A comprehensive thermal management system and method based on deeply supercooled cryogenic propellant

Abstract

The present invention discloses a comprehensive thermal management system based on deeply supercooled cryogenic propellant. The inner cooling circuit subsystem includes a heat insulation mechanism, a circulation pump and a tubular heat exchanger which are connected in a circular manner through an inner cooling pipeline. The heat insulation mechanism is arranged on the outer surface of the liquid hydrogen tank, and the tubular heat exchanger is arranged on the outer surface of the supercooled liquid oxygen tank. The circulation pump drives the working medium to circulate in the inner cooling pipeline to realize the cooling of the outer surface of the liquid hydrogen tank. The outer cooling circuit subsystem includes an outer cooling pipeline passing through the instrument and equipment. After the working medium flows out of the heat insulation mechanism, it enters the outer cooling pipeline to cool the instrument and equipment, and then flows out of the outer cooling pipeline to enter the circulation pump. The exhaust gas recycling loop includes an exhaust gas pipeline passing through the instrument and equipment. After the liquid hydrogen enters the exhaust gas pipeline to cool the instrument and equipment, it is discharged into the external space. The present invention can provide a heat dissipation path for the instrument and equipment, thereby reducing the thermal management cost of the aircraft.

Description

Technical Field

[0001] The present invention relates to a comprehensive thermal management system and method based on deeply supercooled cryogenic propellant, belonging to the technical field of aerospace cryogenic carriers. Background Art

[0002] Cryogenic propellants are often difficult to store due to their low boiling points, which limits the long-term use of high-energy cryogenic propellants in orbit. In order to solve the problem of long-term in-orbit operation of cryogenic propellants in the complex thermal environment of space, and to enhance the performance and carrying capacity of space transportation systems in the fields of manned lunar landing, Mars exploration and interstellar exploration, two tank cooling schemes have been proposed in the prior art. One is the vapor cooling screen technology, which refers to the propellant vapor discharged from the cryogenic tank flowing through the heat exchanger surrounding the tank to reduce the surface temperature of the tank, thereby reducing the heat leakage rate of the tank. The discharged propellant vapor is heated in the cooling screen, and the heat is transferred out of the system with the gas discharge. This method uses the exhaust waste cooling to reduce the heat entering the tank, but the available cooling capacity is limited and it is difficult to meet the long-term in-orbit requirements. The other is to use a space cryogenic refrigerator to cool the cold screen to reduce the heat leakage of the tank, but the weight and power cost of the refrigerator far exceeds the passive insulation measures. Summary of the invention

[0003] The purpose of the present invention is to overcome the above-mentioned defects and provide a comprehensive thermal management system and method based on deeply supercooled cryogenic propellant, which solves the technical problems of limited available cooling capacity in existing propellant management and high weight and power cost of refrigerators. The present invention can provide a heat dissipation path for instruments and equipment, thereby reducing the thermal management cost of aircraft.

[0004] In order to achieve the above-mentioned object of the invention, the present invention provides the following technical solutions:

[0005] An integrated thermal management system based on deeply supercooled cryogenic propellant, comprising an inner cooling circuit system, an outer cooling circuit system and an exhaust gas recycling circuit system;

[0006] The inner cooling circuit subsystem includes a heat insulation mechanism, a circulation pump and a tubular heat exchanger which are connected in a circular manner through the inner cooling pipeline. The heat insulation mechanism is arranged on the outer surface of the liquid hydrogen storage tank, and the tubular heat exchanger is arranged on the outer surface of the supercooled liquid oxygen storage tank and welded into an integrated structure. The circulation pump drives the working fluid to circulate in the inner cooling pipeline to realize the cooling of the outer surface of the liquid hydrogen storage tank.

[0007] The external cooling circuit subsystem includes an external cooling pipeline passing through the instrument and equipment, the first end of the external cooling pipeline is connected to the heat insulation mechanism, and the second end is connected to the circulation pump. After the working fluid flows out of the heat insulation mechanism, it enters the external cooling pipeline to cool the instrument and equipment, and then flows out of the external cooling pipeline to enter the circulation pump;

[0008] The exhaust gas recycling loop comprises an exhaust pipeline passing through the instrument and equipment, wherein the first end of the exhaust pipeline is connected to the inside of the liquid hydrogen storage tank, and the second end is connected to the external space. After the liquid hydrogen enters the exhaust pipeline to cool the instrument and equipment (7), it is discharged into the external space.

