CN114148550A - Integrated flexible energy storage heat dissipation device for satellite - Google Patents
Integrated flexible energy storage heat dissipation device for satellite Download PDFInfo
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- CN114148550A CN114148550A CN202111441333.4A CN202111441333A CN114148550A CN 114148550 A CN114148550 A CN 114148550A CN 202111441333 A CN202111441333 A CN 202111441333A CN 114148550 A CN114148550 A CN 114148550A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
Abstract
The invention discloses an integrated flexible energy storage heat dissipation device for a satellite, which comprises: the phase-change energy storage box is internally provided with a cavity, and a heat source connecting part is arranged on the side wall of the phase-change energy storage box, which is far away from the surface of the heating part; the flexible light heat conducting cable comprises a high heat conducting graphite belt, one end of the high heat conducting graphite belt is connected with the heat source connecting part, and the other end of the high heat conducting graphite belt is connected with the heat sink connecting part; a plurality of fins are arranged on the inner side of the side wall, close to the surface of the heating part, of the phase-change energy storage box, and phase-change materials are filled in the cavity. According to the passive integrated flexible energy storage and heat transfer device, the phase change material and the heat conducting cable are coupled and integrated, instantaneous heat of a heat source is rapidly stored by using the phase change material, and absorbed heat is discharged in time by using the heat conducting cable, so that the passive integrated flexible energy storage and heat transfer device is formed, the advantages and the characteristics of the passive integrated flexible energy storage and heat transfer device are fully exerted, and the requirements of collection, transmission and dissipation of satellite load heat are met.
Description
Technical Field
The invention relates to the technical field of aerospace equipment, in particular to an integrated flexible energy storage heat dissipation device for a satellite.
Background
Currently, phase change materials and thermal cables are two techniques commonly used by satellite systems to solve the thermal control problem.
The phase change material is generally disposed on the surface of the heat source or the surface of the heat source accessory, and absorbs energy at high load and releases energy at low load by latent heat of melting and solidifying by itself to suppress the rate of temperature change and extreme temperature value of the heat source. However, the satellite system has limited target weight and available space, and a heat source with characteristics of large instantaneous heat generation, short heating cycle interval, long duration and the like is easy to cause complete melting of the phase change material.
The heat conducting cable is generally composed of two fixed ends of a heat source and a heat sink and a flexible heat conducting strip in the middle, and the heat flow is directionally transmitted through the high heat conducting property of the flexible heat conducting strip. In the face of a large amount of instant heating of the heating element, the heat conducting cable also has the problem that the heat is difficult to be rapidly and timely removed. In view of the fact that the load which works periodically for a short time has the thermal characteristics of high instantaneous power consumption and high heat flow density, a high-efficiency and low-dissipation thermal control system is needed to finish heat dissipation on a satellite platform with limited space and energy, and the temperature distribution requirement of a target heat source is met.
To solve the above problems, the patent names: passive thermal systems including combined heat pipes and phase change materials and satellites containing such systems, patent No.: 201680028052.7 discloses a passive thermal system for satellite and other aerospace applications, the specific structure is: the heat pipe working fluid is disposed in a first chamber of the container, and the PCM is contained in a second chamber that substantially surrounds the first chamber. According to a typical heat pipe design, the first chamber contains a wick for heat transfer. The exterior of the first chamber has fins or the like extending into the PCM for heat dissipation and increased interface area. This arrangement is disadvantageous for use in satellite systems having moving components or the like that require flexible connections.
To solve the above problems, the patent names: a high-power phase change energy storage heat exchanger, patent number: 201810664426.5, it combines pump-driven single-phase fluid circuit and high-power phase-change energy storage technology, and then uses small-scale outer circuit to slowly dissipate the heat stored in phase-change material, to form fluid circuit system with inner and outer circuit structure, to fully play the advantages of the two, and satisfy the heat dissipation requirement of super-power and super-high heat flow density load. However, the device belongs to an active thermal control system, and is not beneficial to popularization in the thermal control system under the trend of low energy occupancy rate.
