CN112693636A - Light-weight thermal control device for satellite and manufacturing method thereof - Google Patents
Light-weight thermal control device for satellite and manufacturing method thereof Download PDFInfo
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Abstract
The invention relates to a light-weight thermal control device for a satellite and a manufacturing method thereof in the field of thermal control devices for the satellite, and the method comprises the following steps: step A, preparing the high-thermal-conductivity carbon-based composite phase-change material, which comprises the following steps: step A-1: carrying out high-temperature acidification, high-temperature expansion, water washing and drying processes on high-purity flake graphite to form graphite worms; step A-2: pressing the graphite worms into a porous graphite heat-conducting carrier; step A-3: the phase-change material is put into a porous graphite heat-conducting carrier through vacuum and impregnation processes to obtain the high-heat-conductivity carbon-based composite phase-change material; step B, preparing a packaging shell: processing an aluminum alloy material into an upper shell and a lower shell; step C, packaging: and filling and packaging the high-thermal-conductivity carbon-based composite phase change material between the upper shell and the lower shell. According to the invention, through the effective combination of the high-thermal-conductivity graphite substrate and the phase-change material, the peak temperature of a single machine in the working period and the compensation power consumption of a single machine in the non-working period can be effectively reduced.
Description
Technical Field
The invention relates to a heat control device for a satellite, in particular to a light-weight heat control device for the satellite and a manufacturing method thereof.
Background
With the integration of the functions of the satellite electronic components, the heat consumption of a single machine is higher and higher. For a long-time working single machine with large heat consumption, if a traditional heat dissipation scheme based on an aluminum alloy heat-spreading plate is adopted, the required weight resource is very large, and the single machine does not work for a period of time and also needs higher compensation power consumption to maintain the lowest temperature level; the traditional phase change material has a certain energy storage effect, but the self heat conductivity coefficient of the phase change material is very small, so that the heat conduction and the heat dissipation are not facilitated; the phase change energy storage device based on the foam metal utilizes metal to make up for the defect that the self heat conductivity coefficient of the phase change material is small, but the weight advantage is not achieved due to the fact that the density of the metal material is high.
Through the search of the prior art, a patent of a phase change heat storage capsule and a phase change heat storage device with heat pipe assisted heat exchange enhancement (application publication number CNIO8917446A) provides the phase change heat storage capsule and the phase change heat storage device based on heat pipe assisted heat exchange enhancement, heat storage is realized through the phase change heat storage capsule, heat conduction is enhanced by means of heat pipes, but the weight demand of the heat pipes is also large, and along with the commercial development of the aerospace field, the weight and power consumption resources of each subsystem of a satellite are urgently needed to be optimized so as to improve the market competitiveness of the model. The patent "a phase transition energy storage composite material" (patent publication No. CN 1226592A) proposes a composite phase transition energy storage material overlapped by phase transition temperature of 50-200 ℃ and phase transition temperature of 200-750 ℃, the surface of the material is coated by metal and non-metal materials with coating layers, the temperature of the phase transition point of the composite phase transition energy storage material is high, the composite phase transition energy storage material is not suitable for temperature control of satellite electronic components, and a satellite heat control device needs to consider the heat conduction and sealing performance besides the energy storage performance so as to efficiently dissipate heat, simultaneously ensure the reliability and safety of space application, and the design of the heat conduction and sealing performance is not involved in the patent.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a light thermal control device for a satellite and a manufacturing method thereof.
According to the invention, the manufacturing method of the light thermal control device for the satellite comprises the following steps:
step A, preparing the high-thermal-conductivity carbon-based composite phase-change material, which comprises the following steps:
step A-1: carrying out high-temperature acidification, high-temperature expansion, water washing and drying processes on high-purity flake graphite to form graphite worms;
step A-2: pressing the graphite worms into a porous graphite heat-conducting carrier;
step A-3: the phase-change material is put into the porous graphite heat-conducting carrier through vacuum and dipping processes to obtain the high-heat-conductivity carbon-based composite phase-change material;
step B, preparing a packaging shell: processing an aluminum alloy material to form an upper shell and a lower shell;
step C, packaging: filling the high-thermal-conductivity carbon-based composite phase change material between the upper shell and the lower shell, and welding and sealing the contact surface of the upper shell and the lower shell through a welding process, so that the high-thermal-conductivity carbon-based composite phase change material is packaged between the upper shell and the lower shell.
In some embodiments, the porous graphite thermal conductive carrier in step a-2 has a porosity of 65% to 85%.
In some embodiments, the phase change material of step a-3 is paraffin.
In some embodiments, the high thermal conductivity carbon-based composite phase change material in the step a-3 has a thermal conductivity of 35 to 45W/(m.k) in a face direction and a thermal conductivity of 7 to 15W/(m.k) in a longitudinal direction.
