiation band is 0.98, and the average emissivity in the mid-infrared band is 0.95.

[0056] The back electrode 34 is made of a 300 nm thick aluminum film, which is deposited on the back of the photoelectric-thermal conversion layer 33 by magnetron sputtering.

[0057] The overall photovoltaic efficiency of the spectrally selective photothermal / photoelectric conversion collector 3 can reach 18%. When installing, first cover the top of the lander 10 with a backboard 35, and then Figure 4 As shown, the back plate 35, the partition 42, and the shell of the lander 10 form a sealed space, encapsulating the water-ice phase change energy storage device 4 within the space to prevent the collected water-ice phase material from evaporating or leaking. Specifically, the back plate 35 can be a copper plate, and the spectrally selective photothermal / photoelectric conversion heat collector plate 3 is fixedly mounted on the copper plate. At the same time, to prevent the back electrode 34 from being conductive after being bonded to the copper plate, a layer of insulating glue can be applied to the side of the copper plate facing the water-ice phase change energy storage device 4. The insulating glue can be made of polyvinyl alcohol or polyolefin elastomer to prevent the copper plate from discharging into the sealed space. Similarly, the flow medium pipeline 5 fixedly mounted on the back plate 35 can also be coated with insulating glue to prevent discharge.

[0058] 3. Optical window 2:

[0059] like Figure 4 As shown, optical window 2 is installed over the entire spectrally selective solar thermal / photoelectric conversion collector panel 3. It is made of a material with a transmittance greater than 0.90 in the solar band, specifically quartz glass. The main function of optical window 2 is to allow sunlight to pass through while protecting the spectrally selective solar thermal / photoelectric conversion collector panel 3 from the harsh environment of the Martian surface, such as sand, dust, and small rock impacts.

[0060] 4. Water ice phase change energy storage device 4:

[0061] The water-ice phase change energy storage device 4 includes an energy storage box 41, such as Figure 4 As shown, energy storage tank 41 is fixedly mounted above partition 42 within lander 10. Below partition 42 are heating loads 8, which include batteries, electromagnetic relays, and microelectromechanical systems (MEMS) devices, which are susceptible to damage or failure due to low temperatures. The entire energy storage tank 41 acts as a container for storing water-ice materials introduced by water collector 13.

[0062] When the ambient temperature is low, the water-ice phase material in the energy storage box 41 can release heat because the bottom of the energy storage box 41 is in contact with the partition 42. Specifically, the partition 42 and the energy storage box 41 can be made of aluminum alloy. By utilizing the good thermal conductivity of both, the heat released by the water-ice phase material can be transferred to the space below the partition 42 where the heating load 8 is located, thereby increasing the ambient temperature in the space and ensuring that various electronic components can work stably.

[0063] Optionally, in order to avoid heat dissipation and waste, as Figure 4As shown, an aerogel insulation layer 6 can be filled around the energy storage tank 41 and the heating load 8 in the lander 10 to improve the thermal insulation performance inside the lander 10.

[0064] Furthermore, a liquid level gauge can be installed on the side wall of the energy storage tank 41. The liquid level gauge can provide feedback on the current liquid level in the energy storage tank 41. The controller and ground engineers can use the liquid level data provided by the liquid level gauge to determine and control whether the mobile in-situ water extractor 1 needs to continue operating, and ensure that there is still a gap of 5-8 cm between the liquid water level in the energy storage tank 41 and the back plate 35. This prevents the expansion of liquid water after freezing and damaging components such as the energy storage tank 41 and the back plate 35.

[0065] 5. Flowing medium pipeline 5:

[0066] The flow medium pipeline 5 can be a capillary heat pipe, the interior of which can be filled with ammonia water with a concentration of 99.99%. Specifically, a plurality of capillary heat pipes are arranged in an array on the side of the back plate 35 facing the water-ice phase change energy storage device 4. One end of the capillary heat pipe is welded and fixed to the back plate 35, and the other end is immersed in the water-ice phase change material contained in the water-ice phase change energy storage device 4. The capillary heat pipe connects the spectrally selective photothermal / photoelectric conversion collector plate 3 and the water-ice phase change energy storage device 4 as a channel for heat transfer, so that the heat energy generated by the spectrally selective photothermal / photoelectric conversion collector plate 3 can be smoothly transferred to the water-ice phase change energy storage device 4 for storage. The flow medium in the capillary heat pipe circulates under the drive of pressure and capillary force to achieve effective heat transfer.

