A thermal management system for light-thermal-electric energy recovery in space environment

Abstract

The present application belongs to the technical field of space electronic equipment energy and heat management, and relates to a heat management system for light-heat-electric energy recovery in a space environment, comprising: a variable-direction dredging structure, a one-way conductive PN junction, a thermoelectric metal power generation structure, a cooling emission nozzle, a graphene foam phase change nanoparticle, a gradient arc-shaped porous capillary core, a liquid collecting support rod, a tracking sun rotating shaft, a battery, a control system, a photovoltaic panel, the one-way conductive PN junction is electrically connected to the battery, the thermoelectric metal power generation structure is electrically connected to the battery, the battery is electrically connected to the tracking sun rotating shaft and the control system, and the control system is electrically connected to the tracking sun rotating shaft; through the variable-direction dredging structure, a multi-stage light-heat-electric conversion system, intelligent heat management and working medium recycling, the present application realizes efficient collection of solar energy, waste heat recycling and system light weight.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of space electronic equipment energy and thermal management, and particularly relates to a thermal management system for light-heat-electric energy recovery in a space environment. BACKGROUND

[0002] A spacecraft needs to cope with extreme temperature differences in space, and its thermal management can achieve thermal balance of the spacecraft's sunny side against overheating and the shady side against overcooling through the combination of active and passive technologies, thereby ensuring stable operation of the equipment. Existing space electronic equipment heat exchange usually has the following ways: 1. arranging thermal insulation materials or phase change layers on the back plate to control the temperature of the shell. 2. using a separate light shield to isolate the shell from thermal radiation. 3. liquid working medium return relies on a mechanical pump. However, the existing space electronic equipment heat exchange has the following defects:

[0003] 1. In a space environment, the surface of the equipment and the photovoltaic panel face extreme temperature fluctuations (-150 °C to +150 °C), and the traditional fixed photovoltaic panel lacks temperature self-adaptive adjustment capability, resulting in increased brittleness of the photovoltaic material at low temperatures and easy breakage; at high temperatures, the photoelectric conversion efficiency decreases (0.4% reduction in silicon-based photovoltaic efficiency per 1 ℃ increase).

[0004] 2. Traditional phase change thermal insulation materials (such as paraffin) can only passively store heat and cannot convert heat into usable energy, resulting in more than 60% of the absorbed heat being wasted by being discharged into space through a radiator; the thermal cycle efficiency is low.

[0005] 3. The existing spacecraft thermal control system directly discharges more than 90% of the waste heat through a radiator, without energy utilization.

[0006] 4. The split design results in independent photovoltaic, thermoelectric, and heat pipe systems, increasing the mass redundancy; the interface thermal resistance loss is large.

[0007] 5. The independent thermoelectric module requires additional support structure, resulting in an increase in system mass per square meter; the thermal interface material occupies about 20% of the system volume.

[0008] Therefore, an integrated solution is needed to improve the efficiency, energy utilization rate, and reliability of space electronic equipment heat exchange to solve the above technical problems. SUMMARY

[0009] The present application aims to provide an integrated solar photoelectric conversion, thermoelectric recovery, and intelligent thermal management system suitable for a space environment.

[0010] The present application provides the following technical solution: a thermal management system for light-heat-electric energy recovery in a space environment, comprising:

[0011] Variable direction guiding structure, for opening photovoltaic panel at temperature higher than threshold value by shape memory alloy temperature deformation, and folding photovoltaic panel at temperature lower than threshold value.

[0012] One-way conductive PN junction, for generating electricity by temperature difference and transmitting to battery storage. One-way conductive PN junction can be provided with first one-way conductive PN junction at arc-shaped sunshade curtain side (same as outer layer of photovoltaic panel), and second one-way conductive PN junction at shell side.

[0013] Thermoelectric metal power generation structure, for generating electricity by temperature difference between inner and outer layers of spacecraft cabin and transmitting to battery storage.

[0014] Cooling emission nozzle, for spraying steam mist containing ions through gradient arc-shaped porous capillary core and porous phase change material, generating current and conducting heat circulation between inner and outer layers of cabin.

