CN114684392A - Back heat dissipation system of satellite solar sailboard - Google Patents
Back heat dissipation system of satellite solar sailboard Download PDFInfo
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- CN114684392A CN114684392A CN202210502991.8A CN202210502991A CN114684392A CN 114684392 A CN114684392 A CN 114684392A CN 202210502991 A CN202210502991 A CN 202210502991A CN 114684392 A CN114684392 A CN 114684392A
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- satellite
- heat
- heat dissipation
- insulation
- radiation
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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
- B64G1/503—Radiator panels
-
- 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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
Abstract
The invention discloses a back side heat dissipation system of a satellite solar sailboard, which comprises: the solar radiation system comprises a coupling plate and a heat conduction path, wherein the coupling plate comprises a satellite solar panel and a radiation plate, and the radiation plate is coupled to the back surface of the satellite solar panel; the heat conduction path communicates the radiation plate and a heat dissipation device mounted on the satellite. The radiating system fully utilizes the radiating advantage condition of the back of the solar sailboard, and the radiating board is coupled to the back of the solar sailboard to form an integrated coupling board, so that the radiating capacity of a high-heat-consumption satellite can be greatly improved, a guarantee is provided for carrying multiple loads by the satellite, the original structural arrangement of the satellite is not changed by the arrangement of the radiating board and a heat conducting passage in the radiating system, the problem of interference of the radiating system on other structures on the satellite can not be caused, and the normal operation of the satellite is ensured.
Description
Technical Field
The invention relates to the technical field of satellite heat dissipation, in particular to a back heat dissipation system of a satellite solar sailboard.
Background
The satellite will be in orbit in a vacuum and low temperature environment while being subjected to direct solar radiation, earth albedo and external heat flux from infrared radiation. The heat dissipating material may also be affected by spatial atomic oxygen, ultraviolet rays, plasma, and the like to degrade its performance. Therefore, the design of the heat dissipation system of the satellite in orbit is particularly important.
At present, the satellite generally adopts a body cabin plate or a structure of independently installing an expandable radiation plate to meet the requirement of the whole satellite on the radiation heat dissipation area.
However, if the satellite has a large load and a small volume and weight, the heat dissipation capacity of the satellite is high and concentrated, and the area of the satellite cabin body capable of dissipating heat is small, so that the heat dissipation requirement of high heat consumption cannot be met. The use of the radiation plate or the expandable radiation plate can increase the heat dissipation area, but for a small-sized satellite, not only the weight of the whole satellite is obviously increased, but also the complexity of the satellite structure is increased, and the problem of mutual interference with other equipment can occur. Therefore, the existing heat dissipation system cannot meet the heat dissipation requirements of some satellites.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides the following technical scheme.
The invention provides a back side heat dissipation system of a satellite solar sailboard, which comprises: the solar radiation system comprises a coupling plate and a heat conduction path, wherein the coupling plate comprises a satellite solar panel and a radiation plate, and the radiation plate is coupled to the back surface of the satellite solar panel; the heat conduction path communicates the radiation plate and a heat dissipation device mounted on the satellite.
Preferably, the heat dissipation system further comprises a heat insulation portion disposed between the back surface of the satellite solar sail panel and the radiation panel.
Preferably, the heat insulation part comprises a first heat insulation layer and a second heat insulation layer, the first heat insulation layer is attached to the back face of the satellite solar sailboard, the second heat insulation layer is arranged between the first heat insulation layer and the radiation plate, and a plurality of gaps are arranged on the second heat insulation layer at intervals.
Preferably, the second heat insulation layer comprises a first heat insulation piece and a second heat insulation piece which are arranged at intervals, and the gap is positioned between the first heat insulation piece and the second heat insulation piece.
Preferably, the first heat insulation piece is a polyimide heat insulation pad, the second heat insulation piece is an aerogel heat insulation piece, and the first heat insulation layer is a low-temperature multi-layer heat insulation assembly. .
Preferably, the heat dissipation device is mounted on the satellite deck, and the heat conduction path communicates the radiation plate and the position of the satellite deck where the heat dissipation device is mounted.
