CN113911400B - Heat storage device of micro/nano satellite system - Google Patents
Heat storage device of micro/nano satellite system Download PDFInfo
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- CN113911400B CN113911400B CN202111286280.3A CN202111286280A CN113911400B CN 113911400 B CN113911400 B CN 113911400B CN 202111286280 A CN202111286280 A CN 202111286280A CN 113911400 B CN113911400 B CN 113911400B
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- storage bin
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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
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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
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/14—Thermal energy storage
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Abstract
The invention relates to the technical field of satellite thermal control, in particular to a heat storage device of a micro-nano satellite system, which comprises an outer shell formed by satellite side plates and a satellite bottom plate, and a cylinder, a piston, a heat storage bin, a spring and a heat insulation plate which are arranged in the outer shell; the piston is arranged in the cylinder to form a closed space, gas is filled in the closed space, and the piston moves up and down along the wall of the cylinder; the piston is in an inverted T shape, and the neck end of the piston is fixedly connected with the heat storage bin; a first heat conducting unit is embedded in the satellite side plate; a second heat conduction unit is embedded in the satellite bottom plate and connected with the bottom of the cylinder; the heat insulation plates are fixedly arranged on two sides of the heat storage bin and are in sliding fit with the inner walls of the satellite side plates; and two ends of the spring are respectively connected with the satellite bottom plate and the heat storage bin. The invention weakens the temperature change in the satellite, does not need additional energy supply, saves the energy consumption and ensures the normal operation of the low-temperature environment of the satellite system.
Description
Technical Field
The invention relates to the technical field of satellite thermal control, in particular to a heat storage device of a micro/nano satellite system.
Background
Due to the rapid development of microelectronic integration technology, the size and mass of the satellite can be made smaller and smaller. Satellites with a mass of less than 10kg are called micro-nano satellites, which are generally small and consume a lot of power. The satellite outer plate heat insulation technology can ensure stable temperature inside the satellite, but for the micro-nano satellite with large volume heat flux density, the heat insulation outer plate can lead internal heat to be gathered to cause overheating. If the heat insulation performance is reduced for heat dissipation, when the satellite is positioned in a solar eclipse area, heat can be quickly dissipated, and the temperature is too low, so that the work is abnormal.
For the low-temperature protection of the on-orbit satellite, one measure is to use an electric heating sheet, and the electric heating sheet is opened when the temperature is too low, so that the electric energy is converted into heat energy to ensure the normal work of the satellite. The problem with this approach is that the electrical load is increased and the battery capacity may be insufficient.
Disclosure of Invention
In order to solve the technical problems in the prior art, the invention provides a heat storage device of a micro/nano satellite system, which is used for transferring heat in the daytime to night only through energy transfer without energy conversion so as to realize temperature control, and the specific technical scheme is as follows:
a heat storage device of a micro/nano satellite system comprises an outer shell formed by a satellite side plate and a satellite bottom plate, and a cylinder, a piston, a heat storage bin, a spring and a heat insulation plate which are arranged in the outer shell; the piston is arranged in the cylinder to form a closed space, gas is filled in the closed space, and the piston moves up and down along the wall of the cylinder; the piston is in an inverted T shape, and the neck end of the piston is fixedly connected with the heat storage bin; a first heat conduction unit is embedded in the satellite side plate; a second heat conduction unit is embedded in the satellite bottom plate and connected with the bottom of the cylinder; the heat insulation plates are fixedly arranged on two sides of the heat storage bin and are in sliding fit with the inner walls of the satellite side plates; and two ends of the spring are respectively connected with the satellite bottom plate and the heat storage bin.
Preferably, the top of the cylinder is provided with an opening, and the opening is smaller than the head of the piston and larger than the neck of the piston.
Preferably, the gas is helium, when the helium shrinks in the case of cooling, the piston moves to the lowest end to form a first limit, when the helium expands in the case of heating, the piston moves to the highest end to form a second limit, and the spring is in a stretching state.