[0015] Graphene foam phase change nanoparticles, for quickly absorbing heat of steam mist.

[0016] Gradient arc-shaped porous capillary core, for absorbing liquid working medium condensed after steam mist.

[0017] Liquid collecting support rod, for storing liquid working medium absorbed by gradient arc-shaped porous capillary core and transmitting back to cooling emission nozzle for next heat circulation.

[0018] Sun tracking axis, for adjusting incident angle of variable direction guiding structure and sunlight.

[0019] Battery, for storing electric energy generated by photovoltaic panel, one-way conductive PN junction and thermoelectric metal power generation structure and supplying power to system.

[0020] Control system, for adjusting rotation of sun tracking axis through feedback control of light sensor and temperature sensor.

[0021] Photovoltaic panel, one-way conductive PN junction and thermoelectric metal power generation structure are respectively electrically connected to battery, battery is electrically connected to sun tracking axis and control system, and control system is electrically connected to sun tracking axis.

[0022] Variable direction guiding structure is arranged on outer side of outer layer of spacecraft cabin, thermoelectric metal power generation structure is arranged between inner and outer layers of spacecraft cabin, cooling emission nozzle is arranged on outer side of inner layer of spacecraft cabin, graphene foam phase change nanoparticles, gradient arc-shaped porous capillary core and liquid collecting support rod are arranged on inner side of outer layer of spacecraft cabin, emission direction of cooling emission nozzle is towards gradient arc-shaped porous capillary core, and liquid collecting support rod respectively connects gradient arc-shaped porous capillary core and cooling emission nozzle.

[0023] Preferably, the variable-direction guiding structure is a sector that can be folded around the center of the circle, and the photovoltaic panel, the cold-end shape memory alloy chain and the hot-end shape memory alloy chain are arranged on each sector of the sector.

[0024] More preferably, the photosensitive sensor and the temperature sensor are arranged at the arc-shaped end of the sector.

[0025] More preferably, the variable-direction guiding structure is made of a titanium-nickel shape memory alloy chain.

[0026] Preferably, the one-way conductive PN junction comprises a P-type semiconductor and an N-type semiconductor electrically connected by a conductive sheet, and the P-type semiconductor and the N-type semiconductor are respectively structureally bonded to the photovoltaic panel.

[0027] More preferably, the outer side of the inner layer of the spacecraft cabin body is provided with a P-type semiconductor and an N-type semiconductor electrically connected by a conductive sheet, and the P-type semiconductor and the N-type semiconductor are respectively electrically connected to the battery.

[0028] Preferably, the graphene foam phase change nanoparticles are embedded between the one-way conductive PN junction and the gradient arc-shaped porous capillary core.

[0029] Preferably, the gradient arc-shaped porous capillary core is provided with multiple levels of porosity gradient.

[0030] More preferably, the gradient arc-shaped porous capillary core is sequentially provided with a microgravity working medium capturing gradient, a gas phase separation gradient, a liquid phase enrichment gradient and a high-pressure directional backflow gradient along the jetting direction of the cooling and launching nozzle, the porosity of the microgravity working medium capturing gradient is 75-85%, the porosity of the gas phase separation gradient is 55-65%, the porosity of the liquid phase enrichment gradient is 35-45%, and the porosity of the high-pressure directional backflow gradient is 15-25%.

[0031] Preferably, the liquid collecting support rod is provided with a liquid working medium recycling valve at the communication position of the cooling and launching nozzle.

[0032] The beneficial effects of the present application are:

[0033] 1. The present application realizes efficient collection of solar energy, waste heat recycling and system lightening through the variable-direction guiding structure, multi-stage photo-thermal-electric conversion system, intelligent thermal management and working medium recycling.

[0034] 2、The dynamic light pursuit optimizes photovoltaic efficiency, the variable direction dredging structure of the application is expanded through shape memory alloy chain temperature self-adaption, combining with the feedback control of photosensitive sensor, so that the photovoltaic panel always keeps the best incident angle with sunlight, improves the photoelectric conversion efficiency by more than 30%. Compared with the fixed photovoltaic system, the application can continuously maximize the absorption of solar radiation during the orbit operation, and reduce the influence of shadow shielding.