[0009] Further, the first end and the second end of the external cooling pipeline are both connected to the portion of the internal cooling pipeline disposed between the heat insulation mechanism and the circulating pump, and the connection points of the first end and the second end of the external cooling pipeline and the internal cooling pipeline are respectively recorded as the first connection point and the second connection point;

[0010] The portion of the inner cooling pipeline between the heat insulation mechanism and the first connection point is recorded as the first pipeline, the portion between the first connection point and the second connection point is recorded as the second pipeline, and the portion between the second connection point and the circulating pump is recorded as the third pipeline;

[0011] The exhaust gas recycling loop also includes a shell-and-tube heat exchanger, through which the liquid hydrogen in the exhaust pipeline exchanges heat with the first pipeline, and the liquid hydrogen in the exhaust pipeline provides cooling capacity for the working fluid flowing out of the thermal insulation mechanism.

[0012] Furthermore, a second temperature control valve is provided on the second pipeline of the inner cooling pipeline, and a first temperature control valve and a first temperature sensor are provided on the outer cooling pipeline;

[0013] The intelligent temperature controller is used to collect temperature information of the first temperature sensor, and to control the opening of the first temperature control valve and the second temperature control valve in real time according to the difference between the temperature information and the expected temperature.

[0014] Further, the sum of the openings of the first temperature control valve and the second temperature control valve is 100%;

[0015] A compensator for supplementing working fluid is also provided on the second pipeline of the inner cooling pipeline.

[0016] Furthermore, the working fluid is helium at 2MPa to 5MPa;

[0017] The filling temperature of the subcooled liquid oxygen in the subcooled liquid oxygen storage tank is below 65K.

[0018] Further, the thermal insulation mechanism includes a first composite foam thermal insulation material, a composite multi-layer thermal insulation assembly and a cooling screen;

[0019] The first composite foam insulation material is sprayed on the outer surface of the liquid hydrogen tank;

[0020] The composite multi-layer heat insulation component is coated on the outer surface of the first composite foam heat insulation material, the composite multi-layer heat insulation component includes 30 units to 80 units, each unit is composed of a reflection screen layer and a spacer layer, and the cooling screen is arranged inside the composite multi-layer heat insulation component and is located in the middle of the 30 units to 80 units;

[0021] The cooling screen includes multiple parallel aluminum alloy pipes and aluminum foil for conducting heat between the aluminum alloy pipes. The cooling screen completely wraps the outer surface of the liquid hydrogen tank, and the working fluid flows into the aluminum alloy pipes from the tubular heat exchanger.

[0022] Furthermore, a splitter is provided at the inlet of the aluminum alloy pipeline, and one path of working fluid flowing out of the tubular heat exchanger is evenly divided into multiple paths of working fluid by the splitter. The multiple paths of working fluid enter the multiple paths of alloy pipelines, flow through the outer surface of the liquid hydrogen storage tank, and converge into one path of working fluid at the outlet of the aluminum alloy pipeline.

[0023] Furthermore, the outer surface of the subcooled liquid oxygen tank is sprayed with a second composite foam insulation material;

[0024] The preparation method of the first composite foam thermal insulation material is:

[0025] First, a first layer of composite foam is sprayed on the outer surface of the liquid hydrogen tank to allow the first layer of composite foam to foam, and then a second layer of composite foam is sprayed on the surface of the first layer of composite foam to allow the second layer of composite foam to foam;

[0026] The preparation method of the second composite foam thermal insulation material is:

[0027] First, a first layer of composite foam is sprayed on the outer surface of the integrated structure formed by welding the tubular heat exchanger and the subcooled liquid oxygen tank, and the first layer of composite foam is foamed and solidified, and then a second layer of composite foam is sprayed on the surface of the first layer of composite foam to foam the second layer of composite foam;

[0028] The first layer of composite foam is polyurethane foam doped with glass beads, and the second layer of foam is polyurethane foam doped with fragmented heat reflective film.