[0067] During the Martian daytime, when the temperature of the back plate 35 of the spectrally selective photothermal / photoelectric conversion collector 3 is higher than the phase change temperature, the ammonia water in the capillary heat pipe evaporates and moves to the bottom of the capillary heat pipe under the action of capillary force, storing the heat generated by the spectrally selective photothermal / photoelectric conversion collector 3 in the water-ice phase change material; during the Martian nighttime, the ambient temperature drops, and the water-ice phase change material energy storage device supplies heat to the electronic instruments and equipment through heat conduction, first releasing sensible heat and then releasing latent heat of phase change, thereby maintaining the normal operating temperature of the electronic instruments and equipment.

[0068] In addition, if Figure 3 As shown, photovoltaic panels 9 are also installed on the flanks of lander 10. These panels are primarily used to generate electricity to meet some of the lander's power needs, such as charging batteries and driving electronic equipment onboard. Together with the spectrally selective photothermal / photovoltaic conversion collector panels 3, these panels provide power to lander 10, improving the reliability and stability of its energy supply.

[0069] The photovoltaic panel 9 is a common energy supply device on the lander 10. Its specific structure, installation method, and material are all mature existing technologies and are not the design core of the present invention, so they will not be described here.

[0070] 2. Working Principle

[0071] After the Mars lander 10 arrives at the designated location on the Martian surface, the mobile in-situ water extractor 1 begins operation. The deep-groove auger 11 drills into the ice layer or permafrost, collects the pyrosol containing water ice, and retains it in the trough. The cylindrical heat exchanger 12 heats the pyrosol in the trough, sublimating the water ice therein into gas. Under the action of pressure, the generated water vapor enters the water collector 13 through the first one-way valve 131, and condenses into liquid water in the water collector 13. The collected water then flows into the water ice phase change energy storage device 4 through the second one-way valve 132 under the action of gravity, providing water ice material for the phase change energy storage process.

[0072] During the Martian daytime, the spectrally selective photothermal / photoelectric conversion collector panels 3 absorb solar radiation, converting some of it into electricity, which is then used to directly power electronic equipment on the lander 10 or stored in batteries. The remaining portion is converted into heat. When the temperature of the backing plate 35 beneath the spectrally selective photothermal / photoelectric conversion collector panels 3 exceeds the water-ice phase-change temperature, the ammonia in the capillary heat pipe evaporates and, under the action of capillary forces, moves to the bottom of the capillary heat pipe, storing the heat generated by the spectrally selective photothermal / photoelectric conversion collector panels 3 in the water-ice phase-change material, causing it to absorb the heat and undergo a phase change to store energy. During the Martian nighttime, the ambient temperature drops rapidly, at which point the water-ice phase-change material in the water-ice phase-change energy storage device 4 begins to release heat to the heating load 8 through the partition 42. Sensible heat is released first. As the temperature further decreases, the water-ice phase-change material undergoes a phase change, releasing a large amount of latent heat. During this phase change, the temperature remains essentially constant at around 0°C, providing stable thermal energy for electronic equipment and ensuring their normal operation in low-temperature environments.

[0073] In summary, the Mars lander thermal control system of the present invention has outstanding features and advantages in terms of technical solutions, performance and application prospects. It is expected to provide an efficient, reliable and economical thermal control solution for the Mars exploration mission, and promote the further development and breakthroughs of space exploration technology.

[0074] Although the present invention has been described in detail above using general descriptions and specific embodiments, it will be apparent to those skilled in the art that modifications and improvements may be made thereto. Therefore, such modifications and improvements, without departing from the spirit of the present invention, are intended to be within the scope of protection claimed herein.

Claims

1. Mars lander thermal control system, characterized by: include: A mobile in-situ water extractor (1) is vertically mounted on the exterior of the lander (10) for collecting water ice from the Martian environment and transporting it to the water ice phase change energy storage device (4); The water-ice phase-change energy storage device (4) is installed inside the lander (10) and is attached to the heating load (8) inside the lander (10) through a partition (42) to store and supply heat to the heating load (8); A spectrally selective photothermal / photoelectric conversion heat collecting panel (3), covered on the top of the lander (10) via a back panel (35), for collecting solar energy and converting it into electrical energy and thermal energy; A flowing working medium pipeline (5) connects the spectrally selective photothermal / photoelectric conversion heat collecting plate (3) and the water-ice phase change energy storage device (4).