Therefore, the technical personnel in the field provide an integrated flexible energy storage heat sink for satellites to solve the problems in the background art.
Disclosure of Invention
The invention provides an integrated flexible energy storage and heat dissipation device for a satellite, which can solve the problems, can be used for coupling and integrating a phase change material and a heat conducting cable, quickly stores instantaneous heat of a heat source by using the phase change material, and simultaneously discharges absorbed heat in time by using the heat conducting cable to form a passive integrated flexible energy storage and heat transfer device, fully exerts the advantages and the characteristics of the phase change material and the heat conducting cable, and meets the requirements of collection, transmission and dissipation of satellite load heat.
In order to achieve the above purpose, the invention provides the following technical scheme:
the invention discloses an integrated flexible energy storage heat dissipation device for a satellite, which comprises:
the phase-change energy storage box is internally provided with a cavity, and a heat source connecting part is arranged on the side wall of the phase-change energy storage box, which is far away from the surface of the heating part;
the flexible light heat conducting cable comprises a high heat conducting graphite belt, one end of the high heat conducting graphite belt is connected with the heat source connecting part, and the other end of the high heat conducting graphite belt is connected with the heat sink connecting part;
a plurality of fins are arranged on the inner side of the side wall, close to the surface of the heating part, of the phase-change energy storage box, and phase-change materials are filled in the cavity.
Further, phase change energy storage box includes left side wall, right side wall, roof, diapire and two end covers, left side wall, right side wall, roof and diapire are hollow cuboid by 3D printing apparatus integrated into one piece, two the end cover seals in hollow cuboid both ends through laser welding respectively, the filling opening has been seted up on the end cover, the bottom of left side wall and right side wall and the lateral wall of heat sink connecting portion outwards protruding formation a plurality of installation angles respectively.
Furthermore, the heat source connecting part is a slot, a notch of the slot is positioned at the top of the right side wall and extends into the top wall, the thickness of the slot is not more than twenty percent of the maximum thickness of the cavity, one end of the high-heat-conductivity graphite strip is inserted into the slot, and a first heat-conducting layer is arranged between the high-heat-conductivity graphite strip and the inner wall of the slot.
Further, the ribs extend from the bottom wall to the top wall, and the height of the ribs is thirty percent to sixty percent of the maximum thickness of the cavity.
Furthermore, a groove is formed in the side wall of the heat sink connecting portion, the other end of the high-heat-conductivity graphite belt is inserted into the groove, and a second heat-conducting layer is arranged between the high-heat-conductivity graphite belt and the inner wall of the groove.
Furthermore, the bottom surface of the heat sink connecting part close to the heat dissipation surface and the bottom surface of the bottom wall are both provided with thermal interfaces, and the thermal interfaces are made of thermal grease.
Preferably, the high-thermal-conductivity graphite tape is formed by laminating and pressing a pyrolytic graphite heat-conducting film and an adhesive layer, and is packaged by a polyimide film.
Preferably, the cavity is further filled with a particulate matter for enhancing the thermal conductivity of the phase-change material, the phase-change material is paraffin, and the particulate matter is metal powder or graphene powder.
The first heat conduction layer and the second heat conduction layer are made of heat conduction materials, and the heat conduction materials are selected from one or more of heat conduction viscose, heat conduction gel and heat conduction paste.
The first heat conduction layer and the second heat conduction layer are made of metal materials, and the metal materials are selected from one or more of gallium-bismuth alloy, gallium-tin alloy and gallium-indium alloy.