[0029] Furthermore, the fragmented heat reflective film is a fragmented double-sided aluminum-plated polyimide film with an equivalent diameter of 1 to 5 mm, and the glass balls are carbon dioxide glass balls.

[0030] A comprehensive thermal management method based on deeply supercooled cryogenic propellant is implemented by using the above-mentioned comprehensive thermal management system, comprising:

[0031] The circulating pump drives the working fluid to circulate in the internal cooling pipeline to achieve cooling of the outer surface of the liquid hydrogen tank;

[0032] The working fluid flows out of the heat insulation mechanism and enters the external cooling pipeline to cool the instrument and equipment, and then flows out of the external cooling pipeline and enters the circulation pump;

[0033] The liquid hydrogen in the liquid hydrogen storage tank enters the exhaust pipeline to cool the instruments and equipment, and then is discharged into the external space.

[0034] The present invention provides a comprehensive thermal management system and method based on deeply supercooled cryogenic propellants, and mainly proposes a solution for the long-term on-orbit propellant evaporation control and aircraft thermal management of my country's future liquid hydrogen and liquid oxygen space transportation system. The method mainly utilizes the rich cold source of deeply supercooled liquid oxygen (<65K) to provide cooling for the liquid hydrogen insulation layer, connecting support structure, instruments and equipment, structural components, etc., reduce liquid hydrogen evaporation, and provide heat dissipation pathways for instruments and equipment, thereby reducing the cost of aircraft thermal management, and providing a minimum cost control strategy for a liquid hydrogen and liquid oxygen space transportation system to be on-orbit for a long time within 30 days.

[0035] Compared with the prior art, the present invention has the following beneficial effects:

[0036] (1) The present invention creatively provides an integrated thermal management system based on deeply supercooled cryogenic propellants, which utilizes the abundant cooling resources of deeply supercooled liquid oxygen. Since large-scale deeply supercooled liquid oxygen is prepared on the ground and then added to the aircraft, the weight and energy cost of the aircraft are greatly reduced;

[0037] (2) The present invention uses high-pressure helium as a cooling medium to drive the working fluid through a deep subcooled liquid oxygen tank through a circulating pump, and recirculates to cool the insulation layer of the liquid hydrogen tank, thereby greatly reducing the heat leakage of the liquid hydrogen tank, and providing a heat sink for the instruments on the carrier through a bypass, thereby reducing the cost of thermal management and optimizing the system design. The present invention can achieve the minimum cost control of the liquid hydrogen and liquid oxygen space transportation system for long-term on-orbit within 30 days;

[0038] (3) The thermal insulation layer of the hydrogen tank of the present invention adopts capsules or microspheres doped with CO2 atmosphere, multifunctional composite foam composed of heat reflective materials, and multi-layer insulation components, which significantly improves the thermal insulation capacity of the tank and helps to reduce the evaporation of low-temperature propellant. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 It is a schematic diagram of the comprehensive thermal management system based on deeply supercooled cryogenic propellant of the present invention;

[0040] In the figure, 1-liquid hydrogen tank, 2-first composite foam insulation material, 3-composite multi-layer insulation assembly, 4-cooling screen, 5-first temperature control valve, 6-second temperature control valve, 7-instrument, 8-first solenoid valve, 9-compensator, 10-circulating pump, 11-wound tube heat exchanger, 12-subcooled liquid oxygen tank, 13-second composite foam insulation material, 14-diverter, 15-liquid collector, 16-intelligent temperature controller, 17-first temperature sensor, 18-first flow meter, 19-second temperature sensor, 20-second flow meter, 21-first pressure sensor, 22-second pressure sensor, 23-third temperature sensor, 24-fourth temperature sensor, 25-exhaust pipeline, 26-tube heat exchanger, 27-second solenoid valve. DETAILED DESCRIPTION

[0041] The following detailed description of the present invention will make the features and advantages of the present invention more clear and explicit.

[0042] The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Although various aspects of the embodiments are shown in the drawings, the drawings are not necessarily drawn to scale unless otherwise noted.

