A lunar exploration manned spacecraft thermal management system and control method

Abstract

The present application relates to a kind of lunar exploration manned spacecraft thermal management system and control method, thermal management system includes first heat transfer loop, second heat transfer loop, first heat transfer loop bypass, first heat transfer loop includes first heat transfer loop pump, first check valve, first temperature control valve, first heat exchanger first side, first self-locking valve, second heat exchanger, first radiator, second check valve, second temperature control valve, second temperature sensor, first temperature sensor, heat collection module, first liquid reservoir, second heat transfer loop includes first heat exchanger second side, compressor, second radiator, second liquid reservoir, dryer, expansion valve.The present application integrates single-phase fluid circuit, heat pump circulation loop into one, according to the change of task demand and external thermal environment, work mode is switched, the adaptability of lunar exploration manned spacecraft thermal management system under multi-task environment is realized, heat dissipation efficiency is greatly improved, and the area and weight of radiator are reduced.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft thermal control technology, and relates to a thermal management system and control method for a lunar exploration manned spacecraft. Background Technology

[0002] The lunar surface has an extremely complex thermal environment with large diurnal temperature variations and a day-night cycle of approximately 29 days. During the lunar day, the surface temperature increases with the solar altitude angle, reaching a maximum of 120°C. The effective heat dissipation temperature of the heat dissipation surface in a conventional manned spacecraft's single-phase fluid loop thermal management system is limited by the cabin temperature requirements, preventing an increase in surface temperature (approximately 10°C). Therefore, the heat dissipation capacity per unit area of ​​the radiator is limited (approximately 100 W / m²). 2 The lunar probe requires a large-area radiator to operate under the high temperatures of the lunar midday. This radiator area is enormous, resulting in a large system weight and large layout space. Heat pump technology, on the other hand, can increase the radiator temperature (above 50°C) and increase the heat dissipation capacity per unit area (approximately 300W / m²). 2 To achieve the same heat dissipation as manned spacecraft, heat pump technology can reduce the radiator area to 1 / 3 of that of a single-phase circuit, significantly reducing the radiator weight and layout space, and enabling optimized design of the thermal management system.

[0003] Currently, the application of heat pump thermal management systems in spacecraft is in the exploratory stage. In the microgravity of space, technical challenges such as compressor shaft lubrication need to be solved. During the launch and in-orbit flight of lunar manned spacecraft, the application of heat pump thermal management technology requires solving many technical challenges. However, after landing on the moon, due to the effect of lunar gravity, heat pump thermal management technology can be used with the help of mature terrestrial technologies. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a thermal management system and control method for a lunar exploration manned spacecraft. This method combines single-phase loop thermal management technology and heat pump thermal management technology. During the space flight phase and when the solar altitude angle on the lunar surface is low, a single-phase loop working mode is adopted. When the solar altitude angle on the lunar surface is high, a combined working mode of single-phase loop and heat pump circulation loop is adopted. This satisfies the heat dissipation requirements under the extreme high temperature environment on the lunar surface, as well as the heat dissipation requirements under the on-orbit flight and low solar altitude angle environment on the lunar surface.

[0005] The solution of the present invention is: a thermal management system for a lunar exploration manned spacecraft, comprising: a first heat transfer circuit, a second heat transfer circuit, and a bypass of the first heat transfer circuit; wherein the bypass of the first heat transfer circuit is provided with a second self-locking valve;

[0006] The first heat transfer circuit includes a heat collection module and is a single-phase fluid circuit. The first heat transfer circuit contains a circulating first heat transfer medium. After the heat collection module absorbs heat, it is transferred to the first heat transfer circuit through the first heat transfer medium for heat dissipation. The first heat transfer medium after heat dissipation flows back into the heat collection module to continue circulating. When temperature control is performed, the flow distribution of the first heat transfer medium in the first heat transfer circuit is adjusted according to the set target temperature, so that the temperature control point of the first heat transfer circuit reaches the set target temperature.

[0007] The second heat transfer loop is coupled to the first heat transfer loop and forms a heat pump circulation loop. The second heat transfer loop contains a circulating second heat transfer medium. When the second heat transfer loop is working, the heat absorbed by the first heat transfer medium is discharged into the second heat transfer loop at the coupling point to achieve cooling. After the first heat transfer medium is cooled, it flows through the bypass of the first heat transfer loop into the heat collection module and continues to circulate. The second heat transfer loop is used to dissipate the heat transferred by the first heat transfer medium.