Preferably, the heat conduction path includes a heat pipe and a flexible heat conduction lock, the heat pipe is embedded in the satellite deck, one end of the flexible heat conduction lock is disposed on the radiation plate, and the other end of the flexible heat conduction lock is disposed on the satellite deck and connected to the heat pipe.
Preferably, the flexible heat conducting lock consists of copper foil or pyrolytic graphite sheet.
Preferably, the heat conduction path further comprises an externally attached heat pipe, and the externally attached heat pipe is arranged on the radiation plate.
Preferably, the heat dissipation system further comprises a heater and a temperature control device, the heater is arranged on one surface of the radiation plate close to the satellite solar sailboard, and the temperature control device is used for controlling the heater.
The invention has the beneficial effects that: according to the back side heat dissipation system of the satellite solar sailboard, provided by the invention, the heat dissipation advantage condition of the back side of the solar sailboard is fully utilized, the radiation board is coupled to the back side of the solar sailboard to form an integrated coupling board, and the structural strength design requirement is met and the excellent heat insulation effect is realized through multiple heat insulation means between the radiation board and the solar sailboard. In addition, a heat conduction channel is formed by the heat pipe and the flexible heat conduction lock, so that heat conduction and temperature equalization in the whole process are realized, and the safety and reliability of a heat transfer path are ensured. Meanwhile, an indirect temperature control strategy is adopted to realize accurate temperature control of heat consumption equipment in the satellite in a low-temperature mode. The back side heat dissipation system of the satellite solar sailboard can greatly improve the heat dissipation capacity of a high-heat-consumption satellite and guarantee the carrying of the satellite with multiple loads, and the arrangement of the radiation board and the heat conduction path in the heat dissipation system does not change the original structural arrangement of the satellite, so that the problem of interference of the heat dissipation system on other structures on the satellite is solved, and the normal operation of the satellite is guaranteed.
Drawings
Fig. 1 is a schematic structural diagram of a back side heat dissipation system of a satellite solar sailboard according to the present invention;
FIG. 2 is a schematic structural diagram of a coupling plate according to the present invention;
fig. 3 is a schematic structural diagram of the radiation plate according to the present invention.
In the figure, the meaning of each symbol is as follows:
1. a satellite solar panel; 2. a radiation plate; 3. a heat-consuming device; 4. a first insulating layer; 5. a void; 6. a first thermal insulation member; 7. a second thermal insulation member; 8. a satellite deck plate; 9. a heat pipe; 10. a flexible heat-conducting lock; 11. externally pasting a heat pipe; 12. a heater; 13. a battery piece.
Detailed Description
In order to better understand the technical solution, the technical solution will be described in detail with reference to the drawings and the specific embodiments.
As shown in fig. 1 to 3, an embodiment of the present invention provides a back side heat dissipation system for a satellite solar panel, including: the solar radiation system comprises a coupling plate and a heat conduction path, wherein the coupling plate comprises a satellite solar panel 1 and a radiation plate 2, and the radiation plate 2 is coupled to the back surface of the satellite solar panel 1; the heat conducting path communicates the radiation plate 2 with a heat consumer 3 mounted on the satellite.
In this embodiment, the heat dissipated by the heat dissipation device installed in the satellite body is conducted to the radiation plate located on the back surface of the solar sailboard by arranging the heat conduction path, and then the heat is dissipated to the outside through the radiation plate.
The solar sailboard is connected to the satellite body and generally arranged on the side face of the satellite body, and generally in the process of lifting the satellite off, the solar sailboard is in a folded state, and the satellite is unfolded after orbit. The solar panel is generally attached with a battery piece 13 on the surface, and solar energy is converted into electric energy and stored in the battery piece, so that electric energy is provided for the load on the satellite.
The back surface of the solar sailboard is positioned on the sunny side for a long time, and the low temperature is beneficial to heat dissipation; meanwhile, the back surface area of the solar sailboard is large, and the solar sailboard has a large heat dissipation area, so that the back surface of the solar sailboard has a good condition for arranging heat dissipation equipment.
In the embodiment, the radiation plate is arranged on the back surface of the solar sailboard, and the radiation plate and the solar sailboard are coupled into the integrated plate, so that the heat dissipation area is constructed, and the advantage that the back surface of the solar sailboard is used as the heat dissipation area is fully utilized.