[0043] The present invention provides a comprehensive thermal management system and method based on deep supercooled cryogenic propellant, which can simultaneously achieve low evaporation of cryogenic propellant and heat dissipation of instruments and equipment. The advantage of the present invention is that it utilizes the abundant cold resources of deep supercooled liquid oxygen. Since the preparation of large-scale deep supercooled liquid oxygen (supercooled liquid oxygen that reduces 90K saturated liquid oxygen to below 65K) is completed on the ground and then filled into the aircraft, the weight and energy cost of the aircraft are greatly reduced. The present invention uses high-pressure helium as a cooling medium to drive the working fluid to flow through the deep supercooled liquid oxygen tank through a circulating pump, and recirculates the cooling liquid hydrogen tank insulation layer, thereby greatly reducing the heat leakage of the liquid hydrogen tank, and provides a heat sink for the instrument on the carrier through a bypass, realizing the reduction of thermal management cost and system optimization design. The present invention can realize the minimum cost control of the liquid hydrogen and liquid oxygen space transportation system for long-term on-orbit within 30 days. The hydrogen tank insulation layer adopts capsules or microspheres doped with CO2 atmosphere, multifunctional composite foam composed of heat reflective materials, and multi-layer insulation components, which significantly improves the insulation capacity of the tank and is conducive to reducing the evaporation of cryogenic propellant.

[0044] like Figure 1 As shown, in a preferred embodiment, an integrated thermal management system based on deeply supercooled cryogenic propellant of the present invention comprises: a liquid hydrogen tank 1, a first composite foam insulation material 2, a composite multilayer insulation component 3, a cooling screen 4, a first temperature control valve 5, a second temperature control valve 6, an instrument 7, a first solenoid valve 8, a compensator 9, a circulating pump 10, a coil-wound heat exchanger 11, a supercooled liquid oxygen tank 12, a second composite foam insulation material 13, a diverter 14, a liquid collector 15, an intelligent temperature controller 16, a first temperature sensor 17, a first flow meter 18, a second temperature sensor 19, a second flow meter 20, a first pressure sensor 21, a second pressure sensor 22, a third temperature sensor 23, a fourth temperature sensor 24, an exhaust pipeline 25, a shell-and-tube heat exchanger 26, and a second solenoid valve 27. Composite foam insulation materials and composite multi-layer insulation components are used to solve the insulation problems of low-temperature tanks before launch and after entering orbit, respectively. In order to further reduce the evaporation of liquid hydrogen, a pump-driven high-pressure helium working fluid is used to circulate the supercooled oxygen-rich cold resources into the composite multi-layer insulation components of the liquid hydrogen tank, thereby reducing heat leakage of the liquid hydrogen tank and extending the on-orbit life of liquid hydrogen.

[0045] The present invention is based on a comprehensive thermal management system for deeply supercooled cryogenic propellants, comprising three parts: an inner cooling circuit subsystem, an outer cooling circuit subsystem, and an exhaust gas recycling circuit subsystem.

[0046] The internal cooling circuit subsystem is a closed-loop cooling circuit consisting of a subcooled liquid oxygen tank 12, a coil-wound heat exchanger 11, a liquid hydrogen tank 1, a cooling screen 4, a second temperature control valve 6, a compensator 9, a first solenoid valve 8, a circulating pump 10 and connecting pipes, which is used to circulate the surplus cold resources of the subcooled liquid oxygen tank 12 to the cooling screen 4 to reduce heat leakage and liquid hydrogen evaporation. The cooling screen 4 is located in the middle of the composite multilayer insulation component 3, which is about 30 units to 80 units. Taking a 60-unit composite multilayer insulation component as an example, the most efficient position of the cooling screen 4 is located at the 30th unit from the inside to the outside, and the temperature of the cooling screen 4 is about 90K to 100K. Compared with the liquid hydrogen tank without a cooling screen, it can reduce heat leakage by more than 70% in the on-orbit state. The compensator 9 is filled with high-pressure helium, and the helium pressure in the circuit is about 2MPa to 5MPa. The higher helium pressure can increase the working fluid density and cooling capacity, thereby improving the efficiency of the integrated thermal management system.