[0008] The second self-locking valve is used to switch the working mode of the thermal management system. When the second self-locking valve is closed, the thermal management system operates in the mode of the first heat transfer circuit alone; when the second self-locking valve is open, the thermal management system operates in the mode of the first heat transfer circuit and the second heat transfer circuit working together.

[0009] Furthermore, the second heat transfer loop is coupled to the first heat transfer loop through the first heat exchanger.

[0010] Furthermore, the first heat transfer circuit also includes a first heat transfer circuit pump, a first check valve, a first temperature control valve, a first side of a first heat exchanger, a first self-locking valve, a second heat exchanger, a first radiator, a second check valve, a second temperature control valve, a second temperature sensor, a first temperature sensor, a bulkhead heating pipe, and a first liquid reservoir.

[0011] The output of the first heat transfer circuit pump is connected to the input of the first one-way valve. The output of the first one-way valve is connected to the input of the first temperature control valve. The first output of the first temperature control valve is connected to the input of the first side of the first heat exchanger. The output of the first side of the first heat exchanger is divided into a first output and a second output via a three-way valve. The first output of the first side of the first heat exchanger is connected to the input of the first self-locking valve. The second output of the first side of the first heat exchanger is connected to the input of the second self-locking valve. The output of the first self-locking valve is connected to the input of the first side of the second heat exchanger. The first output of the second heat exchanger is connected to the input of the first radiator. The output of the first radiator is connected to the input of the second one-way valve. The connection is as follows: the output end of the second one-way valve is connected to the input end of the second temperature control valve; the first output end of the second temperature control valve is connected to the second side input end of the second heat exchanger; the second side output end of the second heat exchanger and the second output end of the second temperature control valve merge and are then connected to the input end of the second temperature sensor; the output end of the second self-locking valve and the output end of the second temperature sensor merge with the second output end of the first temperature control valve, and then are connected to the input end of the first temperature sensor; the output end of the first temperature sensor is connected to the heat collection module; after passing through the heat collection module, it is connected to the input end of the bulkhead heating pipe; the output end of the bulkhead heating pipe is connected to the input end of the first liquid reservoir; and the output end of the first liquid reservoir is connected to the input end of the first heat transfer circuit pump.

[0012] Wherein, the first side of the first heat exchanger is the cold side, the first side of the second heat exchanger is the hot side, and the second side of the second heat exchanger is the cold side.

[0013] Furthermore, the second heat transfer circuit includes a second side of the first heat exchanger, a compressor, a second radiator, a second liquid receiver, a dryer, and an expansion valve;

[0014] The second side output end of the first heat exchanger is connected to the compressor input end, the compressor output end is connected to the second radiator input end, the second radiator output end is connected to the second liquid receiver input end, the second liquid receiver output end is connected to the dryer input end, the dryer output end is connected to the expansion valve input end, and the expansion valve output end is connected to the second side input end of the first heat exchanger.

[0015] The second side of the first heat exchanger is the hot side, and heat exchange is achieved between the second side and the first side of the first heat exchanger through the heat exchange components of the first heat exchanger itself.

[0016] Furthermore, it also includes a heat pipe, through which the first radiator and the second radiator are thermally coupled.

[0017] Furthermore, the first heat transfer medium is an aqueous solution of ethylene glycol or perfluorotriethylamine used in manned spacecraft.

[0018] Furthermore, the second heat transfer medium is R134a.

[0019] Furthermore, a control method for the thermal management system of a lunar exploration manned spacecraft is provided, including a control method for a first heat transfer loop operating independently. This independent operating mode of the first heat transfer loop is used in orbital flight or under low solar altitude angle conditions after lunar landing, and includes:

[0020] The second self-locking valve is closed and the first self-locking valve is opened. The heat absorbed by the heat collection module is transferred to the first heat transfer circuit through the first heat transfer medium. The first temperature control valve distributes the flow into the first side of the first heat exchanger at the initial opening. At this time, the first heat exchanger does not perform heat exchange.

[0021] The first heat transfer medium flows through the first radiator to dissipate heat to the outside. The second temperature control valve automatically adjusts its opening based on the difference between the temperature measured by the second temperature sensor and the set target temperature, thereby adjusting the flow distribution between the first and second output ends of the first temperature control valve. The first heat transfer medium at the first and second output ends of the first temperature control valve merges and flows into the second temperature sensor.