[0035] 3、The application enhances energy collection through multi-stage semiconductor power generation, the photovoltaic panel utilizes solar power generation, the one-way conductive PN junction utilizes the temperature difference between direct sunlight and shadow to generate electricity, and the thermoelectric metal power generation structure utilizes the temperature difference between the inside and outside of the cabin to generate electricity, ensuring continuous and stable energy supply. The thermoelectric metal emission plate and the collection plate utilize steam mist to transport electrons, and additional heat energy is recovered to generate electricity, so that the overall thermoelectric conversion efficiency of the system is improved to 15-18%.

[0036] 4、The graphene foam phase change nanoparticles of the application can quickly condense steam, and the steam mist can complete condensation in a short time after contacting the high-thermal-conductivity graphene foam phase change material, greatly improving the heat exchange efficiency.

[0037] 5、The gradient capillary core pump-free self-return of the application can reduce energy consumption, and the porosity gradient design is adopted, so that the liquid working medium automatically flows to the liquid collection chamber under the action of capillary force, reducing the power consumption of the traditional mechanical pump by more than 40%.

[0038] 6、The intelligent temperature control of the application can recycle working medium, when the temperature sensor in the shell detects overheating, the control system automatically opens the liquid working medium recycling valve, so that the working medium flows through the heat absorption channel to absorb heat and vaporize, realizing closed-loop thermal management and avoiding damage to the shell equipment caused by heat accumulation.

[0039] 7、The application can realize one material with multiple functions and reduce redundant structures, the variable direction dredging structure of the application has the functions of photovoltaic support, light pursuit adjustment and temperature self-adaptive deformation, reducing the quality of the traditional independent driving mechanism. The thermoelectric metal plate is integrated in the PN junction structure, and simultaneously undertakes power generation and heat radiation, optimizing the space utilization rate.

[0040] 8、The application can reduce mechanical moving parts and reduce failure rate, the shape memory alloy chain of the application replaces the traditional motor drive, avoiding mechanical wear and tear and improving the reliability and service life of the expanded structure; the self-return characteristic of the gradient capillary core reduces the dependence on the pump and reduces the system maintenance requirement. The phase change material enhances the adaptability to extreme environments: the graphene foam phase change nanoparticles can work stably in the range of-100 °C to 300 °C, and are suitable for near-earth orbit, moon and deep space missions. BRIEF DESCRIPTION OF DRAWINGS

[0041] Fig. 1 It is a principle diagram of a light-heat-electricity energy recovery thermal management system in a space environment.

[0042] Fig. 2 Variable-directional guiding structure of the present application;

[0043] Fig. 3 Variable-directional guiding structure of the present application;

[0044] Fig. 4 Arc-shaped porous capillary core of the present application;

[0045] Fig. 5 Control system of the present application.

[0046] In the figure, 1, variable-directional guiding structure, 101, photovoltaic panel, 102, cold-end shape memory alloy chain, 103, hot-end shape memory alloy chain; 2, one-way conductive PN junction, 201, P-type semiconductor, 202, N-type semiconductor, 203, conductive sheet; 3, thermoelectric metal power generation structure, 301, thermoelectric metal emission plate, 302, thermoelectric metal collection plate, 303, emission electron; 4, cooling emission nozzle, 401, steam mist, 402, nozzle driving pump, 403, liquid working medium heat absorption flow channel, 404, liquid working medium recycling valve; 5, graphene foam phase change nanoparticles; 6, gradient arc-shaped porous capillary core, 601, first gradient porosity capillary core, 602, second gradient porosity capillary core, 603, third gradient porosity capillary core, 604, fourth gradient porosity capillary core, 605, capillary core liquid backflow outlet; 7, liquid collecting support rod, 701, liquid collecting cavity; 8, tracking sun rotating shaft; 9, battery; 10, control system, 1001, photosensitive sensor, 1002, temperature sensor. DETAILED DESCRIPTION

[0047] The related technologies in the present application will be described clearly and completely below in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all the other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the present application.