[0047] The external cooling circuit subsystem is a bypass consisting of a first temperature control valve 5, instruments and equipment 7 and a heat exchange pipeline added to the internal cooling circuit subsystem, and is used for cooling instruments and equipment and temperature control.

[0048] The exhaust gas recycling circuit subsystem is an open cooling circuit consisting of an exhaust pipeline 25, a shell-and-tube heat exchanger 26, instruments and equipment 7, and a second solenoid valve 27, and is used to recycle the exhaust gas waste cooling of the liquid hydrogen storage tank 1 to cool the working fluid and instruments and equipment in the inner circuit subsystem, thereby realizing the recycling of the exhaust gas waste cooling of the liquid hydrogen storage tank.

[0049] A first composite foam insulation material 2 is sprayed on the outer wall of the liquid hydrogen storage tank 1, a composite multilayer insulation component 3 is coated on the outer surface of the first composite foam insulation material 2, and a cooling screen 4 formed by multiple pipelines in parallel is embedded in the middle layer of the composite multilayer insulation component 3. The cooling screen is composed of an aluminum alloy pipeline and an aluminum foil with a thickness of 0.15 mm to 0.25 mm. Each pipeline has two fins. The aluminum foil is adhered to the pipeline and its fins by a high thermal conductivity and low temperature adhesive. The cooling screen 4 composed of the pipeline and the aluminum foil completely wraps the liquid hydrogen storage tank 1, thereby diffusing the cold in the pipeline to the entire surface of the aluminum foil, thereby achieving efficient cold preservation of the liquid hydrogen storage tank 1.

[0050] A coiled heat exchanger 11 is installed on the outer wall of the liquid oxygen tank 12, and the two are welded into an integrated structure, and a second composite foam insulation material 13 is sprayed on the outer wall of the liquid oxygen tank 12. The liquid oxygen tank 12 contains deeply subcooled liquid oxygen, and the filling temperature is less than 65K (the saturation temperature is about 90K under normal pressure).

[0051] The first composite foam insulation material 2 and the second composite foam insulation material 13 are doped with heat reflective materials and carbon dioxide glass beads in traditional polyurethane foam. The heat reflective material is a fragmented double-sided aluminum-plated polyimide film, which is located on the hot side of the multifunctional composite foam insulation material, wherein the hot side area accounts for 50% to 70% of the thickness of the multifunctional composite foam insulation material, and the equivalent diameter of a single fragmented double-sided aluminum-plated polyimide film is about 1 to 5 mm, and then uniformly doped into the polyurethane foam raw material. The carbon dioxide glass beads are located on the cold side of the multifunctional composite foam insulation material, and the composite foam is a homogeneous mixture formed by using the hollow glass microspheres of the traditional polyurethane foam raw material and the carbon dioxide atmosphere by the raw material doping method. During the spraying process, a layer of composite foam doped with carbon dioxide glass beads is first sprayed on the surface of the tank and foamed, and then a layer of composite foam doped with heat reflective material is sprayed and foamed after curing and shaping. Among them, the emissivity of the fragmented double-sided aluminum-plated polyimide film is not more than 0.06, which can effectively weaken radiation heat transfer. The freezing point of carbon dioxide is significantly higher than the temperature of liquid hydrogen and liquid oxygen. Carbon dioxide glass beads can form an insulation layer close to vacuum at low temperatures, which is used for low-temperature storage tank insulation. The preparation method of carbon dioxide glass beads is based on the traditional glass powder method, which replaces the flame with a temperature of 1100℃ to 1500℃ with high-temperature carbon dioxide gas at 1100℃ to 1500℃, thereby forming hollow glass beads in a carbon dioxide atmosphere.

[0052] The present invention is a comprehensive thermal management method based on deep supercooled cryogenic propellant. The temperature of the first temperature sensor 17 is collected by the intelligent temperature controller 16, so that the error between the temperature sensor 17 and the Tc temperature control point is less than a preset threshold value. Tc is generally 0°C to 20°C. The intelligent temperature controller 16 adjusts the opening K1 of the first temperature control valve 5 and the opening K2 of the second temperature control valve 6 through PID algorithm feedback to achieve temperature control of the instrument 7. Among them, K1+K2=100%.

