Integrated space thermal control system

Abstract

The invention discloses an integrated space thermal control system which comprises a heat dissipation module, a refrigerating machine and a cooling capacity transmission module. When the refrigerating machine normally works, the temperature of the refrigerating end is reduced, cold energy is provided for the outside, the cold finger hot end continuously emits heat, heat of the cold finger hot end of the refrigerating machine is dissipated outwards through the heat dissipation module, and the cold energy generated by the refrigerating machine is transmitted to spacecraft equipment needing to work at the low temperature through the cold energy transmission module. Therefore, accurate temperature control of the low-temperature spacecraft equipment is realized. The hot end of the cold finger is integrally coupled with the first evaporator, and the refrigerating end of the cold finger is integrally coupled with the second condenser, so that the integrated coupling of low-temperature acquisition, cold energy transmission and heat dissipation is realized, the interface heat transfer temperature difference can be greatly reduced, and the system efficiency is improved.

Description

Technical Field

[0001] The present invention relates to an integrated space thermal control system, and in particular to an integrated space thermal control system for low temperature acquisition, cold energy transmission and heat dissipation, and belongs to the field of spacecraft thermal control technology. Background Art

[0002] With the rapid development of deep space exploration and other fields, remote sensing instruments are widely used in various types of spacecraft. The spacecraft thermal control system that matches the remote sensing instrument needs to be able to obtain cold at low temperatures, efficiently transmit the cold to the load, and promptly dissipate the heat generated by the refrigeration device, thereby providing a stable and reliable low-temperature working environment for low-temperature detectors, superconducting devices, cryogenic electronics and other devices, reducing thermal noise interference and improving detection accuracy and sensitivity.

[0003] Existing mechanical refrigerator technology has been successfully applied in the field of spacecraft remote sensing. The cold is transferred to the payload through solid heat conduction, and the heat generated by the refrigeration device is dissipated through heat pipes. However, with the continuous improvement of the micro-vibration index and weight index requirements of the satellite platform, the existing solid heat conduction solutions represented by copper braids, copper foil cold chains, graphite-copper composite guide ropes, etc. have limited heat conduction distance, large heat transfer temperature difference, large heat leakage loss, and easy vibration transmission. They can no longer meet the low micro-vibration index requirements of satellites and the requirements for efficient transmission of cold over long distances. On the other hand, with the increase in the number of spacecraft launch missions, the weight and heat dissipation resources on the satellite are tight. At the same time, the enhanced payload performance also brings challenges to the efficient dissipation of heat on the satellite. The existing heat dissipation solution based on external heat pipes has a large heat transfer temperature difference, low heat dissipation efficiency, and high demand for on-satellite heat dissipation surface resources. Moreover, from the perspective of the overall system, there are multiple interfaces between the cold acquisition device, the cold transmission device, and the heat dissipation device in the existing solution, and there are many coupling interfaces between the systems, and the overall refrigeration and cold and heat transfer efficiency is low. Therefore, it is necessary to design an integrated space thermal control system with high efficiency and reliability for low-temperature acquisition, cold transmission and heat dissipation based on the spacecraft's low-temperature refrigeration needs and efficient heat dissipation needs. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art and provide an integrated space thermal control system. In view of the characteristics of conventional thermal control schemes, such as the independence of the cold acquisition system, the cold transmission system and the heat dissipation system, redundant coupling interfaces, poor overall system performance and low efficiency, an integrated design, overall filling and system control scheme is adopted to achieve efficient acquisition of cold and efficient long-distance transmission.