Preferably, the height of the heat insulation plate is not less than that of the first heat conduction unit, and when the device is positioned at a first limit position, the heat insulation plate completely shields the heat conduction unit.
Preferably, the height of the heat storage bin is not less than that of the first heat conduction unit, and when the device is positioned at the second limit position, the side face of the heat storage bin is completely connected with the first heat conduction unit.
Preferably, the heat storage bin is composed of a shell and heat storage filler, the shell is made of heat conduction materials, and the heat storage filler is paraffin.
Preferably, the shell of the cylinder, the shell of the heat storage bin, the satellite side plate and the satellite bottom plate are all made of heat conduction materials comprising copper and aluminum; the satellite side plates and the satellite bottom plate are filled with heat insulation layers, and the heat insulation layers and the heat insulation plates are made of multiple layers of heat insulation materials MLI.
The invention is used for reducing the influence of the day and night temperature difference of the environment outside the satellite on the internal temperature: the temperature is high in the daytime, the gas in the cylinder is thermally expanded to push the heat storage bin to rise, and the side surface of the heat storage bin is in contact with the heat conduction unit to form a heat path to absorb external heat; the temperature is low at night, the gas shrinks, the heat storage bin returns to the original position, the heat path is disconnected, and the heat is stored.
The invention has the beneficial effects that:
(1) The functions of heat absorption in a high-temperature environment and heat preservation and heat release in a low-temperature environment are realized, and the temperature change in the satellite is weakened.
(2) The effect is achieved by changing the heat path by means of expansion with heat and contraction with cold of gas, additional energy supply is not needed, and energy consumption is saved.
(3) The heat storage material is used for transferring the illumination heat energy in the daytime to the use when no illumination is available at night, so that the normal operation of the system in the satellite in the low-temperature environment is ensured, and no extra electric energy is consumed.
Drawings
FIG. 1 is a schematic view of the first position limiting device of the present invention;
FIG. 2 is a schematic view of the structure of the device of the present invention when the second limit is formed;
in the figure, 1-cylinder, 2-piston, 3-heat storage bin, 4-spring, 5-satellite side plate, 6-satellite bottom plate, 7-heat insulation plate, 8-first heat conduction unit, 9-second heat conduction unit and 10-gas.
Detailed Description
In order to make the objects, technical solutions and technical effects of the present invention more clearly apparent, the present invention is further described in detail below with reference to the accompanying drawings and examples.
The heat storage device of the micro/nano satellite system comprises a cylinder 1, a piston 2, a heat storage bin 3, a spring 4, a satellite side plate 5, a satellite bottom plate 6 and a heat insulation plate 7, and is in a state of a low-temperature environment outside a satellite as shown in figure 1, and is in a state of a high-temperature environment outside the satellite as shown in figure 2. The satellite side plate 5 and the satellite bottom plate 6 are made of aluminum, are respectively embedded with a first heat conduction unit 8 and a second heat conduction unit 9, and are filled with heat insulation layers which are made of multilayer heat insulation materials MLI. The second heat conducting unit 9 of the satellite bottom plate 6 is connected with the cylinder 1, the cylinder 1 is made of aluminum and has good heat conduction with the satellite bottom plate 6, the gas 10 filled inside is affected by temperature, expands with heat and contracts with cold, and the gas 10 can be helium. The outside parcel insulating layer of cylinder 1, cylinder 1 highly is greater than the piston 2 height, and piston 2 forms first spacing when moving to the lower extreme. The top of the cylinder 1 is provided with an opening, the diameter of the opening is smaller than the head of the piston 2 and larger than the neck of the piston, the piston 2 is prevented from falling out of the cylinder 1 after the expansion of the gas 10 in the cylinder 1, and the piston 2 forms a second limit when moving to the uppermost end. The piston 2 is made of poor heat conduction material, such as glass, silica gel and the like. The neck of the piston 2 is connected with the heat storage bin 3, so that the piston moves synchronously. The shell of the heat storage bin 3 is made of aluminum, a heat insulation layer is wrapped outside the shell, and paraffin is filled in the bin. An insulating plate 7 is fixed on the heat storage bin 3, and when the device is positioned at a first limit position, the insulating plate 7 just blocks a first heat conduction unit 8 of the satellite side plate 5. A spring 4 is arranged between the satellite bottom plate 6 and the heat storage bin 3, and the heat storage bin 3 is pulled back to the first limit from the second limit along with the temperature reduction.