[0053] The high-pressure helium is driven by the circulation pump 10 to circulate in the inner cooling loop subsystem and the outer cooling loop subsystem respectively, and the cold energy of the supercooled liquid oxygen tank 12 is transported to the insulation layer of the liquid hydrogen tank 1 and the instrument 7 respectively. The heated helium returns to the coiled heat exchanger 11 to exchange heat with the liquid oxygen tank 12. In this cycle, the reduction of liquid hydrogen evaporation and the joint control of the temperature of the instrument and equipment are achieved, so as to realize the long-term and efficient operation of the cryogenic carrier in orbit.

[0054] Example:

[0055] like Figure 1As shown, an integrated thermal management system based on deeply supercooled cryogenic propellant includes: a liquid hydrogen tank 1, a first composite foam insulation material 2, a composite multilayer insulation component 3, a cooling screen 4, a first temperature control valve 5, a second temperature control valve 6, an instrument 7, a first solenoid valve 8, a compensator 9, a circulating pump 10, a coil-wound heat exchanger 11, a supercooled liquid oxygen tank 12, a second composite foam insulation material 13, a diverter 14, a liquid collector 15, an intelligent temperature controller 16, a first temperature sensor 17, a first flow meter 18, a second temperature sensor 19, a second flow meter 20, a first pressure sensor 21, a second pressure sensor 22, a third temperature sensor 23, a fourth temperature sensor 24, a liquid hydrogen exhaust pipeline 25, a shell-and-tube heat exchanger 26, and a second solenoid valve 27.

[0056] The above-mentioned integrated thermal management system includes an internal cooling circuit subsystem, an external cooling circuit subsystem, and an exhaust gas recycling circuit subsystem.

[0057] The internal cooling circuit subsystem is a closed-loop cooling circuit consisting of a subcooled liquid oxygen tank 12, a coiled heat exchanger 11, a liquid hydrogen tank 1, a cooling screen 4, a second temperature control valve 6, a compensator 9, a first solenoid valve 8, a circulating pump 10 and connecting pipes, which is used to circulate the surplus cold resources of the subcooled liquid oxygen tank 12 to the insulation layer of the liquid hydrogen tank 1 to reduce heat leakage and liquid hydrogen evaporation. The compensator 9 is filled with high-pressure helium.

[0058] The external cooling circuit subsystem is a bypass consisting of a first temperature control valve 5, an instrument and equipment (7) and a heat exchange pipeline added to the internal cooling circuit subsystem, and is used for cooling the instrument and equipment and temperature control.

[0059] The exhaust gas recycling circuit subsystem is an open cooling circuit consisting of an exhaust pipe 25, a shell-and-tube heat exchanger 26, an instrument 7, and a second solenoid valve 27, and is used to recycle the exhaust gas surplus cooling of the liquid hydrogen tank 1 to cool the working fluid and the instrument in the inner circuit subsystem.

[0060] A first composite foam insulation material 2 is sprayed on the outer wall of the liquid hydrogen storage tank 1, a composite multilayer insulation component 3 is coated on the outer surface of the first composite foam insulation material 2, and a large-area cooling screen 4 formed by multiple pipelines connected in parallel is embedded in the middle layer of the composite multilayer insulation component 3.

[0061] A coiled tube heat exchanger 11 is installed on the outer wall of the liquid oxygen tank 12 and is sprayed with a second composite foam insulation material 13 .

[0062] The first composite foam insulation material 2 and the second composite foam insulation material 13 are prepared by doping heat reflective material and carbon dioxide glass beads into traditional polyurethane foam, wherein the heat reflective material composed of fragmented double-sided aluminum-coated polyimide film is located on the hot side of the multifunctional composite foam insulation material, and the carbon dioxide glass beads are located on the cold side of the multifunctional composite foam insulation material. The fragmented double-sided aluminum-coated polyimide film has an emissivity of no more than 0.06, and the carbon dioxide glass beads can form an insulation layer that is close to a vacuum at low temperatures, which is used for thermal insulation of low-temperature storage tanks.