In the technical scheme, the integrated flexible energy storage heat dissipation device for the satellite provided by the invention has the following beneficial effects:
1. the phase change energy storage box and the heat source connecting part are integrally processed and molded, so that the thermal resistance of the heat transmission intermediate link is effectively reduced, and the space resources of the satellite platform are reasonably utilized. Meanwhile, two thermal control technologies of the phase-change material and the flexible light heat conducting cable are effectively combined to make up for the shortages, so that on one hand, the phase-change material is utilized to collect the instantaneous heat generated by the satellite load, and the large temperature change rate and temperature peak value of a target heat source are avoided; on the other hand, the stored heat is transmitted and dissipated in time by utilizing the heat conducting cable, the phase-change material is ensured to continuously and reliably absorb the heat of the heat source, and the target temperature is maintained in a stable range by effectively and regularly collecting and discharging the redundant heat.
2. The integrated fins are processed on the inner surface of the bottom wall of the phase change energy storage box, and the phase change material is added with the heat transfer enhancement particle substances, so that the heat transfer in the phase change energy storage box is enhanced; the flexible light heat conducting cable is convenient to use in a small satellite platform which is provided with a movable assembly, is not easy to be connected with a larger rigidity or is complex in layout, a heat transmission path is flexibly arranged, and the thermal control requirement of the complex satellite body assembly is met; the satellite platform thermal control method does not need extra energy supply, and is a better choice for a miniaturized and intensive satellite platform thermal control mode with high power density load.
Drawings
In order to more clearly illustrate the embodiments of the present application or technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present invention, and other drawings can be obtained by those skilled in the art according to the drawings.
Fig. 1 is an exploded schematic structural view of an integrated flexible energy storage heat dissipation device for a satellite according to an embodiment of the present invention;
FIG. 2 is a cross-sectional view of FIG. 1;
fig. 3 is a reference diagram of a use state of an integrated flexible energy storage and heat dissipation device for a satellite according to an embodiment of the present invention.
Description of reference numerals:
1. a phase change energy storage box; 2. a heat source connection part; 3. a flexible lightweight thermal cable; 4. a heat sink connecting portion; 5. mounting an angle; 6. a thermal interface; 7. a satellite; 8. a movable focal plane assembly;
11. ribs; 12. a left side wall; 13. a right side wall; 14. a top wall; 15. a bottom wall; 16. an end cap; 17. a filling port; 18. a cavity;
31. a high thermal conductivity graphite tape; 32. a first thermally conductive layer;
41. a groove; 42. a second thermally conductive layer;
71. a satellite heat dissipation surface;
81. a CCD detector.
Detailed Description
In order to make the technical solutions of the present invention better understood, those skilled in the art will now describe the present invention in further detail with reference to the accompanying drawings.
As shown in FIGS. 1-2;
the embodiment of the invention provides an integrated flexible energy storage heat dissipation device for a satellite, which comprises:
the phase change energy storage box 1 is internally provided with a cavity 18, and the side wall of the phase change energy storage box 1, which is far away from the surface of a heating element, is provided with a heat source connecting part 2;
the flexible light heat conducting cable 3 comprises a high heat conducting graphite belt 31, one end of the high heat conducting graphite belt 31 is connected with the heat source connecting part 2, and the other end of the high heat conducting graphite belt 31 is connected with the heat sink connecting part 4; the high-heat-conductivity graphite belt 31 is integrally connected with the heat source connecting part 2 and the heat sink connecting part 4 by adopting a cold die forging process;
the inner side of the side wall close to the surface of the heating element on the phase change energy storage box 1 is provided with a plurality of fins 11, the cavity 18 is filled with a phase change material, the fins 11 can enable heat of a heat source to be received by the phase change material in the phase change energy storage box 1 well, each fin 11 is in the shape of a cuboid, a cylinder, a prismatic table, a circular truncated cone and the like, the shape of each fin 11 is preferably a cone with the sectional area of the top of the fin 11 smaller than that of the bottom of the fin, so that the fins 11 maintain a uniform temperature gradient to ensure the temperature uniformity of the whole phase change energy storage box 1, and the distance between every two adjacent fins is 2-3 mm.