[0022] The first heat transfer medium flowing out of the second temperature sensor and the first heat transfer medium flowing out of the second output end of the first temperature control valve merge and enter the first temperature sensor. The first temperature control valve automatically adjusts its opening according to the difference between the temperature measured by the first temperature sensor and the set target temperature, thereby adjusting the flow rate into the first side of the first heat exchanger.

[0023] Repeatedly adjust the opening of the second and first temperature control valves until the temperatures measured by the second and first temperature sensors both reach the set target temperature.

[0024] Furthermore, a control method for the thermal management system of a lunar exploration manned spacecraft is provided, including a control method for a combined working mode of a first heat transfer loop and a second heat transfer loop. This combined working mode is used in high solar altitude angle environments after lunar landing, and includes:

[0025] The second self-locking valve is opened and the first self-locking valve is closed. The heat absorbed by the heat collection module is transferred to the first heat transfer circuit through the first heat transfer medium. The first temperature control valve distributes the flow into the first heat exchanger at the initial opening.

[0026] The temperature of the first heat transfer medium drops after heat exchange through the first heat exchanger. The second heat transfer loop receives the heat transferred by the first heat exchanger and dissipates it. The first heat transfer medium flows out of the first side output end of the first heat exchanger and flows into the bypass where the second self-locking valve is located.

[0027] The first heat transfer medium flowing out of the second self-locking valve and the first heat transfer medium flowing out of the second output end of the first temperature control valve merge and enter the first temperature sensor. The first temperature control valve automatically adjusts its opening according to the difference between the temperature measured by the first temperature sensor and the set target temperature, thereby regulating the flow rate into the first heat exchanger.

[0028] The opening of the first temperature control valve is repeatedly adjusted until the temperature measured by the first temperature sensor reaches the set target temperature.

[0029] Furthermore, the second heat transfer loop receives and dissipates the heat transferred from the first heat exchanger, specifically including:

[0030] The second heat transfer medium circulates in the second heat transfer loop, collecting heat from the first heat transfer loop through the first heat exchanger. After absorbing heat and vaporizing on the second side of the first heat exchanger, the second heat transfer medium enters the compressor. The compressor increases the temperature and pressure of the gaseous medium, which then enters the second radiator to dissipate heat and condense. After passing through the second liquid receiver, dryer, and expansion valve in sequence, it cools and depressurizes before returning to the input end of the second side of the first heat exchanger to absorb heat again.

[0031] The advantages of this invention compared to the prior art are:

[0032] (1) The lunar exploration manned spacecraft thermal management system provided by the present invention has a high degree of integration, integrating the single-phase fluid circuit and the heat pump circulation circuit into one, and realizing the heat dissipation requirements of the manned spacecraft during the flight process and after landing on the lunar surface through the switching of working modes.

[0033] (2) The present invention realizes heat dissipation of the limited radiator area under the high temperature environment of the lunar surface through the heat pump circulation loop. Compared with the heat dissipation efficiency of only using the single-phase fluid loop under the high temperature environment of the lunar surface, the heat dissipation efficiency is greatly improved, and the radiator area and weight are reduced.

[0034] (3) The present invention achieves heat dissipation during flight and when the solar altitude angle on the lunar surface is low through a single-phase fluid circuit, thus avoiding the technical difficulties of using a heat pump circulation circuit during space flight. Attached Figure Description

[0035] Figure 1 This is a schematic diagram of the thermal management system of a lunar exploration manned spacecraft according to an embodiment of the present invention. Detailed Implementation

[0036] The invention will now be further described with reference to the accompanying drawings.

[0037] Reference Figure 1As shown, this embodiment provides a thermal management system for a lunar exploration manned spacecraft, including: a first heat transfer loop, a second heat transfer loop, and a bypass of the first heat transfer loop; the first heat transfer loop bypass is equipped with a second self-locking valve 18, and the first heat transfer loop and the second heat transfer loop are coupled through a first heat exchanger 4. The thermal management system has two operating modes: a first heat transfer loop operating mode and a combined operating mode of the first and second heat transfer loops. The operating mode can be switched according to mission requirements and changes in the external thermal environment. During spaceflight and at low solar altitude angles after landing on the lunar surface, the first heat transfer loop operates alone. After landing on the lunar surface, when the solar altitude angle is high, the first and second heat transfer loops operate in combination.