[0005] The technical solution of the present invention is:

[0006] The present invention discloses an integrated space thermal control system, which is characterized by comprising: a heat dissipation module, a refrigerator and a cold transmission module; wherein:

[0007] The cold energy transmission module comprises: a second condenser, a transmission pipeline and a second evaporator;

[0008] The refrigerator comprises a compressor and a refrigeration end; the operation of the compressor drives the refrigeration end to generate cold;

[0009] The heat dissipation module includes a first condenser, a heat dissipation pipeline and a first evaporator; the first condenser is coupled to an external heat dissipation surface;

[0010] The second condenser is coupled to the refrigeration end, and the refrigeration end cools the second condenser; the working fluid forms a cycle in the second condenser, the transmission pipeline, and the second evaporator, and the cold energy generated by the refrigerator at the second condenser is transmitted to the second evaporator; the second evaporator is coupled to the external load, and the acquired cold energy is transmitted to the spacecraft load, providing a low-temperature working environment for the load;

[0011] The first evaporator is connected to the refrigerator; the working fluid circulates in the first condenser, the heat exhaust pipeline and the first evaporator, transferring the heat generated by the operation of the refrigerator to the first condenser, and dissipating the heat through the heat dissipation surface.

[0012] Furthermore, in the above system, the heat exhaust pipeline includes a first gas pipeline and a first liquid pipeline; wherein,

[0013] The heat generated by the operation of the refrigerator vaporizes the working fluid in the first evaporator. The vaporized gaseous working fluid in the first evaporator flows along the first gas pipeline to the first condenser. The gaseous working fluid releases heat and condenses and liquefies in the first condenser. Driven by the pressure difference, the condensed liquid flows back to the first evaporator along the first liquid pipeline to continue absorbing the heat generated by the refrigerator.

[0014] Furthermore, in the above system, the refrigerator also includes a cold finger hot end; wherein the cold finger hot end, the compressor and the first evaporator are coupled to realize heat exchange between the cold finger hot end, the compressor and the first evaporator; the cold energy generated by the refrigeration end is conducted to the second condenser, and heat exchange is performed with the working fluid in the second condenser. The cold energy generated by the refrigeration end causes the gas phase working fluid in the second condenser to condense and liquefy to form a supercooled liquid working fluid; driven by the pressure difference, the supercooled liquid working fluid flows along the second liquid pipeline to the second evaporator, absorbs the heat generated by the load in the second evaporator, and maintains the load in a low-temperature working environment; the gas working fluid after absorbing heat and vaporizing flows back to the second condenser along the second gas pipeline, and is condensed into liquid again under the action of the cold energy of the refrigeration end; the heat generated on the cold finger hot end and the compressor is conducted to the first evaporator, and heat exchange is performed with the working fluid in the first evaporator. The liquid working fluid in the first evaporator absorbs heat and vaporizes, absorbing the heat generated by the operation of the refrigerator.

[0015] Furthermore, in the above system, the transmission pipeline includes: an air storage chamber, a second gas pipeline and a second liquid pipeline; wherein, the input end of the second gas pipeline is connected to the second evaporator, and the output end is sequentially connected to the air storage chamber and the second condenser; the input end of the second liquid pipeline is connected to the second condenser, and the output end is connected to the second evaporator; the working fluid forms a circulation in the second condenser, the second liquid pipeline, the second evaporator, the second gas pipeline and the air storage chamber, and the cold energy generated by the refrigerator at the second condenser is transmitted to the second evaporator, and the second evaporator transmits the obtained cold energy to the spacecraft payload.

[0016] Furthermore, in the above system, the hot end of the cold finger, the compressor and the first evaporator are connected by welding, screws, powder metallurgy or integrated processing.

[0017] Furthermore, in the above system, a channel is provided on the hot end of the cold finger and the shell of the compressor, and a first evaporator is formed by filling a porous structure in the channel, thereby realizing an integrated coupling of the first evaporator and the hot end of the cold finger.

[0018] Furthermore, in the above system, the refrigeration end and the second condenser are designed to be coupled in an integrated manner, using welding, screw connection, powder metallurgy or integrated processing.

[0019] Furthermore, in the above system, the refrigeration end is provided with an S-shaped coil channel, and the second condenser is fixed to the coil channel by welding or integrated molding, thereby realizing integrated coupling between the second condenser and the refrigeration end.

[0020] Furthermore, in the above system, the refrigerator adopts a single pulse tube refrigerator or a plurality of pulse tube refrigerators connected in parallel.