In some embodiments, the density of the high thermal conductive carbon-based composite phase change material in the step A-3 is 0.9-1.1g/cm3, and the latent heat of phase change is 175-185 kJ/kg.
In some embodiments, in the step B, the plate thickness of the upper shell is 0.3-0.7mm, and the inner surface of the lower shell is provided with a reinforcing rib, a heat-conducting column and a single-machine installation column, wherein the height of the reinforcing rib is smaller than the thickness of the high-heat-conducting carbon-based composite phase-change material.
In some embodiments, in the step C, the inner surface of the upper shell and/or the inner surface of the lower shell are coated with a heat-conducting silica gel layer.
In some embodiments, in the step C, in the process of welding and packaging the upper housing and the lower housing, a welding tool for fixing the upper housing and the lower housing is placed on the cold plate, and a cooling liquid circulates in the cold plate.
In some embodiments, in the step C, the upper casing and the lower casing are packaged by a friction stir welding process, and the overall leakage rate after packaging is less than 10-7pa.m 3/s.
The invention also provides a light-weight thermal control device for the satellite, which is manufactured by adopting the manufacturing method of the light-weight thermal control device for the satellite, and comprises a high-thermal-conductivity carbon-based composite phase-change material, an upper shell and a lower shell;
the high-thermal-conductivity carbon-based composite phase-change material is prepared by compounding graphite and paraffin, the upper shell and the lower shell are heat-conducting plates processed by aluminum alloy materials, and the high-thermal-conductivity carbon-based composite phase-change material is filled and packaged between the upper shell and the lower shell.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the invention, through the effective combination of the high-thermal-conductivity graphite substrate and the phase-change material, the high thermal conductivity of the high-thermal-conductivity graphite substrate and the energy storage advantage of the phase-change material are fully utilized, and the peak temperature in the working period of a single machine and the compensation power consumption in the non-working period can be effectively reduced.
2. According to the invention, the composite phase change material is packaged by adopting the thin-wall aluminum alloy material, so that the generation of redundant materials in a vacuum environment can be reduced, the composite phase change material is suitable for on-orbit use of satellite models, and has a remarkable weight advantage compared with the phase change material of the traditional foam metal base material.
3. The heat conduction coating is arranged on the surfaces of the upper shell and the lower shell, which are in contact with the high-heat-conduction carbon-based composite phase-change material, so that the contact thermal resistance is reduced, and meanwhile, the heat conduction performance of the light-weight thermal control device for the satellite is effectively improved by optimizing the packaging process.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of the process steps of the manufacturing method of the lightweight thermal control device for a satellite according to the present invention;
FIG. 2 is a schematic diagram of an exploded view of a lightweight thermal control device for a satellite according to the present invention;
fig. 3 is a schematic structural view of a lower shell of the lightweight thermal control device for a satellite according to the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Example 1
The invention provides a manufacturing method of a light-weight thermal control device for a satellite, which comprises the following steps as shown in figures 1-3:
step A, preparing the high-thermal-conductivity carbon-based composite phase-change material, which comprises the following steps:
step A-1: carrying out high-temperature acidification, high-temperature expansion, water washing and drying processes on high-purity flake graphite to form graphite worms;
step A-2: and pressing the graphite worms into a porous graphite heat-conducting carrier, wherein the porosity of the prepared porous graphite heat-conducting carrier is 65-85%. The porous graphite is used as a phase-change material reinforced heat transfer carrier, the porous graphite has good wettability with two phases of the phase-change material, the melted paraffin phase-change material is easily adsorbed and filled in pores of the porous graphite through the unique latticed pore structure and the capillary force of micropores of the porous graphite, the phase-change material is uniformly dispersed in pores formed by the graphite structure through the communicated porous structure, and the interfaces of the two phases are tightly combined, so that the product has better phase-change latent heat performance. Particularly preferably, the porosity of the porous graphite heat-conducting carrier is 75%, so that the amount of the phase-change material in the pores of the porous graphite filled with the phase-change material reaches an optimal balance point, and the phase-change latent heat performance is improved.
Step A-3: and (3) putting the phase-change material into the porous graphite heat-conducting carrier through vacuum and impregnation processes to obtain the high-heat-conductivity carbon-based composite phase-change material 1, wherein the phase-change material is preferably paraffin. The density of the prepared high-thermal-conductivity carbon-based composite phase change material 1 is 0.9-1.1g/cm through process control3The latent heat of phase change is 175-185kJ/kg, the facing thermal conductivity of the high thermal conductive carbon-based composite phase change material 1 is 35-45W/(m.K), and the longitudinal thermal conductivity is 7-15W/(m.K). Preferably, the density of the high-thermal-conductivity carbon-based composite phase change material 1 is 1.0g/cm3The latent heat of phase change is 180kJ/kg, the facing thermal conductivity is 40W/(m.K), and the longitudinal thermal conductivity is 10W/(m.K), so that the high thermal conductivity carbon-based composite phase change material 1 has better thermal conductivity stability.