[0048] As Figs. 1-5As shown, the main components of the space environment light-heat-electric energy recycling thermal management system of the present embodiment include: a variable-direction guiding structure 1, a photovoltaic panel 101, a cold-end shape memory alloy chain 102, a hot-end shape memory alloy chain 103; a one-way conductive PN junction 2, a P-type semiconductor 201, an N-type semiconductor 202, a conductive sheet 203; a thermoelectric metal power generation structure 3, a thermoelectric metal emission plate 301, a thermoelectric metal collection plate 302, an emission electron 303; a cooling emission nozzle 4, a steam mist 401, a nozzle driving pump 402, a liquid working medium heat absorption flow channel 403, a liquid working medium recycling valve 404; a graphene foam phase change nanoparticle 5; a gradient arc-shaped porous capillary core 6, a first gradient porosity capillary core 601, a second gradient porosity capillary core 602, a third gradient porosity capillary core 603, a fourth gradient porosity capillary core 604, a capillary core liquid return outlet 605; a liquid collecting support rod 7, a liquid collecting cavity 701; a tracking sun rotating shaft 8; a battery 9; a control system 10, and a photosensitive sensor 1001 arranged uniformly on each photovoltaic panel 101 arrangement surface of the variable-direction guiding structure 1, and a temperature sensor 1002 arranged uniformly on the inner surface of the shell.

[0049] The space environment light-heat-electric energy recycling thermal management system, the photovoltaic panel 101 is fixedly installed and arranged on each fan leaf of the variable-direction guiding structure 1, the expanded end and the contracted end are the hot-end shape memory alloy chain 103 and the cold-end shape memory alloy chain 102 respectively, the shape memory alloy expands and contracts according to the change of temperature, and the expanded angle is automatically adjusted according to the environmental temperature: the hot-end shape memory alloy chain 103 elongates when the temperature is greater than the transition threshold, and the cold-end shape memory alloy chain 102 contracts when the temperature is less than the threshold. The variable-direction guiding structure 1 can adopt a titanium-nickel shape memory alloy chain, which automatically adjusts under the change of space environmental temperature: when the temperature of the sun-facing surface is higher than 80℃, the hot-end shape memory alloy chain 103 elongates to expand the photovoltaic panel 101; when the temperature of the sun-shielding surface is lower than -50℃, the cold-end shape memory alloy chain 102 contracts to fold.

[0050] A plurality of photosensitive sensors 1001 and a plurality of temperature sensors 1002 are arranged on the distal end and the proximal end of each fan surface of the variable-direction guiding structure 1. The signal of the photosensitive sensor 1001 is fed back to the control system 10, and the control system 10 controls the rotation of the tracking sun rotating shaft 8, so as to cause the variable-direction guiding structure 1 to maintain a 90° incident angle with sunlight, thereby ensuring the maximum photoelectric conversion efficiency. The double-mode sensing control has higher precision and faster response, and is suitable for more complex and fluctuating space environments.

[0051] P-type semiconductor 201 and N-type semiconductor 202 are connected by conductive sheet 203 to form a "bridge" structure, and the P and N semiconductors and conductive sheet 203 are arranged in an arc shape in series, and the two ends are connected by insulating bonding to photovoltaic panel 101, one end is positive and the other end is negative, and the generated current is collected into battery 9 for use of the power inside the shell and the start of the nozzle driving pump 402 of the system. The arc-shaped PN junction array: P-type semiconductor 201 / N-type semiconductor 202 is arranged in an arc shape with a large curvature radius, and the electron mobility is significantly improved in the vacuum environment of space.

[0052] In addition, there are also P-type semiconductor 201 and N-type semiconductor 202 on the inner surface of the shell, and conductive sheet 203 connects the two, presenting an array of concave structures. The generated current is collected into battery 9. The cabin wall embedded thermoelectric layer generates power using the temperature difference between the inside and outside of the cabin, and realizes parallel power supply with the photovoltaic system.