[0038] The first heat transfer circuit is a single-phase fluid circuit, including a first heat transfer circuit pump 1, a first one-way valve 2, a first temperature control valve 3, a first side of a first heat exchanger 4, a first self-locking valve 5, a second heat exchanger 6, a first radiator 7, a second one-way valve 8, a second temperature control valve 9, a second temperature sensor 10, a first temperature sensor 11, a heat collection module, a bulkhead heating pipe 16, and a first liquid reservoir 17. The cold side of the first heat exchanger 4 is defined as the first side of the first heat exchanger 4, and the hot side of the first heat exchanger 4 is defined as the second side of the first heat exchanger 4; heat exchange occurs between the second side of the first heat exchanger 4 and the first side of the first heat exchanger 4 through the heat exchange components of the first heat exchanger 4 itself.

[0039] The output of the first heat transfer circuit pump 1 is connected to the input of the first one-way valve 2. The output of the first one-way valve 2 is connected to the input of the first temperature control valve 3. The first output of the first temperature control valve 3 is connected to the first side input of the first heat exchanger 4. The output of the first side of the first heat exchanger 4 is divided into a first output and a second output via a three-way valve. The first output of the first side of the first heat exchanger 4 is connected to the input of the first self-locking valve 5. The second output of the first side of the first heat exchanger 4 is connected to the input of the second self-locking valve 18. The output of the first self-locking valve 5 is connected to the first side input of the second heat exchanger 6. The first side output of the second heat exchanger 6 is connected to the input of the first radiator 7. The output of the first radiator 7 is connected to the second... The input terminal of the one-way valve 8 is connected, the output terminal of the second one-way valve 8 is connected to the input terminal of the second temperature control valve 9, the first output terminal of the second temperature control valve 9 is connected to the second side input terminal of the second heat exchanger 6, the second side output terminal of the second heat exchanger 6 and the second output terminal of the second temperature control valve 9 are combined and then connected to the input terminal of the second temperature sensor 10, the output terminal of the second self-locking valve 18 is combined with the output terminal of the second temperature sensor 10 and then combined with the second output terminal of the first temperature control valve 3, and then connected to the input terminal of the first temperature sensor 11. The output terminal of the first temperature sensor is connected to the heat collection module. In this embodiment, the heat collection module specifically includes a liquid-cooled spacesuit heat exchanger 12, a spacesuit ventilation heat exchanger 13, an in-cabin air conditioning device 14, and a cold plate 15. After passing through the heat collection module, the input terminal of the cabin wall heating pipe 16 is connected, the output terminal of the cabin wall heating pipe 16 is connected to the input terminal of the first liquid reservoir 17, and the output terminal of the first liquid reservoir 17 is connected to the input terminal of the first heat transfer circuit pump 1.

[0040] Specifically, the input end of the second self-locking valve 18 (i.e. the inlet end of the first heat transfer circuit bypass) is located between the first heat exchanger 4 and the first self-locking valve 5, and the output end of the second self-locking valve 18 (i.e. the outlet end of the first heat transfer circuit bypass) is located between the second temperature sensor 10 and the first temperature sensor 11.

[0041] The first heat transfer loop contains a circulating first heat transfer medium, which can be either ethylene glycol aqueous solution or perfluorotriethylamine, currently used in manned spacecraft. A first heat transfer loop pump 1 provides power for the movement of the first heat transfer medium. A first one-way valve 2 prevents backflow in the first heat transfer loop. A first temperature control valve 3 controls the flow rate into the two output branches by adjusting its opening, thereby achieving the first control point of the loop temperature reaching the set target temperature. Specifically, the first control point of the loop temperature is located at the first temperature sensor 11. After the two output branches of the first temperature control valve 3 converge, the flow rate enters the input terminal of the first temperature sensor 11. Based on the difference between the temperature measured by the first temperature sensor 11 and the set target temperature, the opening of the first temperature control valve 3 is automatically adjusted, thereby regulating the flow distribution between the two output terminals of the first temperature control valve 3 and achieving temperature control.