[0021] Furthermore, in the above system, the first evaporator and the second evaporator are both provided with channels and capillary structures composed of porous materials placed in the channels, and the capillary force generated by the porous structure is used to drive the flow circulation of the internal heat transfer medium.

[0022] Furthermore, in the above system, the refrigerator, the cold energy transmission module and the heat dissipation module are all closed modules, and there is only energy exchange but no material exchange between the three.

[0023] The beneficial effects of the present invention and the prior art are:

[0024] (1) The present invention combines a low-temperature acquisition device with a two-phase heat transfer device to achieve integrated coupling of low-temperature acquisition, cold transfer and heat dissipation, and sets the coupling interface between the modules inside the integrated system, which is conducive to integrated design and interface coupling. Compared with the design in which each module has an external interface in the traditional solution, the integrated system proposed in the present invention has only two external interfaces, which can be more conveniently coupled with external interfaces such as spacecraft payloads and heat dissipation surfaces. At the same time, it effectively reduces the thermal resistance of the system, increases the transmission efficiency of cold and heat, and greatly improves the overall heat transfer efficiency and operating performance of the system.

[0025] (2) The space thermal control system proposed in the present invention can be filled with working fluid after the integration is completed, which shortens the system development cycle; at the same time, it is convenient to control the system as a whole. The systematic design concept can effectively reduce the local redundant design of each module such as low temperature acquisition, cold transmission, and heat dissipation within the system, which is convenient for realizing the optimal design of the system.

[0026] (3) The cold energy transmission scheme adopted in the present invention has the advantages of high transmission efficiency, high reliability, long-distance cold energy transmission, and isolation of micro-vibration. The working medium can be selected according to the working temperature zone of the payload, and can meet the low-temperature working requirements of different payloads such as low-temperature detectors. It is particularly suitable for spacecraft platforms with high vibration requirements and transmission distance requirements.

[0027] (4) The present invention adopts an integrated design, overall filling and system control solution to improve the energy transmission efficiency within the system, reduce the overall design margin of the system, simplify the system and external coupling interface, and has the characteristics of strong stability, high heat dissipation efficiency, and the ability to efficiently transmit cold energy over long distances. It can meet the requirements of high reliability, small micro-vibration, limited on-board heat dissipation resources, and weight and volume constraints in space applications, and can provide the required low-temperature working environment for spacecraft payloads. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic structural diagram of an embodiment of the present invention.

[0029] Among them, 1-heat dissipation module, 2-refrigeration machine, 3-cold transmission module, 4-first condenser, 5-first gas pipeline, 6-first liquid pipeline, 7-first evaporator, 8-cold finger hot end, 9-compressor, 10-refrigeration end, 11-second condenser, 12-gas storage chamber, 13-second gas pipeline, 14-second liquid pipeline, 15-second evaporator. DETAILED DESCRIPTION

[0030] The present invention is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0031] like Figure 1 As shown, the present invention discloses an integrated space thermal control system for low temperature acquisition, cold energy transmission and heat dissipation, including a heat dissipation module 1, a refrigerator 2 and a cold energy transmission module 3.

[0032] The heat dissipation module 1 is composed of a first condenser 4, a first gas pipeline 5, a first liquid pipeline 6, and a first evaporator 7, and is used to dissipate the heat generated by the system. In some preferred embodiments, the evaporator is preferably an annular heat exchanger.

[0033] The refrigerator 2 is composed of a cold finger hot end 8, a compressor 9 and a cooling end 10; the cold finger hot end 8 and the compressor 9 are the main heat generating parts, and the cooling end 10 is the part generating cold; the cold finger hot end 8 and the compressor 9 are coupled and connected with the first evaporator 7 to realize heat exchange between the cold finger hot end 8, the compressor 9 and the first evaporator 7. In some preferred embodiments, the refrigerator is preferably a pulse tube refrigerator, using a single or multiple parallel refrigeration units.