The phase change energy storage box 1 comprises a left side wall 12, a right side wall 13, a top wall 14, a bottom wall 15 and two end covers 16, wherein the left side wall 12, the right side wall 13, the top wall 14 and the bottom wall 15 are integrally formed into a hollow cuboid by 3D printing equipment, the two end covers 16 are respectively sealed at two ends of the hollow cuboid through laser welding, a filling port 17 is formed in each end cover 16, and a space defined by the two end covers 16, the left side wall 12, the right side wall 13, the top wall 14 and the bottom wall 15 is a cavity 18; the bottoms of the left side wall 12 and the right side wall 13 and the side wall of the heat sink connecting part 4 respectively protrude outwards to form a plurality of mounting angles 5; the mounting angle 5 is a mounting angle with a hole, so that the phase change energy storage box 1 is conveniently connected with the surface of the heating element and the heat sink connecting part 4 through bolts and the heat dissipation surface.
The heat source connecting part 2 is a slot, a notch of the slot is positioned at the top of the right side wall 13 and extends into the top wall 14, the slot is processed by linear cutting on the right side wall 13, and the outer surface of the top wall 14 is provided with fins integrally formed with the top wall, so that the heat transfer surface is increased to the maximum extent, and the overall heat transfer efficiency of the phase change energy storage box 1 is further enhanced; the thickness of the slot is not more than twenty percent of the maximum thickness of the cavity 18, one end of the high-heat-conductivity graphite belt 31 is inserted into the slot, and a first heat-conduction layer 32 is arranged between the high-heat-conductivity graphite belt 31 and the inner wall of the slot so as to improve the heat conductivity.
The slots can be reasonably distributed according to the available space of the satellite thermal control system and can be selectively arranged on the left side wall 12, the right side wall 13, the top wall 14 or the bottom wall 15, the optimal position is the top center position of the vertical side surface of the contact surface of the phase change energy storage box 1 and a target heat source, and the thickness of the slots is 1-3 mm. The length of the high heat conduction graphite strip 31 extending into the slot is less than or equal to the depth of the slot.
The ribs 11 extend from the bottom wall to the top wall, and the height of the ribs 11 is thirty percent to sixty percent of the maximum thickness of the cavity 18.
A groove 41 is formed in the side wall of the heat sink connecting portion 4, the other end of the high thermal conductivity graphite tape 31 is inserted into the groove 41, and a second thermal conductive layer 42 is arranged between the high thermal conductivity graphite tape 31 and the inner wall of the groove 41 to improve the thermal conductivity.
The bottom surface of the heat sink connecting part 4 close to the heat dissipation surface and the bottom surface of the bottom wall are both provided with thermal interfaces 6, and the thermal interfaces 6 are made of heat conducting grease, specifically one of room temperature vulcanized silicone resin RTV or epoxy resin. The bottom surface of the bottom wall 15 is thermally coupled with the surface of the heating element, the heat sink connecting part 4 and the heat dissipation surface through thermal interfaces, so that the interface contact thermal resistance is reduced.
The high-thermal-conductivity graphite belt 31 is formed by laminating and pressing a pyrolytic graphite heat-conducting film and an adhesive layer, and is packaged by a polyimide film, wherein the raw material of the adhesive layer is an acrylic adhesive.
The cavity 18 is further filled with a particulate matter for enhancing the thermal conductivity of the phase change material, the phase change material is a substance capable of performing phase change between solid and liquid within a certain temperature range, and is preferably paraffin. The phase change material and particulate matter are filled through fill port 17 and sealed with a high vacuum sealant.
The first heat conduction layer and the second heat conduction layer are made of heat conduction materials, and the heat conduction materials are selected from one or more of heat conduction viscose, heat conduction gel and heat conduction paste.
The first heat conduction layer and the second heat conduction layer are made of metal materials, and the metal materials are selected from one or more of gallium-bismuth alloy, gallium-tin alloy and gallium-indium alloy.