[0042] The second heat exchanger 6 functions as a regenerator. When the first heat transfer loop operates independently, the heat flows through the first side of the second heat exchanger 6, then through the first radiator 7, and finally through the second temperature control valve 9 into two branches. One branch flows through the second side of the second heat exchanger 6, and the other branch merges with the output of the second side of the second heat exchanger 6 before entering the input of the second temperature sensor 10. The second temperature control valve 9 adjusts its opening to bring the second control point of the loop temperature to the set target temperature. The second control point of the loop temperature is located at the second temperature sensor 10. The opening of the second temperature control valve 9 is adjusted based on the difference between the temperature measured by the second temperature sensor 10 and the set target temperature, thereby adjusting the flow distribution between the two outputs of the first temperature control valve 9 and achieving temperature control. By using a second heat exchanger 6 and a second temperature control valve 9 to control the temperature, the first heat transfer medium can flow through the first radiator 7 under different temperature control targets. Under low external heat flow conditions, the temperature of the first heat transfer medium entering the first radiator 7 can be reduced in advance, and the heat dissipation after entering the first radiator 7 is reduced. The first heat transfer medium is less likely to condense due to low temperature, and the stability of temperature control can be increased.

[0043] The liquid-cooled spacesuit heat exchanger 12 and the spacesuit ventilation heat exchanger 13 provide ventilation and cooling for the spacesuits inside the cabin, and are only used when the astronauts are inside the spacesuits. The cabin air conditioning device 14 is a gas-liquid heat exchanger that transfers heat from the cabin air to the first heat transfer loop to control the cabin air temperature and humidity. The cold plate 15 collects heat from the cabin electronic equipment; multiple cold plates can be installed for electronic equipment requiring heat dissipation. The cabin wall heating pipes 16 provide supplemental heating to the cabin walls in areas with lower temperatures, achieving comprehensive heat utilization. The first liquid reservoir 17 serves to compensate for liquid loss and stabilize the loop pressure.

[0044] The second heat transfer circuit is a heat pump cycle circuit, including the second side of the first heat exchanger 4, compressor 19, second radiator 20, second liquid receiver 21, dryer 22, and expansion valve 23. The hot side of the second heat exchanger 6 is defined as the first side of the second heat exchanger 6, and the cold side of the second heat exchanger 6 is defined as the second side of the second heat exchanger 6.

[0045] The second output terminal of the first heat exchanger 4 is connected to the input terminal of the compressor 19. The output terminal of the compressor 19 is connected to the input terminal of the second radiator 20. The output terminal of the second radiator 20 is connected to the input terminal of the second liquid receiver 21. The output terminal of the second liquid receiver 21 is connected to the input terminal of the dryer 22. The output terminal of the dryer 22 is connected to the input terminal of the expansion valve 23. The output terminal of the expansion valve 23 is connected to the second input terminal of the first heat exchanger 4. A second heat transfer medium is provided in the second heat transfer circuit.

[0046] The second heat transfer medium can be selected from commonly used working media such as R134a in vapor compression heat pump systems. The second heat transfer medium circulates in the second heat transfer loop, collecting heat from the first heat transfer loop through the first heat exchanger 4. After absorbing heat and vaporizing on the second side of the first heat exchanger 4, the second heat transfer medium enters the compressor 19. The compressor 19 increases the temperature and pressure of the gaseous working medium, and it enters the second radiator 20 to dissipate heat and condense. Then, it passes through the second liquid receiver 21, dryer 22, and expansion valve 23 in sequence, and after cooling and depressurizing, it returns to the input end of the second side of the first heat exchanger 4 to absorb heat again.

[0047] The thermal management system of this invention also includes a heat pipe 24. The first radiator 7 and the second radiator 20 are thermally coupled through the heat pipe 24, enabling full utilization of both radiators for external heat dissipation in both operating modes. Specifically: in the independent operating mode of the first heat transfer circuit, when the first heat transfer medium passes through the first radiator 7, it can simultaneously utilize the second radiator 20 for heat dissipation due to the thermal coupling effect of the heat pipe 24; in the combined operating mode of the first and second heat transfer circuits, when the second heat transfer medium passes through the second radiator 20, it can simultaneously utilize the first radiator 7 for heat dissipation due to the thermal coupling effect of the heat pipe 24. In both operating modes, the heat dissipation area of ​​a single radiator is increased, accelerating external heat dissipation.

[0048] The first heat exchanger 4 performs heat exchange in the combined operation mode of the first and second heat transfer loops. The working medium flowing on the first side of the first heat exchanger 4 is the first heat transfer medium, and the working medium flowing on the second side is the second heat transfer medium. The heat absorbed by the first heat transfer loop is transferred to the second heat transfer loop through the heat transfer components (such as metal heat-conducting plates) in the first heat exchanger 4. In the mode of operation of the first heat transfer loop alone, only the first heat transfer medium flows on the first side of the first heat exchanger 4, and the first heat exchanger 4 does not perform heat exchange.