[0034] The cold energy transmission module 3 is composed of a second condenser 11, an air storage chamber 12, a second gas pipeline 13, a second liquid pipeline 14 and a second evaporator 15, and is used to efficiently transmit the cold energy generated by the refrigerator to the spacecraft payload; the second condenser 11 is coupled with the refrigeration end 10, and the second condenser 11 is cooled by the refrigeration end 10.

[0035] The integrated space thermal control system has two external interfaces. The first condenser 4 is the connection interface of the system to the external heat dissipation surface, which can dissipate the heat generated by the integrated system through the coupling of the condenser and the heat dissipation surface; the second evaporator 15 is the connection interface of the system to the external load, which can efficiently transmit the cold energy obtained by the integrated system to the spacecraft payload through the coupling of the evaporator and the load.

[0036] The cold finger hot end 8, the compressor 9 and the first evaporator 7 can be connected by welding, screw connection, powder metallurgy or the like, or can be formed by integrated processing. In a preferred embodiment of the present invention, a channel structure can be processed on the shell of the cold finger hot end 8 and the compressor 9, and a porous structure such as a metal mesh or felt can be filled in the channel to form the first evaporator, thereby realizing the integrated coupling of the first evaporator 7 and the cold finger hot end 8.

[0037] The refrigeration end 10 and the second condenser 11 are designed to be integrated, and can be welded, screwed, powder metallurgical, or integrated. In a preferred embodiment of the present invention, an S-shaped coil channel can be provided on the refrigeration end 10, and the second condenser can be fixed on the coil channel by welding or integrated molding technology to achieve integrated coupling between the second condenser 11 and the refrigeration end 10.

[0038] For this embodiment, in the spacecraft payload working mode, it is necessary to provide a low-temperature working environment for the payload. The compressor 9 of the refrigerator 2 is driven by electric power input to generate cold energy at the refrigeration end 10. Based on the integrated coupling structure of the refrigeration end 10 and the second condenser 11, the cold energy generated by the refrigeration end 10 can be directly conducted to the second condenser 11, and heat exchange is performed with the working medium in the second condenser 11. The cold energy generated by the refrigeration end 10 causes the gas phase working medium in the second condenser 11 to condense and liquefy, forming a liquid working medium with a certain degree of supercooling. Driven by the pressure difference, the supercooled liquid working medium flows along the second liquid pipeline 14 to the second evaporator 15, absorbs the heat generated by the load in the second evaporator 15, and maintains the load in a low-temperature working environment. The gas working medium after absorbing heat and vaporizing flows back to the second condenser 11 along the second gas pipeline 13, and is condensed into liquid again under the action of the cold energy of the refrigeration end 10. In this way, the working fluid forms a complete cycle in the second condenser 11, the second liquid pipeline 14, the second evaporator 15, the second gas pipeline 13 and the gas storage chamber 12, and the cold energy of the refrigerator at the second condenser 11 is efficiently transmitted to the second evaporator 15, thereby realizing efficient and long-distance transmission of the cold energy of the refrigerator to the spacecraft payload, providing a stable low-temperature working environment for the payload.

[0039] At the same time, the heat generated by the operation of the refrigerator is concentrated on the cold finger hot end 8 and the compressor 9. Based on the integrated coupling structure of the cold finger hot end 8, the compressor 9 and the first evaporator 7, the heat generated by the cold finger hot end 8 compressor 9 can be transferred to the first evaporator 7, and heat exchange is carried out with the working medium in the evaporator. The liquid working medium in the evaporator absorbs heat and vaporizes, which can effectively absorb the heat generated by the operation of the refrigerator. The gaseous working medium in the first evaporator 7 flows along the first gas pipeline 5 to the first condenser 4. The first condenser 4 is a coupling interface between the system and the heat dissipation surface on the satellite. The temperature of the first condenser 4 is relatively low. The gaseous working medium releases heat and liquefies in the first condenser 4. The condensed liquid flows back to the first evaporator 7 along the first liquid pipeline 6 under the drive of the pressure difference, and continues to absorb the heat generated by the refrigerator. In this way, the working medium forms a complete cycle in the first condenser 4, the first liquid pipeline 6, the first evaporator 7 and the first gas pipeline 5, and the heat generated by the operation of the refrigerator is efficiently transmitted to the first condenser 4, and is dissipated by the heat dissipation surface on the satellite, ensuring the efficient dissipation of heat in the integrated system.