[0063] A comprehensive thermal management method based on deeply supercooled cryogenic propellant, wherein the first temperature control valve 5 and the second temperature control valve 6 are controlled by the intelligent temperature controller 16 according to the feedback of the first temperature sensor 17, so as to realize the temperature control of the instrument 7. The high-pressure helium is driven by the circulation pump 10 to circulate in the inner cooling circuit subsystem and the outer cooling circuit subsystem respectively, and the coldness of the supercooled liquid oxygen tank 12 is transported to the insulation layer of the liquid hydrogen tank 1 and the instrument 7 respectively. The heated helium is then returned to the coil heat exchanger 11 to exchange heat with the liquid oxygen tank 12. In this cycle, the reduction of liquid hydrogen evaporation and the joint control of the temperature of the instrument are realized, so as to realize the long-term efficient operation of the cryogenic carrier on orbit.

[0064] The present invention has been described in detail above in conjunction with specific implementations and exemplary examples, but these descriptions cannot be understood as limiting the present invention. Those skilled in the art understand that, without departing from the spirit and scope of the present invention, a variety of equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its implementation methods, all of which fall within the scope of the present invention. The scope of protection of the present invention shall be subject to the attached claims.

[0065] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. An integrated thermal management system based on deeply supercooled cryogenic propellant, characterized in that: It includes an internal cooling circuit system, an external cooling circuit system and an exhaust gas recycling circuit system; The inner cooling circuit subsystem comprises a heat insulation mechanism, a circulation pump (10) and a tubular heat exchanger (11) which are connected in a circular manner in sequence through an inner cooling pipeline. The heat insulation mechanism is arranged on the outer surface of the liquid hydrogen storage tank (1), and the tubular heat exchanger (11) is arranged on the outer surface of the supercooled liquid oxygen storage tank (12) and welded into an integrated structure. The circulation pump (10) drives the working fluid to circulate in the inner cooling pipeline to achieve cooling of the outer surface of the liquid hydrogen storage tank (1). The external cooling circuit subsystem comprises an external cooling pipeline passing through the instrument equipment (7), the first end of the external cooling pipeline is connected to the heat insulation mechanism, and the second end is connected to the circulation pump (10), the working fluid flows out of the heat insulation mechanism and enters the external cooling pipeline to cool the instrument equipment (7), and then flows out of the external cooling pipeline and enters the circulation pump (10); The exhaust gas recycling loop comprises an exhaust gas pipeline passing through the instrument (7), wherein the first end of the exhaust gas pipeline is connected to the interior of the liquid hydrogen storage tank (1), and the second end is connected to the external space. The liquid hydrogen enters the exhaust gas pipeline to cool the instrument (7) and is then discharged into the external space.

2. The integrated thermal management system based on deeply supercooled cryogenic propellant according to claim 1, characterized in that: The first end and the second end of the external cooling pipeline are both connected to the portion of the internal cooling pipeline disposed between the heat insulation mechanism and the circulation pump (10), and the connection points of the first end and the second end of the external cooling pipeline and the internal cooling pipeline are respectively recorded as the first connection point and the second connection point; The portion of the inner cooling pipeline between the heat insulation mechanism and the first connection point is recorded as the first pipeline, the portion between the first connection point and the second connection point is recorded as the second pipeline, and the portion between the second connection point and the circulation pump (10) is recorded as the third pipeline; The exhaust gas recycling loop also includes a shell-and-tube heat exchanger (26), through which the liquid hydrogen in the exhaust pipeline exchanges heat with the first pipeline, and the liquid hydrogen in the exhaust pipeline provides cooling capacity for the working fluid flowing out of the heat insulation mechanism.

3. The integrated thermal management system based on deeply supercooled cryogenic propellant according to claim 2, characterized in that: A second temperature control valve (6) is provided on the second pipeline of the inner cooling pipeline, and a first temperature control valve (5) and a first temperature sensor (17) are provided on the outer cooling pipeline; The intelligent temperature controller (16) is used to collect temperature information from the first temperature sensor (17) and to control the opening of the first temperature control valve (5) and the second temperature control valve (6) in real time according to the difference between the temperature information and the expected temperature.