[0053] Graphene foam phase change nanoparticles 5 are embedded in the PN structure and gradient arc-shaped porous wick of the light-shielding curtain, and are tightly connected to P-type semiconductor 201, conductive sheet 203, and N-type semiconductor 202 on one side, and are tightly connected to gradient arc-shaped porous wick 6 on the other side. The structure of graphene foam phase change nanoparticles 5 can quickly absorb the heat of the steam mist 401 sprayed by several cooling emission nozzles 4, so that the steam mist 401 is quickly condensed into liquid. After the steam mist 401 is condensed and liquefied by the graphene foam phase change nanoparticles 5, it is recycled to the liquid collection cavity 701 through the gradient arc-shaped porous wick 6 so that it can be recycled. Compared with the use of a single gradient arc-shaped porous wick 6, the overall condensation rate is significantly improved, and the cabin temperature is efficiently maintained.

[0054] The liquid working medium is then absorbed by the gradient arc-shaped porous wick 6. It is worth noting that the gradient arc-shaped porous wick 6 has a four-stage porosity gradient structure, with a porosity decreasing from 80% (at the liquid return outlet of the wick) to 20% (at the farthest end) at a constant and uniform gradient. The present embodiment uses four different gradients of 80% (microgravity working medium capture), 60% (gas phase separation), 40% (liquid phase enrichment), and 20% (high-pressure directional return). The present application can have N gradients. The liquid working medium is actively directed to flow towards the liquid return outlet of the wick, saving pump power and achieving working medium recycling.

[0055] The liquid working medium that is refluxed is stored in the liquid collecting cavity 701 of the liquid collecting support rod 7. When it is needed to be reused, the control system sends a command to open the liquid working medium reuse valve according to the signal of the temperature sensor 1002 on the inner surface of the shell, and the liquid working medium flows into the liquid working medium heat absorption channel 403, absorbs the heat accumulation of the shell caused by solar radiation and space radiation, and becomes steam mist, which is sprayed out by the cooling emission nozzle 4 driven by the spray head driving pump, thereby realizing single structure and saving the space and mass of the spacecraft. Intelligent heat cycle: when the surface temperature is greater than 85℃, the liquid working medium reuse valve 404 is opened, and the working medium is vaporized and sprayed after flowing through the high heat flux density area (such as the CPU module).

[0056] The thermoelectric metal emission plate 301 and the cooling emission nozzle 4 are located in the inner recess of the side PN structure of the shell, and the thermoelectric metal collecting plate 302 is arranged in the “bridge” structure of the PN structure of the light shielding curtain. The steam mist 401 will wrap and transport the ions emitted by the thermoelectric metal emission plate 301 through the gradient arc-shaped porous capillary core 6 and the porous phase change material, and be absorbed by the thermoelectric metal collecting plate 302 to form an additional current, thereby forming a multi-stage and multi-functional power generation. The steam mist 401 is electronically transported through the thermoelectric metal emission plate 301, and the electron emission efficiency is effectively improved under the condition of high vacuum in space. After being captured by the thermoelectric metal collecting plate 302, an additional current is formed. In addition, the surface of the thermoelectric metal emission plate 301 is coated with a hafnium carbide (HfC) radiation-resistant layer, and the electron emission stability is improved by 30%.

[0057] The temperature sensor 1002 is used to monitor the temperature difference between the inside and outside of the shell, and the opening and closing of the liquid working medium reuse valve 404 is controlled. When the temperature is greater than the set value, the spray head driving pump 402 drives the working medium to enter the liquid working medium heat absorption channel 403 to vaporize, thereby completing the heat cycle.

[0058] The technical effect of the embodiment is also:

[0059] 1. The variable direction dredging structure 1 (self-adaptive light chasing + temperature driven deformation) is driven by a folding fan unfolding mechanism of shape memory alloy chain: the hot end shape memory alloy chain 103 and the cold end shape memory alloy chain 102 automatically adjust the unfolding angle according to the temperature, replace the traditional motor drive, and realize self-adaptive deformation without power consumption. Temperature-unfolding amount nonlinear mapping: the elongation rate of the hot end chain is greater than 8% at high temperature, and the contraction rate of the cold end chain is greater than 5% at low temperature, so as to ensure that the photovoltaic panel 101 is always at the optimal light receiving angle.