Step B, preparing a packaging shell: and (3) processing the aluminum alloy material into the upper shell 2 and the lower shell 3 through a whole machine. Preferably, the prepared upper shell 2 and lower shell 3 have a plate thickness of 0.3-0.7mm, wherein the plate thickness of the upper shell is preferably 0.5mm, and the upper shell 2 and lower shell 3 have a more obvious weight advantage by adopting thin-walled aluminum alloy materials. Preferably, the lower case 3 is prepared to have reinforcing ribs 31, heat conduction columns 32, and single mounting columns 33 provided on the inner surface thereof. The arrangement of the reinforcing ribs 31, the heat-conducting columns 32 and the single mounting columns 33 on the lower shell 3 is preferably an array design, and the number and the positions can be determined according to actual needs. Strengthening rib 31 is used for strengthening the intensity of casing 3 and the whole casing after the encapsulation down, and heat conduction post 32 is used for strengthening casing 3 and high heat conduction carbon based composite phase change material's heat-conduction area of contact down, and stand-alone erection column 33 is connected with the fixed orifices of seting up on last casing 2 after being used for running through high heat conduction carbon based composite phase change material, ensures casing 2 and casing 3's connection structure intensity down. The height of strengthening rib 31 is less than the thickness of high heat conduction carbon base composite phase change material 1, and too much heat passes through directly the transmission between upper housing 2 and the lower housing 3, further improves the control effect of the peak temperature of satellite unit during operation, reduces the supplementary consumption demand of unit non-operating period simultaneously.
Step C, packaging: filling the high-thermal-conductivity carbon-based composite phase-change material 1 between the upper shell 2 and the lower shell 3, and welding the contact surface of the upper shell 2 and the lower shell 3 through a welding process, so that the high-thermal-conductivity carbon-based composite phase-change material 1 is hermetically packaged between the upper shell 2 and the lower shell 3.
According to the preparation method of the light-weight satellite thermal control device, the high thermal conductivity of the high thermal conductivity graphite substrate and the energy storage advantage of the phase change material are fully utilized through the effective combination of the high thermal conductivity graphite substrate and the phase change material, the peak temperature of a single machine in a working period and the compensation power consumption of the phase change material in a non-working period can be reduced, meanwhile, the device is used for packaging the composite phase change material through the thin-wall aluminum alloy material, the generation of redundant materials in a vacuum environment can be reduced, the device is suitable for on-orbit use of satellite models, and compared with the phase change material of the traditional foam metal substrate, the device has a remarkable weight advantage.
Preferably, the upper shell 2 and the lower shell 3 are packaged through a friction stir welding process, and the whole leakage rate of the packaged light thermal control device for the satellite is smaller than 10-7Pa.m3/s through the control of related processes compared with the processes such as gluing, so that the requirement of the use environment of the spacecraft is better met.
Example 2
The embodiment 2 is formed on the basis of the embodiment 1, the thermal contact resistance is reduced by arranging the thermal conductive coating on the surfaces of the upper shell and the lower shell, which are in contact with the high-thermal-conductivity carbon-based composite phase change material, and meanwhile, the thermal conductivity of the light-weight thermal control device for the satellite is effectively improved by optimizing the packaging process.
As shown in fig. 1 to 3, after the aluminum alloy material is manufactured into the upper shell 2 and the lower shell 3 by the whole machine process, at least one of the inner surface of the upper shell 2 and the inner surface of the lower shell 3 is coated with a heat conductive coating to reduce the contact thermal resistance and improve the heat conductivity. Here, the inner surface of the upper case 2 or the inner surface of the lower case refers to a surface that is in contact with the high thermal conductive carbon-based composite phase change material 1. Preferably, a heat conductive coating is coated on both the upper and lower housings 2 and 3, the heat conductive coating preferably being a silicone rubber coating, such as silicone rubber available under the designation GDA-508.
Further, in the process of a packaging process, the high-thermal-conductivity carbon-based composite phase change material 1 is filled in the upper shell 2 and the lower shell 3 for welding and sealing, and a welding tool for fixing the upper shell 2 and the lower shell 3 is placed on a cold plate in which cooling liquid circulates. The temperature of the surface of the device in the welding process is reduced through the cold plate, so that the loss of the phase change material caused by high temperature in the welding process is reduced.
Example 3
Example 3 is a lightweight thermal control device for a satellite formed on the basis of example 1 or example 2, and is manufactured by the manufacturing method of the lightweight thermal control device for a satellite of any one of example 1 or example 2, and includes a high thermal conductive carbon-based composite phase change material 1, an upper case 2, and a lower case 3, as shown in fig. 1 to 3.