As shown in fig. 3;
the phase change energy storage box 1 transfers heat from the CCD detector 81 in the active focal plane assembly 8 within the satellite 7 to the satellite cooling surface 71.
Specifically, the phase change energy storage box 1 is arranged on one side (the surface of a heating element) of the CCD detector 81 and is fixedly connected by a bolt; the heat sink connecting portion 4 is provided on one side of the satellite heat radiating surface 71 (heat radiating surface) and fixed by bolting. The bottom wall 15 of the phase change energy storage box 1 is thermally connected with the CCD detector 12, and the bottom surface of the heat sink connecting part 4 is thermally connected with the contact surface of the satellite heat dissipation surface 71 through thermal interfaces 6.
The phase change energy storage box 1 collects heat generated by the CCD detector 81 in the movable focal plane assembly 8 through solid-liquid phase change of the phase change material in the cavity 18 within a certain temperature range, and the phase change material usually undergoes phase change at a higher temperature (usually set within a range of fifteen to forty degrees centigrade according to a target working temperature of a heat source), so that the temperature of the CCD detector 81 is kept near a phase change temperature point of the phase change material. The heat absorbed by the phase-change material is transferred to the heat source connecting part 2 through the auxiliary enhancement effect of the plurality of fins 11 and the particulate matter, then is transferred to the heat sink connecting part 4 through the high-heat-conductivity graphite tape 31, and is radiated to the outer space through the satellite radiating surface 71, so that the phase-change material is ensured not to be completely melted due to continuous heat generation at short periodic intervals and instantaneous high power of the CCD detector 81. With the pause of the CCD detector 81, the phase change material gradually solidifies in preparation for the next cycle.
This application can carry out integration machine-shaping with phase change energy storage box 1 and heat source connecting portion 2, effectively reduces the thermal resistance of heat transmission intermediate link, the space resource of rational utilization satellite platform. By effectively combining the phase change material and the flexible light heat conducting cable 3, the instantaneous heat generation amount of the satellite load is collected by the phase change material, so that the larger temperature change rate and temperature peak value of a target heat source are avoided; on the other hand, the stored heat is transmitted and dissipated in time by utilizing the heat conducting cable, the phase-change material is ensured to continuously and reliably absorb the heat of the heat source, and the target temperature is maintained in a stable range by effectively and regularly collecting and discharging the redundant heat.
The integrated fins 11 are processed on the inner surface of the bottom wall 15 of the phase change energy storage box 1, and the phase change material is added with heat transfer enhancement particle substances, so that the heat transfer inside the phase change energy storage box 1 is enhanced. The flexible light heat conducting cable 3 is convenient to use in a small satellite platform which is provided with a movable assembly, is not easy to be connected with larger rigidity or has a complex layout, a heat transmission path is flexibly arranged, and the thermal control requirement of the complex satellite body assembly is met. The whole assembly does not need additional energy supply, and is a better choice for a miniaturized and intensified satellite platform thermal control mode with high power density load.
While certain exemplary embodiments of the present invention have been described above by way of illustration only, it will be apparent to those of ordinary skill in the art that the described embodiments may be modified in various different ways without departing from the spirit and scope of the invention. Accordingly, the drawings and description are illustrative in nature and should not be construed as limiting the scope of the invention.
Claims (10)
1. An integrated flexible energy storage heat sink for a satellite, the device comprising:
the phase change energy storage box (1), a cavity (18) is arranged in the phase change energy storage box (1), and a heat source connecting part (2) is arranged on the side wall, far away from the surface of the heating element, of the phase change energy storage box (1);
the flexible light heat conducting cable (3) comprises a high heat conducting graphite belt (31), one end of the high heat conducting graphite belt (31) is connected with the heat source connecting part (2), and the other end of the high heat conducting graphite belt is connected with the heat sink connecting part (4);
a plurality of fins (11) are arranged on the inner side of the side wall of the phase change energy storage box (1) close to the surface of the heating element, and phase change materials are filled in the cavity (18).