[0060] 2. Multi-stage semiconductor energy harvesting (photovoltaic + thermoelectric + electron transport power generation) arc-shaped PN junction bridge circuit design: P-type semiconductor 201 / N-type semiconductor 202 and conductive sheet 203 are arranged in an arc shape with a curvature radius R=50mm, increasing the effective contact area and improving the current density. The thermoelectric layer is embedded in the shell: the concave PN junction array generates electricity using the temperature difference (ΔT≥50K) between the inner and outer surfaces of the shell, complementing the photovoltaic system. Vapor mist electron transport technology: emitted electrons 303 generated by the thermoelectric metal emission plate 301 are wrapped by the vapor mist 401, and are captured by the thermoelectric metal collection plate 302 after penetrating the gradient arc-shaped porous capillary core 6, realizing thermoelectric-fluid three-field coupling power generation.

[0061] 3. Graphene foam phase change nanoparticle 5 enhanced condensation: ultra-fast condensation characteristic graphene foam greatly shortens the vapor condensation time. Integrated structure and function design: nanoparticles are embedded in the pores of the gradient arc-shaped porous capillary core 6, simultaneously serving as condensation, electron transport, and mechanical support.

[0062] 4. Gradient arc-shaped porous capillary core 6 (pump-free self-driven backflow), step porosity capillary core realizes sequential changes of liquid working medium: rapid absorption of liquid working medium (porosity: 20%) — preliminary directional guidance of flow (porosity: 40%) — acceleration of working medium transport (porosity: 60%) — high-pressure output to the liquid collection chamber (porosity: 80%). Arc-shaped flow channel optimization: the curvature radius matches the steam injection angle (15° to 30°), reducing flow resistance and gradually increasing backflow speed.

[0063] 5. Intelligent thermal management control system, multi-parameter collaborative regulation: temperature sensor 1002 monitors 6 key points, combined with photovoltaic panel 101 output power, vapor pressure, etc. data, dynamically adjusts the opening degree of liquid working medium reuse valve 404 and the speed of spray head drive pump 402.

[0064] In summary, the present application realizes efficient collection of solar energy, waste heat recovery and utilization, and system light weight through variable direction dredging structure, multi-stage photothermal-electric conversion system, intelligent thermal management and working medium recycling, etc. technical means, and can be widely applied to space stations, deep space probes, lunar / mars bases and other space missions, having broad application prospects.

[0065] It should be emphasized that the above is only a preferred embodiment of the present application, and does not limit the present application in any form. Any simple modification, equivalent change and modification of the above embodiment according to the technical essence of the present application still belongs to the scope of the technical solution of the present application.

Claims

1. A thermal management system for light-heat-electricity energy recovery in space environment, characterized in that, Comprise: Variable direction guiding structure (1) for opening photovoltaic panel (101) by shape memory alloy temperature deformation when temperature is higher than threshold value, and folding photovoltaic panel (101) when temperature is lower than threshold value; One-way conductive PN junction (2) for generating electricity by temperature difference and transmitting to battery (9) storage; Thermoelectric metal power generation structure (3) for generating electricity by spacecraft cabin inner and outer temperature difference and transmitting to battery (9) storage; Cooling emission nozzle (4) for spraying steam mist (401) containing ions through gradient arc-shaped porous capillary core (6) and porous phase change material, generating electric current and conducting heat circulation between cabin inner and outer layers; Graphene foam phase change nanoparticles (5) for quickly absorbing heat of steam mist (401); Gradient arc-shaped porous capillary core (6) for absorbing liquid working medium after steam mist (401) condensation; Liquid collecting support rod (7) for storing liquid working medium absorbed by gradient arc-shaped porous capillary core (6) and transmitting back to cooling emission nozzle (4) for next heat cycle; Sun tracking axis (8) for adjusting the incidence angle of variable direction guiding structure (1) and sunlight; Battery (9) for storing electric energy generated by photovoltaic panel (101), one-way conductive PN junction (2) and thermoelectric metal power generation structure (3) and supplying power to the system; Control system (10) for adjusting the rotation of sun tracking axis (8) through the feedback control of photosensitive sensor (1001) and temperature sensor (1002); The photovoltaic panel (101), one-way conductive PN junction (2) and thermoelectric metal power generation structure (3) are respectively electrically connected to the battery (9), the battery (9) is electrically connected to the sun tracking axis (8) and control system (10), and the control system (10) is electrically connected to the sun tracking axis (8); The variable direction guiding structure (1) is arranged on the outside of the outer layer of the spacecraft cabin, the thermoelectric metal power generation structure (3) is arranged between the inner and outer layers of the spacecraft cabin, the cooling emission nozzle (4) is arranged on the outside of the inner layer of the spacecraft cabin, the graphene foam phase change nanoparticles (5), gradient arc-shaped porous capillary core (6) and liquid collecting support rod (7) are arranged on the inside of the outer layer of the spacecraft cabin, the emission direction of the cooling emission nozzle (4) is towards the gradient arc-shaped porous capillary core (6), and the liquid collecting support rod (7) respectively communicates the gradient arc-shaped porous capillary core (6) and the cooling emission nozzle (4).

