CN201699483U - Solar power supplying device used for astrovehicle - Google Patents
Solar power supplying device used for astrovehicle Download PDFInfo
- Publication number
- CN201699483U CN201699483U CN2009201740597U CN200920174059U CN201699483U CN 201699483 U CN201699483 U CN 201699483U CN 2009201740597 U CN2009201740597 U CN 2009201740597U CN 200920174059 U CN200920174059 U CN 200920174059U CN 201699483 U CN201699483 U CN 201699483U
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- CN
- China
- Prior art keywords
- astrovehicle
- capacitor
- spacecraft
- solar power
- device used
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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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
- Y02E70/00—Other energy conversion or management systems reducing GHG emissions
- Y02E70/30—Systems combining energy storage with energy generation of non-fossil origin
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- Charge And Discharge Circuits For Batteries Or The Like (AREA)
- Photovoltaic Devices (AREA)
Abstract
The utility model discloses a solar power supplying device used for an astrovehicle, which comprises a large-capacity capacitor and a solar battery. The solar power supplying device used for the astrovehicle is characterized in that: the electric energy generated by the solar battery is used for charging the large-capacity capacitor; the large-capacity capacitor can store a lot of electric energy; after charging is completed, the electric energy stored in the large-capacity capacitor is transmitted to an electric appliance on the astrovehicle through a control switch, in this way, the astrovehicle can normally work relying on energy from the astrovehicle.
Description
Affiliated technical field
The utility model relates to a kind of device that energy can be provided for spacecraft.
Background technology
At present, used energy is that entrained fuel provides when being launched by it on the spacecraft, also there is part to provide by solar cell, but the entrained fuel of spacecraft is limited, can not satisfy long demand, and the energy that solar cell provides is less, can not satisfy the demand of high power device.
Summary of the invention
For overcoming under the existing situation, used energy is that entrained fuel provides when being launched by it on the spacecraft, also there is part to provide by solar cell, but the entrained fuel of spacecraft is limited, can not satisfy long demand, and the energy that solar cell provides is less, can not satisfies the demand deficiency of high power device, the utility model provides a kind of spacecraft solar power supply apparatus, and it can provide lasting and be the bigger energy of power for spacecraft.
The technical scheme that its technical problem that solves the utility model adopts is: capacitor with super capacity and solar cell are installed on spacecraft, the electric energy that utilizes solar cell to produce charges to capacitor with super capacity, can store a large amount of electric energy in the capacitor with super capacity, after charging is finished, give spaceborne electrical appliance the power delivery that capacitor with super capacity stores by control switch, like this, spacecraft just can be by the energy operate as normal that self produces.
The beneficial effects of the utility model are, can fuel savings, reduce the volume of spacecraft, and spacecraft can more stably be worked.
Description of drawings
The utility model is described in further detail below in conjunction with drawings and Examples.
Fig. 1 is that position of the present utility model concerns structural map.
Fig. 2 is each several part annexation figure of the present utility model.
Fig. 3 is a circuit connection diagram of the present utility model.
1. element casees among the figure, 2. base, 3. solar cell, 4. capacitor with super capacity, 5. electrical appliance, 6. power line, 7. control switch.
Embodiment
In Fig. 1, the direct current that solar cell (3) produces provides electric energy by power line (6) to spacecraft element case (1), base (2) is arranged below the element case (1).
In Fig. 2, the direct current that solar cell (3) produces is by capacitor with super capacity (4) charging of power line (6) in the element case, capacitor with super capacity (4) can store a large amount of electric energy, after charging is finished, the electric energy that the transformation of electrical energy that capacitor with super capacity (4) is stored by control switch (7) and power line (6) becomes electrical appliance (5) to use, thus guarantee that spaceborne electrical appliance can operate as normal.
In Fig. 3, to capacitor with super capacity C charging, D1 is anti-adverse current diode to solar cell SR by diode D1, and D2 is a voltage-stabiliser tube, after capacitor with super capacity C was full of electricity, the electric energy that capacitor with super capacity C stores just can use for spaceborne electrical appliance.
Claims (1)
1. spacecraft solar power supply apparatus, it is characterized in that: capacitor with super capacity and solar cell are installed on the spacecraft, the electric energy that solar cell produces charges to capacitor with super capacity, and capacitor with super capacity is given spaceborne electrical appliance the power delivery that stores by control switch.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009201740597U CN201699483U (en) | 2009-08-21 | 2009-08-21 | Solar power supplying device used for astrovehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009201740597U CN201699483U (en) | 2009-08-21 | 2009-08-21 | Solar power supplying device used for astrovehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201699483U true CN201699483U (en) | 2011-01-05 |
Family
ID=43400727
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009201740597U Expired - Fee Related CN201699483U (en) | 2009-08-21 | 2009-08-21 | Solar power supplying device used for astrovehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201699483U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108183513A (en) * | 2017-11-28 | 2018-06-19 | 北京空间技术研制试验中心 | A kind of construction method of spacecraft electric power system |
-
2009
- 2009-08-21 CN CN2009201740597U patent/CN201699483U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108183513A (en) * | 2017-11-28 | 2018-06-19 | 北京空间技术研制试验中心 | A kind of construction method of spacecraft electric power system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110105 Termination date: 20110821 |