CN109178346A - A kind of integrated satellite capsule plate heat-storing device adapting to complicated hot-fluid environment - Google Patents
A kind of integrated satellite capsule plate heat-storing device adapting to complicated hot-fluid environment Download PDFInfo
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- CN109178346A CN109178346A CN201810661553.XA CN201810661553A CN109178346A CN 109178346 A CN109178346 A CN 109178346A CN 201810661553 A CN201810661553 A CN 201810661553A CN 109178346 A CN109178346 A CN 109178346A
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- Prior art keywords
- capsule plate
- phase
- satellite capsule
- covering
- heat
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Classifications
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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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
- F28D20/00—Heat storage plants or apparatus in general; Regenerative heat-exchange apparatus not covered by groups F28D17/00 or F28D19/00
- F28D20/02—Heat storage plants or apparatus in general; Regenerative heat-exchange apparatus not covered by groups F28D17/00 or F28D19/00 using latent heat
-
- 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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- Toxicology (AREA)
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- Environmental & Geological Engineering (AREA)
- Environmental Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Biodiversity & Conservation Biology (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
The present invention provides a kind of integrated satellite capsule plate heat-storing devices for adapting to complicated hot-fluid environment, including covering, fill skeleton, phase-change material, filler line, satellite capsule plate is formed by welding by vacuum brazing with covering in the filling skeleton, the filling skeleton is the filling skeleton with enough voidages, and outer surface is coated with covering, the satellite capsule plate side is welded with the filler line with its internal voids connection, a certain amount of phase-change material is filled in the internal voids of the filling skeleton, the phase-change material is the organic or inorganic material with stable solid-liquid phase change temperature and high latent heat of phase change.The present invention makes satellite capsule plate have metastable temperature, and structure is simple, high reliablity, and the satellite capsule plate under the complicated Orbital heat flux environment shone especially suitable for alternating effectively reduces inside satellite temperature fluctuation, and reduce thermal control resource requirement.
Description
Technical field
The present invention relates to a kind of aircraft thermal control heat-storing devices, and in particular, to a kind of to adapt to the one of complicated hot-fluid environment
Body satellite capsule plate heat-storing device.
Background technique
For low rail inclined plane satellite, is shone in turn on its flight course Satellite surface, lead to its Orbital heat flux condition
Constantly variation, causes whole device heat consumption amplitude of variation big, therefore it is required that satellite thermal control is set simultaneously because the operating mode of satellite is changeable
Meter has very high adaptability.
Usual satellite opens up heat dissipation as section structure plate, and in the relatively small region of Orbital heat flux using aluminum honeycomb panel
Face, the heat extra to dissipation inside satellite.However, with the continuous development of satellite technology and mission requirements, the rail of satellite
Road posture is more and more diversified, load heat consumption is increasing.According to traditional thermal control mode, it is ensured that satellite is under worst hot case
Temperature is unlikely to excessively high, it is necessary to open up sufficiently large cooling surface area.But cooling surface area big under worst cold case can be made again
At big thermal loss, need to consume very big electrical power then to compensate its heat dissipation capacity.In addition, radiating for inclined plane
Face may also be shone, cause can not proper heat reduction or even heat flow backward, cause satellite to be unable to operate normally.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of integrations for adapting to complicated hot-fluid environment to defend
Star deck board heat-storing device effectively reduces in satellite especially suitable for replacing the satellite capsule plate under the complicated Orbital heat flux environment shone
Portion's temperature fluctuation, and reduce thermal control resource requirement.
The invention is realized by the following technical scheme:
A kind of integrated satellite capsule plate heat-storing device adapting to complicated hot-fluid environment, including covering, filling skeleton, phase transformation material
Satellite capsule plate is formed by welding by vacuum brazing in material, filler line, the filling skeleton and covering, and the filling skeleton is with foot
The filling skeleton of enough voidages, and outer surface is coated with covering, the satellite capsule plate side is welded with to be joined with its internal voids
Logical filler line, it is described filling skeleton internal voids in be filled with a certain amount of phase-change material, the phase-change material be with
The organic or inorganic material of stable solid-liquid phase change temperature and high latent heat of phase change, phase transition process is simply reversible, only by temperature because
Element influences.
Preferably, the voidage of the filling skeleton is not less than 85%, and all gaps interconnect, and hole can be selected
The aluminum metal foam of gap rate 85%.
Preferably, the material of the filling skeleton is aluminium and aluminium alloy or high-heat conductivity graphite material.
Preferably, the material of the covering is aluminium alloy.
Preferably, the phase-change material is n-octadecane, and transformation temperature is 28 DEG C, and latent heat of phase change is 343kJ/ (kgK)
Preferably, the covering is the lead-covering of 0.3mm thickness.
Compared with prior art, the invention has the following advantages: the present invention uses the phase transformation with high latent heat of phase change
Material realizes " peak load shifting " of satellite Orbital heat flux and interior power consumption.Under worst hot case, phase-change material occurs solid-liquid phase change and absorbs
Amount of heat effectively prevent satellite and loading temperature excessively high；Under worst cold case, it is a large amount of that liquid-solid phase transformation release occurs for phase-change material
Heat, to guarantee that satellite and loading temperature are unlikely to too low.Using the filling skeleton of highly heat-conductive material, effectively improve deck board etc.