For maximum heat dissipation, the radiation plate may be arranged to have the same area as the back surface of the solar panel to obtain the maximum heat dissipation area.
Wherein the radiation plate may be a plate of material having a high thermal conductivity and being light in weight, such as an aluminum plate.
If the solar panel is in a deployable configuration, the radiation panel may be arranged in a synchronously deployed configuration with the solar panel. The radiation plate and the solar sailboard are used as an integral plate structure and are folded or unfolded synchronously.
Therefore, the heat dissipation system provided by the embodiment has a large enough heat dissipation area, can greatly improve the heat dissipation capacity of the high-heat-consumption satellite, and provides guarantee for carrying multiple loads on the satellite, and the arrangement of the radiation plate and the heat conduction path in the heat dissipation system does not change the original structural arrangement of the satellite (the radiation plate is located on the back of the solar sailboard, does not occupy the space of the satellite, does not change the structural arrangement of the satellite), so that the problem of interference of the heat dissipation system on other structures on the satellite is avoided, and the normal operation of the satellite is ensured.
In this embodiment, the heat dissipation system further includes a heat insulation portion, and the heat insulation portion is disposed between the back surface of the satellite solar sail panel 1 and the radiation panel 2.
Through setting up thermal-insulated portion, can reduce heat-conduction and heat radiation between solar sailboard and the radiation board, guarantee that the radiation board at satellite solar sailboard back keeps good heat-sinking capability.
Further, the heat insulation part may include a first heat insulation layer 4 and a second heat insulation layer, the first heat insulation layer 4 is attached to the back surface of the satellite solar panel 1, the second heat insulation layer is disposed between the first heat insulation layer 4 and the radiation plate 2, and a plurality of gaps 5 are disposed at intervals on the second heat insulation layer.
In the structure, the first heat insulation layer completely covers the whole back of the solar panel, so that the radiation heat insulation effect between the solar panel and the radiation panel is fully ensured. The second insulating layer is arranged, so that the heat conduction and insulation effects are further improved, and meanwhile, a plurality of gaps are formed in the second insulating layer. In the actual use process, the second heat insulation layer can also play a role in supporting between the solar panel and the radiation panel, and the requirement of installation strength of the radiation panel and the solar panel which are coupled together is met. Other components can be arranged in the gap to increase the heat dissipation function of the heat dissipation system.
In this embodiment, the second thermal insulation layer may include a first thermal insulation member 6 and a second thermal insulation member 7, the first thermal insulation member 6 and the second thermal insulation member 7 are disposed at intervals, and the gap 5 is located between the first thermal insulation member 6 and the second thermal insulation member 7.
Through setting up different heat insulation, can utilize the characteristics of different heat insulation itself, realize the different functions in different regions of heat insulation place. For example, in the actual use process, a first heat insulating member having both a heat insulating function and a good mechanical strength may be used at the coupling point of the radiation plate and the solar panel (the mounting point of the radiation plate on the solar panel), and the area of the first heat insulating member is only required to cover the coupling point and the area near the coupling point, and a second heat insulating member having a good heat insulating effect may be used in other areas.
In a preferred embodiment of the present invention, the first thermal insulation member 6 is a polyimide thermal insulation pad, the second thermal insulation member 7 is an aerogel thermal insulation member, and the first thermal insulation layer 4 is a low-temperature multi-layer thermal insulation assembly.
In the embodiment of the invention, the heat consumption equipment 3 is installed on the satellite cabin plate 8, and the heat conduction path is communicated with the radiation plate 2 and the position of the satellite cabin plate 8 where the heat consumption equipment 3 is installed.
By adopting the structure, the heat emitted by the heat consumption equipment can be firstly conducted to the satellite cabin plate and then conducted to the radiation plate from the satellite cabin plate through the heat conduction path.
In this embodiment, the heat conducting path may include a heat pipe 9 and a flexible heat conducting lock 10, the heat pipe 9 is embedded in the satellite deck 8, one end of the flexible heat conducting lock 10 is disposed on the radiation plate 2, and the other end of the flexible heat conducting lock 10 is disposed on the satellite deck 8 and connected to the heat pipe 9.