One cycle of in-orbit operation of the satellite is divided into a solar irradiation phase and a solar eclipse phase without solar irradiation. In the irradiation stage, the temperature of the satellite bottom plate 6 absorbing solar radiation rises, heat is sequentially transmitted to the gas 10 through the second heat conduction unit 9 and the cylinder 1, the heated volume of the gas 10 expands to increase the pressure borne by the piston 2, when the pressure is greater than the tensile force of the spring 4, the piston 2 pushes the heat storage bin 3 to move upwards until the stress is balanced, at the moment, the device is located in the second limit position, as shown in fig. 2, the heat storage bin 3 and the first heat conduction unit 8 form a heat passage, the heat of the solar radiation absorbed by the satellite side plate 5 enters the heat storage bin 3, a large amount of heat can be absorbed by paraffin in the bin through phase change, the state is maintained until the satellite enters the solar food stage, no solar radiation exists, the temperature of the outer plate is rapidly reduced, the pressure borne by the gas 10 is reduced, the spring 4 pulls the heat storage bin 3 back, and the device returns to the first limit position. At this time, the heat insulation plate 7 fixed above the heat storage bin 3 just covers the heat conduction unit 8, so that a heat path is blocked, and heat is stored. The paraffin in the heat storage bin 3 slowly releases heat through phase change, and the intra-satellite environment temperature is not lower than the lower limit of the normal working temperature.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way. Although the foregoing has described in detail the practice of the invention, it will be appreciated by those skilled in the art that variations may be applied to the embodiments described in the foregoing examples, or equivalents may be substituted for elements thereof. All changes, equivalents and modifications which come within the spirit and scope of the invention are desired to be protected.
Claims (7)
1. The heat storage device of the micro/nano satellite system is characterized by comprising an outer shell formed by a satellite side plate (5) and a satellite bottom plate (6), and a cylinder (1), a piston (2), a heat storage bin (3), a spring (4) and a heat insulation plate (7) which are arranged in the outer shell; the piston (2) is arranged in the cylinder (1) to form a closed space, gas (10) is filled in the closed space, and the piston (2) moves up and down along the wall of the cylinder (1); the piston (2) is in an inverted T shape, and the neck end of the piston (2) is fixedly connected with the heat storage bin (3); a first heat conduction unit (8) is embedded in the satellite side plate (5); a second heat conduction unit (9) is embedded in the satellite bottom plate (6), and the second heat conduction unit (9) is connected with the bottom of the cylinder (1); the heat insulation plates (7) are fixedly arranged on two sides of the heat storage bin (3) and are attached to the inner wall of the satellite side plate (5) in a sliding manner; and two ends of the spring (4) are respectively connected with the satellite bottom plate (6) and the heat storage bin (3).
2. The heat storage device of a micro-nano satellite system according to claim 1, wherein an opening is formed in the top of the cylinder (1), and the opening is smaller than the head of the piston (2) and larger than the neck of the piston.
3. The heat storage device of a micro-nano satellite system according to claim 2, wherein the gas (10) is helium, when the helium shrinks under cooling, a first limit is formed when the piston (2) moves to the lowest end, when the helium expands under heating, a second limit is formed when the piston (2) moves to the highest end, and the spring (4) is in a stretching state.
4. The heat storage device of a micro/nano satellite system according to claim 3, wherein the height of the heat insulation plate (7) is not less than that of the first heat conduction unit (8), and when the device is positioned at a first limit position, the heat insulation plate (7) completely shields the first heat conduction unit (8).
