CN200981645Y - Power supply and stretching mechanism for simple moonlet - Google Patents
Power supply and stretching mechanism for simple moonlet Download PDFInfo
- Publication number
- CN200981645Y CN200981645Y CN 200620002172 CN200620002172U CN200981645Y CN 200981645 Y CN200981645 Y CN 200981645Y CN 200620002172 CN200620002172 CN 200620002172 CN 200620002172 U CN200620002172 U CN 200620002172U CN 200981645 Y CN200981645 Y CN 200981645Y
- Authority
- CN
- China
- Prior art keywords
- power supply
- moonlet
- utility
- gravity gradient
- model
- 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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Abstract
An extending device of the power supply and the gravity gradient rod of the moonlet is characterized in that the utility model can integrate a solar battery square array and a gravity gradient rod as a whole, thereby saving the cost and advancing the reliability, especially applicable for the teenager amateur to design and produce according to the present conditions. The utility model employs a flexible circuit board to make the solar battery square array and compresses two elastic thin steel wires on the two sides of the flexible circuit board. One function of the two thin steel wires is to regard as the self- extending gravity gradient rod. The utility model utilizes the physical power supply to supply the moonlet the power, and the life of the physical power supply is two magnitude orders longer than the chemical power supply.
Description
Affiliated technical field
The utility model relates to the power supply of the amateurish small satellite of a kind of teenager and the extending apparatus of gravity gradient boom, especially can be integrated solar array and gravity gradient boom, thereby save cost and improved reliability.
Technical background
Each subsystem of present small satellite all is relatively independent, thereby designs with regard to more complicated, is not suitable for the teenager amateur and designs, makes according to existing condition.
Summary of the invention
In order to simplify the structure of small satellite, it is that the flexible PCB of base material is made solar cell array that the utility model has adopted polyimide, and at two elasticity finer wires of the both sides of flexible PCB pressing.One of function of these two finer wires is as from stretching gravity gradient boom, can also use as power source bus or communication line in addition.
The power-supply system of general satellite adopts the electrochemical power source power supply more, and the life-span of electrochemical power source often can be very not long.It is the small satellite power supply that the utility model adopts physical power source, and its life-span is than long two orders of magnitude of electrochemical power source.Specifically be to adopt solar cell to the charging of farad super capacitor, farad capacitor comes small satellite is powered to the method for secondary power supply discharge.
Small satellite adopts the dumbbell type structure, and respectively there is a twin star on both sides, and one as primary, and another is as the counterweight star.The gravity gradient self-stabilization is adopted in attitude control, and which star is in the face of the earth, and which is exactly a primary.
The counterweight star does not consume more electric energy in order to guarantee the primary normal operation, and the utility model has been taked two measures.Each twin star of the first has been installed the One Earth One Family sensor, receives a star job of terrestrial radiation, and another is as counterweight.Its two be every twin star be equipped with bubble flare be 120 the degree about sending and receiving penetrate antenna.Mode of operation adopts replys formula, has only in the face of the star of the earth and just can receive the signal that send on ground.
Description of drawings
Fig. 1 is that polyimide is that the flexible PCB of base material is made solar cell array and held concurrently from stretching gravity gradient boom.ST is a finer wire, and CAB is the cable of printing,
Fig. 2 is the battery of small satellite.
Fig. 3 is the state of small satellite after launching.
Fig. 4 is the section-drawing of A-B-C.ANT is an antenna, and satellite stretches out after launching.CAP is the farad capacitor group, as energy-storage travelling wave tube.ES is an earth sensor, receives this place star start work after the terrestrial radiation.RECV is that receiver, TRMT are that emitter, CAM are that photographic camera, CMPT are that computing machine on the star, BATT are that backup power, DC/DC are that secondary power supply, ACTL are that solar cell array controller, CARPJT are the lift-launch project.
Specific implementation method
The celestial body physical dimension, the volume of load in the TV star and decide, shell employing aluminium honeycomb carbon fibre material also can adopt epoxide resin material.The inner multilayer insulation material that adopts.Parts are installed and are firmly noted damping.
Claims (1)
1, the power supply of simple and easy small satellite and extension means are that the flexible PCB of base material constitutes by farad capacitor, secondary power supply and polyimide, it is characterized in that: at these two finer wires of two elasticity finer wires of the both sides of flexible PCB pressing, solar cell array has been installed in the centre.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620002172 CN200981645Y (en) | 2006-02-09 | 2006-02-09 | Power supply and stretching mechanism for simple moonlet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620002172 CN200981645Y (en) | 2006-02-09 | 2006-02-09 | Power supply and stretching mechanism for simple moonlet |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN200981645Y true CN200981645Y (en) | 2007-11-28 |
Family
ID=38908806
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200620002172 Expired - Fee Related CN200981645Y (en) | 2006-02-09 | 2006-02-09 | Power supply and stretching mechanism for simple moonlet |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN200981645Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102826236A (en) * | 2012-09-13 | 2012-12-19 | 上海微小卫星工程中心 | Satellite |
| CN105984594A (en) * | 2015-01-28 | 2016-10-05 | 中国科学院空间科学与应用研究中心 | Low-orbit satellite power supply device |
-
2006
- 2006-02-09 CN CN 200620002172 patent/CN200981645Y/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102826236A (en) * | 2012-09-13 | 2012-12-19 | 上海微小卫星工程中心 | Satellite |
| CN102826236B (en) * | 2012-09-13 | 2015-03-25 | 上海微小卫星工程中心 | Satellite |
| CN105984594A (en) * | 2015-01-28 | 2016-10-05 | 中国科学院空间科学与应用研究中心 | Low-orbit satellite power supply device |
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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: 20071128 Termination date: 20100209 |