Wherein, the heat pipe on the satellite cabin plate is connected with the installation position of the satellite heat consumption equipment. The heat dissipated by the heat dissipation device can be firstly conducted into the heat pipe, then conducted to the flexible heat conduction lock installed on the satellite cabin plate through the heat pipe, then conducted to one end of the radiation plate from one end of the satellite cabin plate of the flexible heat conduction lock, and finally conducted to the radiation plate from the flexible heat conduction lock. The heat pipes can be arranged in a plurality of numbers, so that heat can be conducted through the heat pipes, and safety and reliability of a heat transfer path are guaranteed.
In this embodiment, the satellite deck and the solar sailboard (radiation panel) are respectively located on mutually perpendicular planes, and in order to be able to conduct heat in the heat pipes located in the deck to the radiation panel, a flexible heat conduction lock is used at a position between the radiation panel and the deck, thereby solving the problem that heat in the deck is conducted to the vertical radiation panel.
The heat pipe pre-buried in the satellite cabin plate can be an aluminum ammonia groove heat pipe. The inside of the heat pipe can be provided with an omega-shaped capillary structure along the length direction of the pipe. The whole heat pipe can be divided into:
the evaporation section is positioned at the installation position of the heat consumption equipment, the temperature is higher, and the working medium in the heat pipe absorbs heat and evaporates;
the condensation section is positioned near the flexible heat conduction lock, the temperature of the condensation section is lower, and the working medium in the heat pipe releases heat and condenses at the position;
an adiabatic section between the evaporation section and the condensation section.
In this embodiment, the flexible heat-conducting lock 10 may be made of copper foil or pyrolytic graphite sheet.
The flexible heat conduction lock can be composed of a layer of thin copper sheets, has excellent heat conduction performance and good flexibility, and can solve the problems of connection and heat conduction under the condition of a vertical structure between the cabin plate and the radiation plate. The number of the copper heat conducting cables and the number of the thin copper sheets arranged in each copper heat conducting cable can be set according to the actual heat dissipation capacity. Specifically, the thickness of the thin copper sheet can be selected from 0.01mm to 0.05 mm.
The flexible heat conductive lock may be comprised of layers of pyrolytic graphite sheets. The material of pyrolytic graphite flake is graphite with structure close to that of single crystal, which not only has very high heat conductivity coefficient, but also can reach very high curvature and has very good flexibility. The connection and heat conduction problems under the condition of a vertical structure between the cabin plate and the radiation plate can be well met.
In a preferred embodiment of the present invention, the heat conducting path may further include an external heat pipe 11, and the external heat pipe 11 is disposed on the radiation plate 2.
By adopting the structure, after the heat on the flexible heat conduction lock is conducted to the radiation plate, the heat is dispersed by the conduction of the externally attached heat pipe, so that the heat on the radiation plate can be uniformly dispersed, and the safety and the reliability are ensured.
The outer heat pipe and the flexible heat conducting lock can be respectively arranged on two corresponding surfaces of the radiation plate, for example, the outer heat pipe can be arranged on one surface close to the satellite solar panel, and the flexible heat conducting lock is arranged on the corresponding reverse surface where the outer heat pipe is arranged.
In a preferred embodiment of the present invention, the outer heat pipe 11 may be disposed in a gap between the first heat insulator 6 and the second heat insulator 7.
The externally-adhered heat pipe in the structure can play a role in supporting and isolating the satellite solar sailboard and the radiation board, so that the structure of the coupling board formed by the satellite solar sailboard and the radiation board is more stable.
In this embodiment, the heat dissipation system may further include a heater 12 and a temperature control device (not shown in the figure), where the heater 12 is disposed on a side of the radiation plate 2 close to the satellite solar panel 1, and the temperature control device is configured to control the heater 12.
The structure can be used for indirectly controlling the temperature of the heat consumption equipment of the satellite, so that the heat consumption equipment can be kept at normal working temperature in the external low-temperature environment, and the heat consumption equipment can be kept at normal working temperature under the condition of more heat dissipation. The specific temperature control method can be as follows:
when the temperature of the heat consumption equipment is lower than the heating limit, the temperature control equipment controls the heater to be started, the temperature of the heater is conducted to the heat consumption equipment through the heat conduction channel, and the heat consumption equipment is heated to increase the temperature of the heat consumption equipment;
when the temperature of the heat consumption equipment is higher than the heating limit, the temperature control equipment controls the heater to be closed, and the heat consumption equipment is stopped from being heated to reduce the temperature of the heat consumption equipment.