[0040] During the entire operation process, the refrigerator 2 realizes efficient acquisition of cold energy, the cold energy transmission module 3 efficiently transmits the cold energy acquired by the refrigerator to the onboard payload, and the heat dissipation module 1 efficiently dissipates the heat generated by the refrigerator to the onboard heat dissipation surface. Through the integrated coupling design of the cold finger hot end 8 and the compressor 9 with the first evaporator 7, the refrigeration end 10 and the second condenser 11, the system heat transfer temperature difference is effectively reduced, the efficiency of cold energy transmission and heat dissipation is improved, a low-temperature working environment is provided for the spacecraft payload, and the integrated thermal control of the spacecraft's low-temperature acquisition, cold energy transmission, and heat dissipation is realized.

[0041] Preferably, the heat dissipation module is a closed module for achieving efficient heat dissipation, and the heat transfer medium inside it can be ammonia, methane, alcohol or the like. The selected heat transfer medium is in a gas-liquid two-phase state within the operating temperature range of the hot end of the cold finger.

[0042] Preferably, the cold transport module is a closed module for realizing efficient cold transport, and its internal heat transfer medium may be methane, nitrogen, propylene, oxygen or the like, and the selected heat transfer medium is in a gas-liquid two-phase state within the operating temperature range of the refrigeration end.

[0043] Preferably, the first evaporator and the second evaporator have a capillary structure composed of channels and porous materials inside, and the capillary force generated by the porous structure is used to drive the flow circulation of the internal heat transfer medium.

[0044] Preferably, the refrigerator, the cold energy transmission module and the heat dissipation module are all closed modules, and there is only energy exchange but no material exchange between the three.

[0045] Although the content of the present invention has been described in detail through the above preferred embodiments, it should be appreciated that the above description should not be considered as a limitation of the present invention. After reading the above content, it will be apparent to those skilled in the art that various modifications and substitutions of the present invention will occur. Therefore, the protection scope of the present invention should be limited by the appended claims.

[0046] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. Integrated space thermal control system, It is characterized in that include: A heat dissipation module (1), a refrigerator (2) and a cold transmission module (3); wherein: The cold energy transmission module (3) comprises: a second condenser (11), a transmission pipeline and a second evaporator (15); The refrigerator (2) comprises a compressor (9) and a refrigeration end (10); the operation of the compressor (9) drives the refrigeration end (10) to generate cold energy; The heat dissipation module (1) comprises a first condenser (4), a heat dissipation pipeline and a first evaporator (7); The first condenser (4) is coupled to the external heat dissipation surface; The second condenser (11) is coupled to the refrigeration end (10), and the refrigeration end (10) cools the second condenser (11); the working fluid forms a cycle in the second condenser (11), the transmission pipeline and the second evaporator (15), and the cold energy generated by the refrigerator (2) at the second condenser (11) is transmitted to the second evaporator (15); the second evaporator (15) is coupled to the external load, and the acquired cold energy is transmitted to the spacecraft load, thereby providing a low-temperature working environment for the load; The first evaporator (7) is connected to the refrigerator (2); the working fluid circulates in the first condenser (4), the heat dissipation pipeline and the first evaporator (7), and the heat generated by the operation of the refrigerator (2) is transferred to the first condenser (4), and the heat is dissipated through the heat dissipation surface.

2. The integrated space thermal control system according to claim 1, It is characterized in that The heat exhaust pipeline comprises a first gas pipeline (5) and a first liquid pipeline (6); wherein: The heat generated by the operation of the refrigerator (2) causes the working fluid in the first evaporator (7) to vaporize. The vaporized gaseous working fluid in the first evaporator (7) flows along the first gas pipeline (5) to the first condenser (4). The gaseous working fluid releases heat in the first condenser (4) to condense and liquefy. Driven by the pressure difference, the condensed liquid flows back to the first evaporator (7) along the first liquid pipeline (6) to continue to absorb the heat generated by the refrigerator (2).