2. The integrated flexible energy storage and heat dissipation device for the satellite is characterized in that the phase change energy storage box (1) comprises a left side wall (12), a right side wall (13), a top wall (14), a bottom wall (15) and two end covers (16), the left side wall (12), the right side wall (13), the top wall (14) and the bottom wall (15) are integrally formed into a hollow cuboid through 3D printing equipment, the two end covers (16) are sealed at two ends of the hollow cuboid through laser welding respectively, filling ports (17) are formed in the end covers (16), and the bottoms of the left side wall (12) and the right side wall (13) and the side wall of the heat sink connecting portion (4) protrude outwards respectively to form a plurality of mounting angles (5).
3. The integrated flexible energy-storage heat-dissipation device for the satellite is characterized in that the heat source connecting part (2) is a slot, the notch of the slot is positioned at the top of the right side wall (13) and extends into the top wall (14), the thickness of the slot is not more than twenty percent of the maximum thickness of the cavity (18), one end of the high-thermal-conductivity graphite strip (31) is inserted into the slot, and a first thermal-conductivity layer (32) is arranged between the high-thermal-conductivity graphite strip (31) and the inner wall of the slot.
4. An integrated flexible energy-storing and heat-dissipating device for satellites according to claim 2, characterized in that said fins (11) extend from the bottom wall to the top wall, the height of said fins (11) being thirty to sixty percent of the maximum thickness of the cavity (18).
5. The integrated flexible energy storage and heat dissipation device for the satellite is characterized in that a groove (41) is formed in the side wall of the heat sink connecting portion (4), the other end of the high thermal conductivity graphite tape (31) is inserted into the groove (41), and a second thermal conductivity layer (42) is arranged between the high thermal conductivity graphite tape (31) and the inner wall of the groove (41).
6. An integrated flexible energy-storing and heat-dissipating device for satellites according to claim 5, wherein the bottom surface of the heat sink connecting part (4) close to the heat dissipating surface and the bottom surface of the bottom wall (15) are both provided with a thermal interface (6), and the material of the thermal interface (6) is heat conducting grease.
7. The integrated flexible energy storage and heat dissipation device for the satellite is characterized in that the high-thermal-conductivity graphite tape (31) is formed by laminating and pressing a pyrolytic graphite heat-conducting film and an adhesive layer and is encapsulated by a polyimide film.
8. The integrated flexible energy-storage heat-dissipation device for the satellite is characterized in that the cavity (18) is filled with particulate matters for enhancing the thermal conductivity of a phase-change material, wherein the phase-change material is paraffin, and the particulate matters are metal powder or graphene powder.
9. The integrated flexible energy-storing and heat-dissipating device for the satellite according to claim 5, wherein the first heat conducting layer (32) and the second heat conducting layer (42) are made of a heat conducting material selected from one or more of heat conducting adhesive, heat conducting gel and heat conducting paste.
10. The integrated flexible energy storage and heat dissipation device for the satellite according to claim 5, wherein the first heat conduction layer (32) and the second heat conduction layer (42) are made of metal materials, and the metal materials are selected from one or more of gallium-bismuth alloy, gallium-tin alloy and gallium-indium alloy.
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| CN202111441333.4A CN114148550A (en) | 2021-11-30 | 2021-11-30 | Integrated flexible energy storage heat dissipation device for satellite |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114757059A (en) * | 2022-06-15 | 2022-07-15 | 齐鲁空天信息研究院 | Equivalent construction method and device of thermal analysis model of satellite radiating surface |
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| JPH1039955A (en) * | 1996-07-19 | 1998-02-13 | Furukawa Electric Co Ltd:The | Structure for cooling heating element for notebook type electronic equipment |
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| CN114757059B (en) * | 2022-06-15 | 2022-09-06 | 齐鲁空天信息研究院 | Equivalent construction method and device of thermal analysis model of satellite radiating surface |
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