CN106208814A - A kind of method utilizing satellite external surface thermograde to carry out generating electricity - Google Patents
A kind of method utilizing satellite external surface thermograde to carry out generating electricity Download PDFInfo
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- CN106208814A CN106208814A CN201610827913.XA CN201610827913A CN106208814A CN 106208814 A CN106208814 A CN 106208814A CN 201610827913 A CN201610827913 A CN 201610827913A CN 106208814 A CN106208814 A CN 106208814A
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- thermal insulation
- insulation layer
- satellite
- external surface
- heat
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02N—ELECTRIC MACHINES NOT OTHERWISE PROVIDED FOR
- H02N11/00—Generators or motors not provided for elsewhere; Alleged perpetua mobilia obtained by electric or magnetic means
- H02N11/002—Generators
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- Compositions Of Macromolecular Compounds (AREA)
- Photovoltaic Devices (AREA)
Abstract
This disclosure of the invention is a kind of utilizes the satellite external surface thermograde to carry out the device generated electricity, and belongs to thermoelectric generation and applies in spacecraft thermal control field.This device includes: be covered on the first thermal insulation layer of satellite external surface, the heat-conducting layer being covered on the first thermal insulation layer, the second thermal insulation layer being covered on heat-conducting layer, the second thermal insulation layer the body dress solar panel of formula arranged, the thermo-electric device being embedded in the second thermal insulation layer, the energy collection circuit of connection heat-transfer device；All being inlaid with thermo-electric device in the second thermal insulation layer below described each piece of solar panel, each thermo-electric device one end connects the solar panel other end and connects heat-conducting layer.This method utilizing satellite external surface thermograde to carry out generating electricity, the source of satellite energy can not only be increased, the temperature of satellite sunny slope can also be reduced, reduce the temperature fluctuation of satellite external surface, reduce the temperature impact on the solar panel work efficiency of body dress formula.The method has good application prospect on moonlet.
Description
Technical field
The invention belongs to thermoelectric generation apply in spacecraft thermal control field.
Background technology
After entering 21 century, present satellite gradually presents its lightweight, miniaturization, low cost and high functional density and property
The advantages such as valency ratio, are developed rapidly and extensively apply, and it has become the important component part of space system now.
The sunny slope of satellite temperature under strong solar radiation is higher, and opaco is not owing to having solar radiation to shine
Penetrate, its temperature can ratio relatively low.The too high temperature of satellite external surface can affect the work efficiency of solar panel, and the temperature of whole star
Spend uneven meeting and cause the thermal deformation of satellite structure, affect the precision of high-precision equipment in star.
Owing to moonlet volume is little, thermal capacitance is little, run track also ratio relatively low, when its frequently turnover earth's shadow district, meeting
Cause satellite surface temperature fluctuation excessive, easily affect the normal operating conditions of equipment in star, increase satellite thermal control system
Design difficulty.
Summary of the invention
In order to solve the problem that moonlet hull-skin temperature difference is excessive, temperature fluctuation is bigger, and increase coming of satellite energy
Source, the present invention proposes and a kind of utilizes satellite external surface thermograde to carry out the method generated electricity, is especially suitable for applying at moonlet
On, such as micro-, Nano satellite.
To achieve these goals, the technical solution adopted in the present invention is:
A kind of satellite external surface thermograde is utilized to carry out the device generated electricity, it is characterised in that this device includes: be covered in
First thermal insulation layer of satellite external surface, the heat-conducting layer being covered on the first thermal insulation layer, the second thermal insulation layer being covered on heat-conducting layer,
The body dress solar panel of formula arranged on second thermal insulation layer, the thermo-electric device being embedded in the second thermal insulation layer, connection heat conduction
The energy collection circuit of device；Thermo-electric device all it is inlaid with in the second thermal insulation layer below described each piece of solar panel,
Each thermo-electric device one end connects the solar panel other end and connects heat-conducting layer.
Preferably, described thermo-electric device (2) uses low-temperature zone thermoelectric material to make, and its P, N arm cross-sectional area is little, PN junction
Logarithm is many.
Preferably, described heat-conducting layer (4) material is foamy carbon.
Beneficial effects of the present invention: this utilize satellite external surface thermograde to carry out the method generated electricity, can not only increase
Add the source of satellite energy, additionally it is possible to reduce the temperature of satellite sunny slope, reduce the temperature fluctuation of satellite external surface, reduce temperature
Impact on the solar panel work efficiency of body dress formula.The method has good application prospect on moonlet.
Accompanying drawing explanation
Fig. 1 is the present invention schematic three dimensional views with cube satellite as objective for implementation.
Fig. 2 is the present invention floor map with cube satellite as objective for implementation.
Fig. 3 is the mounting structure explosive view on a present invention face with cube satellite as objective for implementation.
Fig. 4 is the schematic diagram of the energy collection circuit module of the present invention.
Detailed description of the invention
Below in conjunction with the accompanying drawings to a kind of method utilizing satellite external surface thermograde to generate electricity that the present invention provides
Detailed description of the invention elaborates.
The present invention towards object be moonlet, in this article as a example by cube satellite.At cube satellite six
Being respectively mounted micro thermoelectric device on face, five faces (in addition near the ground) of its Satellite have the solar panel of body dress formula,
Near the ground be provided with heat sink.
Being the present invention schematic three dimensional views with cube satellite as objective for implementation shown in Fig. 1, six faces of satellite are all defended
Star thermo-electric device.Schematic diagram only puts a thermo-electric device for each, and actual according to the size of satellite, multiple heat can be installed
Electrical part.