3. The integrated space thermal control system according to claim 1, It is characterized in that The refrigerator (2) further comprises a cold finger hot end (8); wherein the cold finger hot end (8), the compressor (9) and the first evaporator (7) are coupled to realize heat exchange among the cold finger hot end (8), the compressor (9) and the first evaporator (7); the cold energy generated by the refrigeration end (10) is conducted to the second condenser (11) to perform heat exchange with the working medium in the second condenser (11); the cold energy generated by the refrigeration end (10) causes the gas phase working medium in the second condenser (11) to condense and liquefy to form a supercooled liquid working medium; driven by the pressure difference, the supercooled liquid working medium flows along the second liquid pipeline ( 14) flows to the second evaporator (15), absorbs the heat generated by the load in the second evaporator (15), and maintains the load in a low-temperature working environment; the gaseous working medium after absorbing heat and vaporizing flows back to the second condenser (11) along the second gas pipeline (13), and is condensed into liquid again under the action of the cold amount of the refrigeration end (10); the heat generated on the hot end (8) and the compressor (9) of the cold finger is conducted to the first evaporator (7), and heat is exchanged with the working medium in the first evaporator (7); the liquid working medium in the first evaporator (7) absorbs heat and vaporizes, absorbing the heat generated by the operation of the refrigeration machine (2).

4. The integrated space thermal control system according to claim 1, It is characterized in that The transmission pipeline comprises: a gas storage chamber (12), a second gas pipeline (13) and a second liquid pipeline (14); wherein the input end of the second gas pipeline (13) is connected to the second evaporator (15), and the output end is sequentially connected to the gas storage chamber (12) and the second condenser (11); the input end of the second liquid pipeline (14) is connected to the second condenser (11), and the output end is connected to the second evaporator (15); the working fluid forms a cycle in the second condenser (11), the second liquid pipeline (14), the second evaporator (15), the second gas pipeline (13) and the gas storage chamber (12), and the cold energy generated by the refrigerator (2) at the second condenser (11) is transmitted to the second evaporator (15), and the second evaporator (15) transmits the acquired cold energy to the spacecraft payload.

5. The integrated space thermal control system according to claim 1, It is characterized in that The cold finger hot end (8), the compressor (9) and the first evaporator (7) are connected by welding, screws, powder metallurgy or integrated processing.

6. The integrated space thermal control system according to claim 3, It is characterized in that A groove is provided on the shell of the cold finger hot end (8) and the compressor (9), and a first evaporator (7) is formed by filling a porous structure in the groove, thereby realizing integrated coupling of the first evaporator (7) and the cold finger hot end (8).

7. The integrated space thermal control system according to claim 1, It is characterized in that The refrigeration end (10) and the second condenser (11) are designed to be coupled in an integrated manner, and are formed by welding, screw connection, powder metallurgy or integrated processing.

8. The integrated space thermal control system according to claim 1, It is characterized in that The refrigeration end (10) is provided with an S-shaped coil channel, and the second condenser (11) is fixed to the coil channel by welding or integrated molding, thereby realizing integrated coupling between the second condenser (11) and the refrigeration end (10).

9. The integrated space thermal control system according to claim 1, It is characterized in that The refrigerator (2) adopts a single pulse tube refrigerator or a plurality of pulse tube refrigerators connected in parallel.

10. The integrated space thermal control system according to claim 1, Features: The first evaporator (7) and the second evaporator (15) are both provided with channels and capillary structures composed of porous materials placed in the channels, and the capillary force generated by the porous structures is used to drive the flow circulation of the internal heat transfer medium.

11. The integrated space thermal control system according to claim 1, Features: The refrigerator (2), the cold energy transmission module (3) and the heat dissipation module (1) are all closed modules, and only energy exchange but no material exchange occurs between the three.

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