2. The Mars lander thermal control system according to claim 1, characterized in that: The mobile in-situ water extractor (1) is installed on the rear surface of the lander (10) and includes a deep groove auger (11), a cylindrical heat exchanger (12), a water collector (13) and a telescopic cylinder (14); The cylindrical heat exchanger (12) is hollow inside and has an inner wall with electric heating wires spirally arranged along the height direction. The cylindrical heat exchanger (12) is fixedly connected to the rear surface of the lander (10); The deep groove spiral drill (11) is coaxially mounted inside the cylindrical heat exchanger (12), and comprises a drill rod (111) and a motor (112) for driving the drill rod (111) to rotate; The telescopic cylinder (14) is fixedly mounted on the end of the cylindrical heat exchanger (12), and the telescopic end of the telescopic cylinder (14) extends into the interior of the cylindrical heat exchanger (12) and is fixedly connected to the motor (112); The water collector (13) is fixedly mounted on the outside of the cylindrical heat exchanger (12), one side of which is in communication with the inner cavity of the cylindrical heat exchanger (12), and the other side of which is in communication with the water-ice phase change energy storage device (4) through a pipeline, and is used to collect steam generated by the fire soil containing water ice drilled by the deep groove spiral drill (11) after being heated by the electric heating wire, and then liquefy the steam and introduce it into the water-ice phase change energy storage device (4).

3. The Mars lander thermal control system according to claim 2, characterized in that: An inlet is provided at the upper end of one side of the water collector (13) close to the cylindrical heat exchanger (12), and the inlet extends to the inner cavity of the cylindrical heat exchanger (12) through a pipe; An outlet is provided at the lower end of the water collector (13) on a side away from the cylindrical heat exchanger (12), and the outlet is connected to the water-ice phase change energy storage device (4) through a pipeline; A first one-way valve (131) is installed at the inlet, and a second one-way valve (132) is installed at the outlet.

4. The Mars lander thermal control system according to claim 3, characterized in that: The opening and closing pressures of the first one-way valve (131) and the second one-way valve (132) are adjustable, so that the liquid level of the liquid water in the water collector (13) is always maintained at one quarter of the inner cavity height of the water collector (13).

5. The Mars lander thermal control system according to claim 1, characterized in that: It also includes an optical window (2), which is installed to cover the top of the spectrally selective photothermal / photoelectric conversion heat collecting plate (3).

6. The Mars lander thermal control system according to claim 5, characterized in that: The optical window (2) is made of a material with a transmittance greater than 0.90 in the solar band, and the material includes quartz glass.

7. The Mars lander thermal control system according to claim 1, characterized in that: The water-ice phase change energy storage device (4) comprises an energy storage box (41), wherein the energy storage box (41) contains liquid water and is fixedly installed above the heating load (8) via a partition (42); A through hole is provided on a side of the energy storage box (41) close to the mobile in-situ water extractor (1) for introducing liquid water; The energy storage box (41) and the heating load (8) are both filled and wrapped with an aerogel insulation layer (6).

8. The Mars lander thermal control system according to claim 1, characterized in that: The fluid pipe (5) is a capillary heat pipe; One end of the capillary heat pipe is fixed to the back side of the back plate (35), and the other end is immersed in the water-ice phase change material contained in the water-ice phase change energy storage device (4).

9. The Mars lander thermal control system according to claim 1, characterized in that: The fluid medium filled in the fluid medium pipeline (5) is ammonia water.

10. The Mars lander thermal control system according to claim 1, characterized in that: The spectrally selective photothermal / photoelectric conversion heat collecting plate (3) comprises a laminated structure, which comprises an encapsulation layer (31), a transparent electrode (32) layer, a photoelectric / photothermal conversion layer (33) and a back electrode (34) layer in sequence; The transparent electrode (32) layer is a metal nano-grid structure, and the photoelectric conversion layer is a semiconductor material.

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