The high-thermal-conductivity carbon-based composite phase change material 1 is prepared by compounding graphite and paraffin, the upper shell 1 and the lower shell 3 are heat-conducting plates of thin-wall aluminum alloy materials formed by machining the whole machine, and the high-thermal-conductivity carbon-based composite phase change material 1 is filled and packaged between the upper shell 2 and the lower shell 3. Preferably, after the aluminum alloy material is manufactured into the upper shell 2 and the lower shell 3 through a whole machine process, at least one of the inner surface of the upper shell 2 and the inner surface of the lower shell 3 is coated with a silicon rubber heat-conducting coating so as to reduce contact thermal resistance and improve heat conduction performance. Here, the inner surface of the upper case 2 or the inner surface of the lower case refers to a surface that is in contact with the high thermal conductive carbon-based composite phase change material 1.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A manufacturing method of a light thermal control device for a satellite is characterized by comprising the following steps:
step A, preparing the high-thermal-conductivity carbon-based composite phase-change material, which comprises the following steps:
step A-1: carrying out high-temperature acidification, high-temperature expansion, water washing and drying processes on high-purity flake graphite to form graphite worms;
step A-2: pressing the graphite worms into a porous graphite heat-conducting carrier;
step A-3: the phase-change material is put into the porous graphite heat-conducting carrier through vacuum and dipping processes to obtain the high-heat-conductivity carbon-based composite phase-change material (1);
step B, preparing a packaging shell: processing an aluminum alloy material to form an upper shell (2) and a lower shell (3);
step C, packaging: filling the high-thermal-conductivity carbon-based composite phase change material (1) between the upper shell (2) and the lower shell (3), and welding and sealing the contact surface of the upper shell (2) and the lower shell (3) through a welding process, so that the high-thermal-conductivity carbon-based composite phase change material (1) is packaged between the upper shell (2) and the lower shell (3).
2. The method for manufacturing a light-weight thermal control device for a satellite according to claim 1, wherein the porosity of the porous graphite heat-conducting carrier in the step a-2 is 65% to 85%.
3. The method for manufacturing a star light-weight thermal control device according to claim 1 or 2, wherein the phase change material in the step a-3 is paraffin.
4. The manufacturing method of the light-weight thermal control device for the satellite according to claim 3, wherein the high-thermal-conductivity carbon-based composite phase change material (1) in the step A-3 has a face thermal conductivity of 35-45W/(m.K) and a longitudinal thermal conductivity of 7-15W/(m.K).
5. The manufacturing method of the star-use light weight thermal control device according to claim 3, wherein the density of the high thermal conductive carbon-based composite phase change material (1) in the step A-3 is 0.9-1.1g/cm3, and the latent heat of phase change is 175-185 kJ/kg.
6. The method for manufacturing the star lightweight thermal control device according to claim 1, wherein in the step B, the plate thickness of the upper case (2) is 0.3 to 0.7mm, a rib (31), a heat conduction column (32) and a single mounting column (33) are provided on the inner surface of the lower case (3), and the height of the rib (31) is smaller than the thickness of the high thermal conductive carbon-based composite phase change material (1).
7. The manufacturing method of the star-use light-weight thermal control device according to claim 1 or 6, wherein in the step C, the inner surface of the upper shell (2) and/or the inner surface of the lower shell (3) are coated with a heat-conducting silica gel layer.
8. The manufacturing method of the star-use light-weight thermal control device according to claim 7, wherein in the step C, in the process of welding and packaging the upper shell (2) and the lower shell (3), a welding tool for fixing the upper shell (2) and the lower shell (3) is placed on a cold plate, and cooling liquid circulates in the cold plate.
9. The manufacturing method of the star light thermal control device according to claim 1 or 8, wherein in the step C, the upper case (2) and the lower case (3) are encapsulated by a friction stir welding process, and the overall leak rate after encapsulation is less than 10-7Pa.m 3/s.
10. A lightweight thermal control device for a satellite, characterized by being manufactured by the manufacturing method of the lightweight thermal control device for a satellite according to any one of claims 1 to 9, and comprising a high thermal conductive carbon-based composite phase change material (1), an upper shell (2) and a lower shell (3);
high heat conduction carbon base composite phase change material (1) is graphite and paraffin complex preparation and forms, go up casing (1) with casing (3) are the heat-conducting plate that aluminum alloy material processing formed down, high heat conduction carbon base composite phase change material (1) is filled and is encapsulated in go up casing (2) with between lower casing (3).
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| CN113532175A (en) * | 2021-06-25 | 2021-10-22 | 山东大学 | Structural and functional integrated device based on composite phase-change material and preparation method thereof |
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Application publication date: 20210423 |