[0049] In summary, based on the thermal management system of the present invention, the control method for the independent operating mode of the first heat transfer loop includes the following process:

[0050] The second self-locking valve 18 is closed and the first self-locking valve 5 is opened. The heat absorbed by the heat collection module is transferred to the first heat transfer circuit through the first heat transfer medium. The first temperature control valve 3 distributes the flow into the first side of the first heat exchanger 4 at the initial opening. At this time, the first heat exchanger 4 does not perform heat exchange.

[0051] The first heat transfer medium flows through the first radiator 7 to dissipate heat to the outside. The second temperature control valve 9 automatically adjusts its opening based on the difference between the temperature measured by the second temperature sensor 10 and the set target temperature, thereby adjusting the flow distribution between the first output end and the second output end of the first temperature control valve 9. The first heat transfer medium at the first output end and the second output end of the first temperature control valve 9 merges and flows into the second temperature sensor 10.

[0052] After the first heat transfer medium flowing out of the second temperature sensor 10 and the first heat transfer medium flowing out of the second output end of the first temperature control valve 3 merge, they enter the first temperature sensor 11. The first temperature control valve 3 automatically adjusts its opening according to the difference between the temperature measured by the first temperature sensor 11 and the set target temperature, thereby adjusting the flow rate into the first side of the first heat exchanger 4.

[0053] Repeatedly adjust the opening of the second temperature control valve 9 and the first temperature control valve 3 until the temperatures measured by the second temperature sensor 10 and the first temperature sensor 11 both reach the set target temperature.

[0054] Based on the thermal management system of the present invention, the control method for the combined operation mode of the first heat transfer loop and the second heat transfer loop includes the following process:

[0055] The second self-locking valve 18 is opened and the first self-locking valve 5 is closed. The heat absorbed by the heat collection module is transferred to the first heat transfer circuit through the first heat transfer medium. The first temperature control valve 3 distributes the flow into the first heat exchanger 4 at the initial opening. In the current working mode, the branch where the second heat exchanger 6, the first radiator 7, the second one-way valve 8, the second temperature control valve 9, and the second temperature sensor 10 are located is not working. The heat of the first heat transfer circuit is transferred to the second heat transfer circuit through the first heat exchanger 4.

[0056] The temperature of the first heat transfer medium drops after heat exchange through the first heat exchanger 4. The second heat transfer circuit receives the heat transferred by the first heat exchanger 4 and dissipates it. The first heat transfer medium flows out of the first side output end of the first heat exchanger 4 and flows into the bypass where the second self-locking valve 18 is located.

[0057] The first heat transfer medium flowing out of the second self-locking valve 18 and the first heat transfer medium flowing out of the second output end of the first temperature control valve 3 merge and enter the first temperature sensor 11. The first temperature control valve 3 automatically adjusts its opening according to the difference between the temperature measured by the first temperature sensor 11 and the set target temperature, thereby adjusting the flow rate into the first heat exchanger 4.

[0058] By repeatedly adjusting the opening of the first temperature control valve 3, the temperature measured by the first temperature sensor 11 reaches the set target temperature.

[0059] The thermal management system of the present invention operates only in the first heat transfer loop when the spacecraft is in orbit or in a low solar altitude angle environment after lunar landing (in this embodiment, a solar altitude angle of less than 30° is considered a low solar altitude angle). Through the feedback control of the first temperature control valve 3 + the first temperature sensor 11 and the feedback control of the second temperature control valve 9 + the second temperature sensor 10, the goal of temperature closed-loop control and heat dissipation of cabin equipment and personnel can be achieved.

[0060] When the spacecraft is in a high solar altitude angle environment after landing on the moon (in this embodiment, a solar altitude angle higher than 30° is taken as a high solar altitude angle), the first heat transfer loop and the second heat transfer loop work together. The first heat transfer loop realizes closed-loop temperature control and heat collection and transmission of equipment and personnel in the cabin through feedback control of the first temperature control valve 3 and the first temperature sensor 11. Heat exchange between the two heat transfer loops is realized through the first heat exchanger 4, and heat dissipation is realized through the second heat transfer loop.