4. The integrated thermal management system based on deeply supercooled cryogenic propellant according to claim 3, characterized in that: The sum of the opening degrees of the first temperature control valve (5) and the second temperature control valve (6) is 100%; A compensator (9) for replenishing working fluid is also provided on the second pipeline of the inner cooling pipeline.

5. The integrated thermal management system based on deeply supercooled cryogenic propellant according to claim 1, characterized in that: The working fluid is helium at 2MPa to 5MPa; The filling temperature of the subcooled liquid oxygen in the subcooled liquid oxygen storage tank (12) is below 65K.

6. The integrated thermal management system based on deeply supercooled cryogenic propellant according to claim 1, characterized in that: The heat insulation mechanism comprises a first composite foam heat insulation material (2), a composite multi-layer heat insulation component (3) and a cooling screen (4); A first composite foam heat insulating material (2) is sprayed on the outer surface of the liquid hydrogen storage tank (1); The composite multi-layer heat insulation component (3) is coated on the outer surface of the first composite foam heat insulation material (2), the composite multi-layer heat insulation component (3) includes 30 to 80 units, each unit is composed of a reflection screen layer and a spacer layer, and the cooling screen (4) is arranged inside the composite multi-layer heat insulation component (3) and is located in the middle of the 30 to 80 units; The cooling screen (4) comprises a plurality of parallel aluminum alloy pipelines and aluminum foil for conducting heat between the aluminum alloy pipelines. The cooling screen (4) completely wraps the outer surface of the liquid hydrogen storage tank (1), and the working fluid flows into the aluminum alloy pipelines from the tubular heat exchanger (11).

7. The integrated thermal management system based on deeply supercooled cryogenic propellant according to claim 6, characterized in that: A flow divider (14) is provided at the inlet of the aluminum alloy pipeline. One path of working fluid flowing out of the tubular heat exchanger (11) is evenly divided into multiple paths of working fluid by the flow divider (14). The multiple paths of working fluid enter the multiple paths of the aluminum alloy pipeline, flow through the outer surface of the liquid hydrogen storage tank (1), and converge into one path of working fluid at the outlet of the aluminum alloy pipeline.

8. The integrated thermal management system based on deeply supercooled cryogenic propellant according to claim 6, characterized in that: The outer surface of the subcooled liquid oxygen storage tank (12) is also sprayed with a second composite foam insulation material (13); The preparation method of the first composite foam thermal insulation material (2) is as follows: First, a first layer of composite foam is sprayed on the outer surface of the liquid hydrogen storage tank (1) to allow the first layer of composite foam to foam, and then a second layer of composite foam is sprayed on the surface of the first layer of composite foam to allow the second layer of composite foam to foam; The preparation method of the second composite foam thermal insulation material (13) is as follows: First, a first layer of composite foam is sprayed on the outer surface of the integrated structure formed by welding the tubular heat exchanger (11) and the subcooled liquid oxygen storage tank (12), and the first layer of composite foam is foamed and solidified, and then a second layer of composite foam is sprayed on the surface of the first layer of composite foam to allow the second layer of composite foam to foam; The first layer of composite foam is polyurethane foam doped with glass beads, and the second layer of foam is polyurethane foam doped with fragmented heat reflective film.

9. The integrated thermal management system based on deeply supercooled cryogenic propellant according to claim 8, characterized in that: The fragmented heat reflective film is a fragmented double-sided aluminum-plated polyimide film with an equivalent diameter of 1 to 5 mm, and the glass balls are carbon dioxide glass balls.

10. A comprehensive thermal management method based on deeply supercooled cryogenic propellant, characterized in that: The integrated thermal management system according to any one of claims 1 to 9 is implemented, comprising: The circulating pump (10) drives the working medium to circulate in the internal cooling pipeline to achieve cooling of the outer surface of the liquid hydrogen storage tank (1); The working fluid flows out of the heat insulation mechanism and enters the external cooling pipeline to cool the instrument equipment (7), and then flows out of the external cooling pipeline and enters the circulation pump (10); The liquid hydrogen in the liquid hydrogen storage tank (1) enters the exhaust pipeline to cool the instrument equipment (7) and is then discharged into the external space.

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