Thermal coefficient is imitated, the utilization rate of phase-change material is improved.Using thin lead-covering, heat transmission thermal resistance is reduced, system is improved
Heat transfer efficiency.It is welded between covering and filling skeleton using vacuum brazing, reduces thermal contact resistance, improve system heat transfer effect
Rate.The integration heat-storing device, structure is simple, high reliablity, under the complicated Orbital heat flux environment shone especially suitable for alternating
Satellite capsule plate effectively reduces inside satellite temperature fluctuation, and reduces thermal control resource requirement.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is the structural representation for the integrated satellite capsule plate heat-storing device that the embodiment of the present invention adapts to complicated hot-fluid environment
Figure.
Fig. 2 is the cross section signal for the integrated satellite capsule plate heat-storing device that the embodiment of the present invention adapts to complicated hot-fluid environment
Figure.
Fig. 3 is the curve that single machine temperature changes over time under Legacy Status.
Fig. 4 is the curve that single machine temperature changes over time after implementing the present invention.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
As depicted in figs. 1 and 2, the embodiment of the invention provides a kind of integrated satellite capsule plates for adapting to complicated hot-fluid environment
Heat-storing device, including covering 1, filling skeleton 2, phase-change material 3, filler line 4, the filling skeleton 2 pass through vacuum pricker with covering 1
Satellite capsule plate is formed by welding, the filling skeleton 2 is the filling skeleton with enough voidages, and outer surface is coated with covering
1, the satellite capsule plate side is provided with filler line 4, the internal voids connection of filler line 4 and filling skeleton 2, the filling skeleton
Be filled with a certain amount of phase-change material in 2 internal voids, the phase-change material 3 be with stable solid-liquid phase change temperature and
The organic or inorganic material of high latent heat of phase change, phase transition process is simply reversible, is only influenced by temperature factor.The covering 1 is
The lead-covering of 0.3mm thickness；The filling skeleton is the aluminum metal foam of porosity 85%, and the phase-change material 3 is n-octadecane.
This specific implementation is processed by following steps:
S1, the satellite capsule plate that covering 1 and filling skeleton 2 are used to being welded as a whole of Vacuum Soldering Technology, need to guarantee to cover
Skin 1 and filling 2 good fit of skeleton, to reduce covering 1 and fill the thermal contact resistance between skeleton 2；
S2, in the aperture of resulting satellite capsule plate side, and weld filler line 4, all welding require to guarantee leakproofness and
Resistance to pressure, being sealed property and resistance to pressure detection test after the completion of welding, to guarantee that phase-change material will not leak；
S3, the integrated satellite capsule plate heat-storing device that phase-change material 3 is adapted to complicated hot-fluid environment by the injection of filler line 4
In；Specifically, phase-change material 3 and the satellite capsule plate being welded all are heated to the phase transition temperature of phase-change material 3 or more first, protect
The mobility that phase-change material 3 is liquid and has had is demonstrate,proved, then will be vacuumized inside satellite capsule plate, by the way of external pressurized
Liquid state phase change material 3 is injected in satellite capsule plate；
S4, the cold welding tong of filler line 4 is clamped to shutdown, then the opening of filler line 4 is blocked by welding, guarantee will not occur
Leakage situation.
Under traditional design state, it is very big that single machine temperature changes over time amplitude, as shown in Figure 3.In order to guarantee it in high temperature
Temperature when state is unlikely to need to open bigger radiating surface beyond temperature index.And when worst cold case, need bigger electric work
The excessive radiation loss of rate heating compensation.Cause to consume a large amount of electrical power, satellite weight and the excessive of power consumption resource is caused to disappear
Consumption.After constructional device of the invention, single machine temperature changes over time amplitude and is obviously reduced, as shown in Figure 4.Due to phase transformation material
The latent heat heat accumulation characteristic of material 3, under worst hot case, the fusing heat absorption of phase-change material 3 absorbs under temperature constant state and stores single machine certainly
Body waste heat and Orbital heat flux flow backward heat, to guarantee that single machine temperature under worst hot case is unlikely to excessively high；Under worst cold case, phase
Become material 3 and solidify heat release, heat is discharged under temperature constant state, the heat dissipation capacity of radiating surface is balanced to a certain extent, to guarantee
Single machine temperature is unlikely to be greatly reduced.In conclusion as shown in figure 4, single machine temperature changes over time amplitude after implementing the present invention
It is obviously reduced, and then can reduce heat control system for the demand of cooling surface area and compensation electrical power consumed, reduce the weight of satellite
With power consumption scale.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.