Adopt above-mentioned structure to carry out indirect accuse temperature, can realize under the low temperature mode, the accurate accuse temperature of satellite under-deck heat consumption equipment for example electronic equipment guarantees that it can normally work.
In a preferred embodiment of the present invention, the heater 12 may be disposed between the two outer heat pipes 11.
By adopting the structure, the solar energy heat dissipation device can play a role in supporting and isolating between the satellite solar sailboard and the radiation board through the heater and the outer heat-sticking pipe, can ensure that the temperature of the heater can be quickly conducted to the flexible heat conduction lock through the outer heat-sticking pipe and the radiation board, further conducts to heat dissipation equipment through the heat pipe, avoids heat loss, and realizes high-efficiency utilization of heat and quick adjustment of the temperature of the heat dissipation equipment.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the invention. It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (10)
1. A back side heat dissipation system for a satellite solar sailboard is characterized by comprising: the solar radiation system comprises a coupling plate and a heat conduction path, wherein the coupling plate comprises a satellite solar panel and a radiation plate, and the radiation plate is coupled to the back surface of the satellite solar panel; the heat conduction path communicates the radiation plate and a heat dissipation device mounted on the satellite.
2. The satellite solar panel backside heat dissipation system of claim 1, further comprising a thermal insulation portion disposed between the satellite solar panel backside and the radiation panel.
3. The satellite solar panel backside heat dissipation system of claim 2, wherein the thermal insulation portion includes a first insulation layer and a second insulation layer, the first insulation layer is attached to the backside of the satellite solar panel, the second insulation layer is disposed between the first insulation layer and the radiation plate, and a plurality of gaps are disposed at intervals on the second insulation layer.
4. The satellite solar panel backface cooling system of claim 3, wherein the second insulation layer comprises a first insulation member and a second insulation member, and the first insulation member and the second insulation member are spaced apart, the gap being located between the first insulation member and the second insulation member.
5. The satellite solar panel backside heat dissipation system of claim 4, wherein the first insulation is a polyimide insulation mat, the second insulation is an aerogel insulation, and the first insulation is a low temperature multi-layer insulation assembly.
6. The satellite solar sail panel backside heat dissipation system according to claim 1, wherein the heat dissipation device is mounted on a satellite deck, and the heat conduction path communicates between the radiation panel and a location on the satellite deck where the heat dissipation device is mounted.
7. The satellite solar panel backside heat dissipation system of claim 6, wherein the heat conduction path comprises a heat pipe and a flexible heat conduction lock, the heat pipe is pre-embedded in the satellite deck, one end of the flexible heat conduction lock is disposed on the radiation plate, and the other end of the flexible heat conduction lock is disposed on the satellite deck and connected to the heat pipe.
8. The satellite solar sail panel back side heat dissipation system of claim 7, wherein the flexible heat conducting lock is comprised of copper foil or pyrolytic graphite sheets.
9. The satellite solar panel backside heat dissipation system of claim 7, wherein the heat conduction path further comprises an externally attached heat pipe, the externally attached heat pipe being disposed on the radiation panel.
10. The satellite solar panel backside heat dissipation system of claim 1, further comprising a heater disposed on a side of the radiant panel adjacent to the satellite solar panel and a temperature control device for controlling the heater.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210502991.8A CN114684392A (en) | 2022-05-10 | 2022-05-10 | Back heat dissipation system of satellite solar sailboard |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210502991.8A CN114684392A (en) | 2022-05-10 | 2022-05-10 | Back heat dissipation system of satellite solar sailboard |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114684392A true CN114684392A (en) | 2022-07-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210502991.8A Pending CN114684392A (en) | 2022-05-10 | 2022-05-10 | Back heat dissipation system of satellite solar sailboard |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114684392A (en) |
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2022
- 2022-05-10 CN CN202210502991.8A patent/CN114684392A/en active Pending
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