[0061] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A thermal management system for a lunar exploration manned spacecraft, characterized in that, include: First heat transfer circuit, second heat transfer circuit, first heat transfer circuit bypass; The first heat transfer circuit bypass is equipped with a second self-locking valve (18). The first heat transfer circuit includes a heat collection module and is a single-phase fluid circuit. The first heat transfer circuit contains a circulating first heat transfer medium. After the heat collection module absorbs heat, it is transferred to the first heat transfer circuit through the first heat transfer medium for heat dissipation. The first heat transfer medium after heat dissipation flows back into the heat collection module to continue circulating. When temperature control is performed, the flow distribution of the first heat transfer medium in the first heat transfer circuit is adjusted according to the set target temperature, so that the temperature control point of the first heat transfer circuit reaches the set target temperature. The second heat transfer loop is coupled to the first heat transfer loop and forms a heat pump circulation loop. The second heat transfer loop contains a circulating second heat transfer medium. When the second heat transfer loop is working, the heat absorbed by the first heat transfer medium is discharged into the second heat transfer loop at the coupling point to achieve cooling. After the first heat transfer medium is cooled, it flows through the bypass of the first heat transfer loop into the heat collection module and continues to circulate. The second heat transfer loop is used to dissipate the heat transferred by the first heat transfer medium. The second self-locking valve (18) is used to switch the working mode of the thermal management system. When the second self-locking valve (18) is closed, the thermal management system is in the working mode of the first heat transfer circuit alone; when the second self-locking valve (18) is open, the thermal management system is in the working mode of the first heat transfer circuit and the second heat transfer circuit together. The second heat transfer circuit includes the second side of the first heat exchanger (4), the compressor (19), the second radiator (20), the second liquid receiver (21), the dryer (22), and the expansion valve (23). The second side output end of the first heat exchanger (4) is connected to the input end of the compressor (19), the output end of the compressor (19) is connected to the input end of the second radiator (20), the output end of the second radiator (20) is connected to the input end of the second liquid receiver (21), the output end of the second liquid receiver (21) is connected to the input end of the dryer (22), the output end of the dryer (22) is connected to the input end of the expansion valve (23), and the output end of the expansion valve (23) is connected to the second side input end of the first heat exchanger (4). Among them, the second side of the first heat exchanger (4) is the hot side, and heat exchange is achieved between the first heat exchanger (4) and the first side of the first heat exchanger (4) through the heat exchange components of the first heat exchanger (4) itself; The second heat transfer loop is coupled to the first heat transfer loop through the first heat exchanger (4); The second heat transfer medium is R134a.

2. The thermal management system for a lunar exploration manned spacecraft according to claim 1, characterized in that, The first heat transfer circuit also includes a first heat transfer circuit pump (1), a first check valve (2), a first temperature control valve (3), a first heat exchanger (4) first side, a first self-locking valve (5), a second heat exchanger (6), a first radiator (7), a second check valve (8), a second temperature control valve (9), a second temperature sensor (10), a first temperature sensor (11), a bulkhead heating pipe (16), and a first liquid reservoir (17). The output end of the first heat transfer circuit pump (1) is connected to the input end of the first one-way valve (2). The output end of the first one-way valve (2) is connected to the input end of the first temperature control valve (3). The first output end of the first temperature control valve (3) is connected to the first side input end of the first heat exchanger (4). The output end of the first side of the first heat exchanger (4) is divided into the first output end and the second output end of the first side of the first heat exchanger (4) through a three-way valve. The first output end of the first side of the first heat exchanger (4) is connected to the input end of the first self-locking valve (5). The second output end of the first side of the first heat exchanger (4) is connected to the input end of the second self-locking valve (18). The output end of the first self-locking valve (5) is connected to the first side input end of the second heat exchanger (6). The first side output end of the second heat exchanger (6) is connected to the input end of the first radiator (7). The output end of the first radiator (7) is connected to the input end of the second one-way valve (8). Then, the output end of the second one-way valve (8) is connected to the input end of the second temperature control valve (9), the first output end of the second temperature control valve (9) is connected to the second side input end of the second heat exchanger (6), the second side output end of the second heat exchanger (6) and the second output end of the second temperature control valve (9) are connected to the input end of the second temperature sensor (10), the output end of the second self-locking valve (18) and the output end of the second temperature sensor (10) are connected to the second output end of the first temperature control valve (3) respectively, and then connected to the input end of the first temperature sensor (11), the output end of the first temperature sensor is connected to the heat collection module, and then connected to the input end of the bulkhead heating pipe (16) through the heat collection module, the output end of the bulkhead heating pipe (16) is connected to the input end of the first liquid reservoir (17), and the output end of the first liquid reservoir (17) is connected to the input end of the first heat transfer circuit pump (1); The first heat exchanger (4) has a cold side on the first side, the second heat exchanger (6) has a hot side on the first side, and the second heat exchanger (6) has a cold side on the second side.