2. The thermal management system for light-thermal-electric energy recovery in space environment according to claim 1, wherein, The variable direction guiding structure (1) is a sector that can be contracted and folded around the center, each sector of the sector is provided with a photovoltaic panel (101), a cold end shape memory alloy chain (102) and a hot end shape memory alloy chain (103), the cold end shape memory alloy chain (102) is arranged at the center end of the sector, and the photovoltaic panel (101) and the hot end shape memory alloy chain (103) are arranged at the arc-shaped end of the sector.

3. The thermal management system for light-thermal-electric energy recycling in space environment according to claim 2, wherein, The photosensitive sensor (1001) and temperature sensor (1002) are arranged at the arc-shaped end of the sector.

4. The thermal management system for light-thermal-electric energy recycling in space environment according to claim 2, wherein, The variable direction guiding structure (1) is made of titanium-nickel shape memory alloy chain.

5. The photothermal-electric energy harvesting thermal management system of claim 1, wherein, The one-way conductive PN junction (2) comprises a P-type semiconductor (201) and an N-type semiconductor (202) electrically connected by a conductive sheet (203), and the P-type semiconductor (201) and the N-type semiconductor (202) are respectively insulated and bonded to the photovoltaic panel (101).

6. The thermal management system for light-thermal-electric energy recycling in space environment according to claim 5, wherein, The outer side of the spacecraft cabin inner layer is provided with a P-type semiconductor (201) and an N-type semiconductor (202) electrically connected by a conductive sheet (203), and the P-type semiconductor (201) and the N-type semiconductor (202) are respectively electrically connected to the battery (9).

7. The photothermal-electric energy harvesting thermal management system of claim 1, wherein, The graphene foam phase change nanoparticles (5) are embedded between the one-way conductive PN junction (2) and the gradient arc-shaped porous capillary core (6).

8. The thermal management system for light-thermal-electric energy recycling in space environment according to claim 1, wherein, The gradient arc-shaped porous capillary core (6) is provided with multiple levels of porosity gradient.

9. The thermal management system for light-heat-electric energy recovery in space environment according to claim 8, wherein, The gradient arc-shaped porous capillary core (6) is sequentially provided with a microgravity working medium capture gradient, a gas phase separation gradient, a liquid phase enrichment gradient, and a high-pressure directional backflow gradient along the jetting direction of the cooling and launching nozzle (4), the porosity of the microgravity working medium capture gradient is 75-85%, the porosity of the gas phase separation gradient is 55-65%, the porosity of the liquid phase enrichment gradient is 35-45%, and the porosity of the high-pressure directional backflow gradient is 15-25%.

10. The thermal management system for light-heat-electric energy recovery in space environment according to claim 1, wherein, The liquid collection support rod (7) is provided with a liquid working medium recycling valve (404) at the communication position with the cooling and launching nozzle (4).

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