It is the present invention floor map with cube satellite as objective for implementation shown in Fig. 2, is a face shown in accompanying drawing 3
Structural blast figure.Shown construction package includes that body fills the solar panel 1 of formula, thermo-electric device the 2, second thermal insulation layer 3, heat conduction
Layer 4 and the first thermal insulation layer 5.Described thermo-electric device 2 is embedded in the second thermal insulation layer 3, and one face is close to by heat-conducting silicone grease
On the solar panel of body dress formula, another face is close on high-performance heat-conducting layer 4 by heat-conducting silicone grease.Insulating assembly 5
The heat being mainly used to block satellite surface is delivered to inside satellite.
Thermo-electric device 2 in Fig. 2 uses the thermoelectric material of low-temperature zone high zt to make, and the ceramic wafer at thermo-electric device two ends is adopted
(such as AlN, its thermal conductivity is Al to the material higher by thermal conductivity2O3More than 5 times).
High thermal conductivity layer 4 in Fig. 3 mainly uses the new material that thermal conductivity is high, density is little, specific heat capacity is big to make, such as foam
Carbon.
Fig. 4 is the schematic diagram of the energy collection circuit module of present aspect, uses TPS61200, LTC3109 etc. in this module
Boost chip, it is possible to the voltage that micro thermoelectric device exports is raised to the charging voltage of accumulator, directly charges a battery.
Above-mentioned is to be shown and described with cube satellite for embodiment, but the embodiment of patent of the present invention is also
It is not restricted to the described embodiments, as long as it reaches the technique effect of patent of the present invention with essentially identical means, all should belong to
The protection domain of patent of the present invention.
Claims (3)
1. one kind utilizes satellite external surface thermograde to carry out the device generated electricity, it is characterised in that this device includes: is covered in and defends
First thermal insulation layer of star outer surface, the heat-conducting layer being covered on the first thermal insulation layer, the second thermal insulation layer being covered on heat-conducting layer,
The body dress solar panel of formula arranged on two thermal insulation layers, the thermo-electric device being embedded in the second thermal insulation layer, connection conducting heat
The energy collection circuit of part；Thermo-electric device all it is inlaid with, respectively in the second thermal insulation layer below described each piece of solar panel
Thermo-electric device one end connects the solar panel other end and connects heat-conducting layer.
A kind of satellite external surface thermograde is utilized to carry out the device generated electricity, it is characterised in that institute
The thermo-electric device (2) stated uses low-temperature zone thermoelectric material to make, and its P, N arm cross-sectional area is little, and PN junction logarithm is many.
A kind of satellite external surface thermograde is utilized to carry out the device generated electricity, it is characterised in that institute
Heat-conducting layer (4) material stated is foamy carbon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610827913.XA CN106208814B (en) | 2016-09-18 | 2016-09-18 | A kind of device to be generated electricity using satellite external surface temperature gradient |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610827913.XA CN106208814B (en) | 2016-09-18 | 2016-09-18 | A kind of device to be generated electricity using satellite external surface temperature gradient |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106208814A true CN106208814A (en) | 2016-12-07 |
| CN106208814B CN106208814B (en) | 2019-04-05 |
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ID=58067379
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610827913.XA Expired - Fee Related CN106208814B (en) | 2016-09-18 | 2016-09-18 | A kind of device to be generated electricity using satellite external surface temperature gradient |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148248A (en) * | 2021-06-02 | 2021-07-23 | 北京理工大学 | Space environment simulation platform and method for artificial satellite thermoelectric power generation system |
| WO2023038100A1 (en) * | 2021-09-10 | 2023-03-16 | 株式会社Ｇｃｅインスティチュート | Environmental power generation device and environmental power generation system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101572515A (en) * | 2009-05-26 | 2009-11-04 | 广东富信电子科技有限公司 | Generating device |
| CN102437212A (en) * | 2011-11-22 | 2012-05-02 | 北京航空航天大学 | Photoelectric-thermoelectric integrated battery pack |
| CN203071070U (en) * | 2012-12-26 | 2013-07-17 | 中国电子科技集团公司第十八研究所 | Composite power supply of solar cell-thermoelectric cell |
| US20150083196A1 (en) * | 2013-09-25 | 2015-03-26 | Prime Photonics, Lc | Magneto-thermoelectric generator for energy harvesting |
-
2016
- 2016-09-18 CN CN201610827913.XA patent/CN106208814B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101572515A (en) * | 2009-05-26 | 2009-11-04 | 广东富信电子科技有限公司 | Generating device |
| CN102437212A (en) * | 2011-11-22 | 2012-05-02 | 北京航空航天大学 | Photoelectric-thermoelectric integrated battery pack |
| CN203071070U (en) * | 2012-12-26 | 2013-07-17 | 中国电子科技集团公司第十八研究所 | Composite power supply of solar cell-thermoelectric cell |
| US20150083196A1 (en) * | 2013-09-25 | 2015-03-26 | Prime Photonics, Lc | Magneto-thermoelectric generator for energy harvesting |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148248A (en) * | 2021-06-02 | 2021-07-23 | 北京理工大学 | Space environment simulation platform and method for artificial satellite thermoelectric power generation system |
| WO2023038100A1 (en) * | 2021-09-10 | 2023-03-16 | 株式会社Ｇｃｅインスティチュート | Environmental power generation device and environmental power generation system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106208814B (en) | 2019-04-05 |
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Granted publication date: 20190405 Termination date: 20210918 |