Claims (6)
1. a kind of integrated satellite capsule plate heat-storing device for adapting to complicated hot-fluid environment, it is characterised in that: including covering (1), fill out
Skeleton (2), phase-change material (3), filler line (4) are filled, the filling skeleton (2) is formed by welding with covering (1) by vacuum brazing
Satellite capsule plate, filling skeleton (2) is the filling skeleton with enough voidages, and outer surface is coated with covering (1), described
Satellite capsule plate side is welded with the filler line (4) with its internal voids connection, fills out in the internal voids of filling skeleton (2)
Filled with a certain amount of phase-change material, the phase-change material (3) is having with stable solid-liquid phase change temperature and high latent heat of phase change
Machine or inorganic material.
2. the integrated satellite capsule plate heat-storing device according to claim 1 for adapting to complicated hot-fluid environment, it is characterised in that:
The voidage of the filling skeleton (2) is not less than 85%, and all gaps interconnect.
3. the integrated satellite capsule plate heat-storing device according to claim 1 for adapting to complicated hot-fluid environment, it is characterised in that:
The material of the filling skeleton (2) is aluminium and aluminium alloy or high-heat conductivity graphite material.
4. the integrated satellite capsule plate heat-storing device according to claim 1 for adapting to complicated hot-fluid environment, it is characterised in that:
The material of the covering (1) is aluminium alloy.
5. the integrated satellite capsule plate heat-storing device according to claim 1 for adapting to complicated hot-fluid environment, it is characterised in that:
The phase-change material (3) is n-octadecane.
6. the integrated satellite capsule plate heat-storing device according to claim 4 for adapting to complicated hot-fluid environment, it is characterised in that:
The covering (1) is the lead-covering of 0.3mm thickness.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810661553.XA CN109178346A (en) | 2018-06-25 | 2018-06-25 | A kind of integrated satellite capsule plate heat-storing device adapting to complicated hot-fluid environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810661553.XA CN109178346A (en) | 2018-06-25 | 2018-06-25 | A kind of integrated satellite capsule plate heat-storing device adapting to complicated hot-fluid environment |
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| Publication Number | Publication Date |
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| CN109178346A true CN109178346A (en) | 2019-01-11 |
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| CN201810661553.XA Pending CN109178346A (en) | 2018-06-25 | 2018-06-25 | A kind of integrated satellite capsule plate heat-storing device adapting to complicated hot-fluid environment |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111806730A (en) * | 2020-06-02 | 2020-10-23 | 上海利正卫星应用技术有限公司 | Phase change radiator |
| CN111934744A (en) * | 2020-07-30 | 2020-11-13 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Relay satellite rocket-borne user terminal system equipment |
| CN113581493A (en) * | 2021-07-30 | 2021-11-02 | 北京微焓科技有限公司 | Plate-shaped satellite main frame and plate-shaped satellite |
| CN113911400A (en) * | 2021-11-02 | 2022-01-11 | 之江实验室 | Heat storage device of micro-nano satellite system |
Citations (4)
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| CN103010318A (en) * | 2011-09-26 | 2013-04-03 | 蓝星(北京)化工机械有限公司 | Cold storage and thermoregulation carriage, and manufacturing method and application thereof |
| CN104354879A (en) * | 2014-10-17 | 2015-02-18 | 上海利正卫星应用技术有限公司 | Low-flow-resistance energy storage type efficient radiator |
| CN204651303U (en) * | 2015-05-25 | 2015-09-16 | 新乡市特美特换热设备有限公司 | A kind of electronic element radiating cold drawing |
| CN207006955U (en) * | 2017-05-26 | 2018-02-13 | 北京空间飞行器总体设计部 | A kind of phase change device that can quickly fill |
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2018
- 2018-06-25 CN CN201810661553.XA patent/CN109178346A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103010318A (en) * | 2011-09-26 | 2013-04-03 | 蓝星(北京)化工机械有限公司 | Cold storage and thermoregulation carriage, and manufacturing method and application thereof |
| CN104354879A (en) * | 2014-10-17 | 2015-02-18 | 上海利正卫星应用技术有限公司 | Low-flow-resistance energy storage type efficient radiator |
| CN204651303U (en) * | 2015-05-25 | 2015-09-16 | 新乡市特美特换热设备有限公司 | A kind of electronic element radiating cold drawing |
| CN207006955U (en) * | 2017-05-26 | 2018-02-13 | 北京空间飞行器总体设计部 | A kind of phase change device that can quickly fill |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111806730A (en) * | 2020-06-02 | 2020-10-23 | 上海利正卫星应用技术有限公司 | Phase change radiator |
| CN111934744A (en) * | 2020-07-30 | 2020-11-13 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Relay satellite rocket-borne user terminal system equipment |
| CN111934744B (en) * | 2020-07-30 | 2022-04-01 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Relay satellite rocket-borne user terminal system equipment |
| CN113581493A (en) * | 2021-07-30 | 2021-11-02 | 北京微焓科技有限公司 | Plate-shaped satellite main frame and plate-shaped satellite |
| CN113911400A (en) * | 2021-11-02 | 2022-01-11 | 之江实验室 | Heat storage device of micro-nano satellite system |
| CN113911400B (en) * | 2021-11-02 | 2022-12-09 | 之江实验室 | Heat storage device of micro/nano satellite system |
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Application publication date: 20190111 |