3. The thermal management system for a lunar exploration manned spacecraft according to claim 2, characterized in that, It also includes a heat pipe (24), through which the first radiator (7) and the second radiator (20) are thermally coupled.

4. The thermal management system for a lunar exploration manned spacecraft according to claim 1, characterized in that, The first heat transfer medium is an aqueous solution of ethylene glycol or perfluorotriethylamine used in manned spacecraft.

5. A control method for the thermal management system of a lunar exploration manned spacecraft based on the system described in claim 3, characterized in that, This includes a control method for a standalone operating mode of the first heat transfer loop, used in on-orbit flight or under low solar altitude angle conditions after lunar landing, including: The second self-locking valve (18) is closed, and the first self-locking valve (5) is opened. The heat absorbed by the heat collection module is transferred to the first heat transfer circuit through the first heat transfer medium. The first temperature control valve (3) distributes the flow into the first side of the first heat exchanger (4) at the initial opening. At this time, the first heat exchanger (4) does not perform heat exchange. The first heat transfer medium flows through the first radiator (7) to dissipate heat to the outside. The second temperature control valve (9) automatically adjusts its opening according to the difference between the temperature measured by the second temperature sensor (10) and the set target temperature, thereby adjusting the flow distribution of the first output end and the second output end of the first temperature control valve (3). The first heat transfer medium at the first output end and the second output end of the first temperature control valve (3) merges and flows into the second temperature sensor (10). The first heat transfer medium flowing out of the second temperature sensor (10) and the first heat transfer medium flowing out of the second output end of the first temperature control valve (3) merge and enter the first temperature sensor (11). The first temperature control valve (3) automatically adjusts its opening according to the difference between the temperature measured by the first temperature sensor (11) and the set target temperature, thereby adjusting the flow rate into the first side of the first heat exchanger (4). Repeatedly adjust the opening of the second temperature control valve (9) and the first temperature control valve (3) until the temperatures measured by the second temperature sensor (10) and the first temperature sensor (11) both reach the set target temperature.

6. A control method for the thermal management system of a lunar exploration manned spacecraft based on the system described in claim 3, characterized in that, This includes a control method for a combined operation mode of the first and second heat transfer loops, used in environments with high solar altitude angles after lunar landing, and comprising: Open the second self-locking valve (18) and close the first self-locking valve (5). The heat absorbed by the heat collection module is transferred to the first heat transfer circuit through the first heat transfer medium. The first temperature control valve (3) distributes the flow into the first heat exchanger (4) at the initial opening. The temperature of the first heat transfer medium drops after heat exchange through the first heat exchanger (4). The second heat transfer circuit receives the heat transferred by the first heat exchanger (4) and dissipates it. The first heat transfer medium flows out of the first side output end of the first heat exchanger (4) and flows into the bypass where the second self-locking valve (18) is located. The first heat transfer medium flowing out of the second self-locking valve (18) and the first heat transfer medium flowing out of the second output end of the first temperature control valve (3) merge and enter the first temperature sensor (11). The first temperature control valve (3) automatically adjusts its opening according to the difference between the temperature measured by the first temperature sensor (11) and the set target temperature, thereby adjusting the flow rate into the first heat exchanger (4). The opening degree of the first temperature control valve (3) is repeatedly adjusted until the temperature measured by the first temperature sensor (11) reaches the set target temperature.

7. The control method for the thermal management system of a lunar exploration manned spacecraft according to claim 6, characterized in that, The second heat transfer loop receives and dissipates the heat transferred by the first heat exchanger (4), specifically including: The second heat transfer medium circulates in the second heat transfer loop and collects heat from the first heat transfer loop through the first heat exchanger (4). After absorbing heat and vaporizing on the second side of the first heat exchanger (4), the second heat transfer medium enters the compressor (19). The compressor (19) increases the temperature and pressure of the gaseous medium and enters the second radiator (20) to dissipate heat and condense. Then, it passes through the second liquid storage tank (21), dryer (22), and expansion valve (23) in sequence. After cooling and depressurizing, it returns to the input end of the second side of the first heat exchanger (4) to absorb heat again.

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