5. The heat storage device of a micro-nano satellite system according to claim 3, wherein the height of the heat storage bin (3) is not less than that of the first heat conducting unit (8), and when the device is located at the second limit position, the side surface of the heat storage bin (3) is completely connected with the first heat conducting unit (8).
6. The heat storage device of the micro-nano satellite system according to claim 1, wherein the heat storage bin (3) is composed of a shell and heat storage filler, the shell is made of heat conduction material, and the heat storage filler is paraffin.
7. The heat storage device of the micro-nano satellite system according to claim 1, wherein the shell of the cylinder (1), the shell of the heat storage bin (3), the satellite side plate (5) and the satellite bottom plate (6) are all made of heat conducting materials comprising copper and aluminum; the satellite side plates (5) and the satellite bottom plate (6) are filled with heat insulation layers, and the heat insulation layers and the heat insulation plates (7) are made of multiple layers of heat insulation materials MLI.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111286280.3A CN113911400B (en) | 2021-11-02 | 2021-11-02 | Heat storage device of micro/nano satellite system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111286280.3A CN113911400B (en) | 2021-11-02 | 2021-11-02 | Heat storage device of micro/nano satellite system |
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| Publication Number | Publication Date |
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| CN113911400A CN113911400A (en) | 2022-01-11 |
| CN113911400B true CN113911400B (en) | 2022-12-09 |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04163298A (en) * | 1990-10-26 | 1992-06-08 | Hitachi Ltd | Temperature control mechanism for electronic device mounted on artificial satellite and spacecraft |
| CN102200072A (en) * | 2009-07-22 | 2011-09-28 | 徐志平 | Solar and chemical energy external heat composite helium cycle engine |
| CN104803011A (en) * | 2015-05-12 | 2015-07-29 | 东南大学 | Lunar vehicle temperature control system |
| CN109178346A (en) * | 2018-06-25 | 2019-01-11 | 上海卫星工程研究所 | A kind of integrated satellite capsule plate heat-storing device adapting to complicated hot-fluid environment |
| CN109703788A (en) * | 2018-12-13 | 2019-05-03 | 航天东方红卫星有限公司 | A kind of isothermal thermal controls apparatus being suitable for micro-nano satellite based on graphene and copper bar |
| CN110274503A (en) * | 2019-06-27 | 2019-09-24 | 北京无线电测量研究所 | A kind of phase-change energy storage device |
| CN211782959U (en) * | 2019-11-28 | 2020-10-27 | 中国航空工业集团公司西安航空计算技术研究所 | Pressure overload protection's phase transition heat-retaining plate |
-
2021
- 2021-11-02 CN CN202111286280.3A patent/CN113911400B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04163298A (en) * | 1990-10-26 | 1992-06-08 | Hitachi Ltd | Temperature control mechanism for electronic device mounted on artificial satellite and spacecraft |
| CN102200072A (en) * | 2009-07-22 | 2011-09-28 | 徐志平 | Solar and chemical energy external heat composite helium cycle engine |
| CN104803011A (en) * | 2015-05-12 | 2015-07-29 | 东南大学 | Lunar vehicle temperature control system |
| CN109178346A (en) * | 2018-06-25 | 2019-01-11 | 上海卫星工程研究所 | A kind of integrated satellite capsule plate heat-storing device adapting to complicated hot-fluid environment |
| CN109703788A (en) * | 2018-12-13 | 2019-05-03 | 航天东方红卫星有限公司 | A kind of isothermal thermal controls apparatus being suitable for micro-nano satellite based on graphene and copper bar |
| CN110274503A (en) * | 2019-06-27 | 2019-09-24 | 北京无线电测量研究所 | A kind of phase-change energy storage device |
| CN211782959U (en) * | 2019-11-28 | 2020-10-27 | 中国航空工业集团公司西安航空计算技术研究所 | Pressure overload protection's phase transition heat-retaining plate |
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| CN113911400A (en) | 2022-01-11 |
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