CN105984594A - Low-orbit satellite power supply device - Google Patents
Low-orbit satellite power supply device Download PDFInfo
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- CN105984594A CN105984594A CN201510044347.0A CN201510044347A CN105984594A CN 105984594 A CN105984594 A CN 105984594A CN 201510044347 A CN201510044347 A CN 201510044347A CN 105984594 A CN105984594 A CN 105984594A
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- satellite
- cable
- core wire
- metal core
- power supply
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Abstract
Provided is a low-orbit satellite power supply device. The low-orbit satellite power supply device comprises a cable. One end of a satellite is installed on the outer surface of the satellite and the other end of the cable is suspended. The cable is formed by metal core wire and a cable sleeve. The metal core wire penetrates through a satellite sheath to be connected with a power supply regulator.The low-orbit satellite power supply device has following advantages: the low-orbit satellite power supply device can be utilized for power supply of the satellite such that power supply can be provided for the satellite in the earth shadow and other regions.
Description
Technical field
The present invention relates to spacecraft in-orbit time power supply supply field, particularly relate to one utilize wire cut earth's magnetic field
Produce electromotive force and to provide for satellite the electric supply installation of power supply supply.
Background technology
When satellite transit is in terrestrial space, carries out every service application or scientific exploration is required for corresponding instrument
Equipment, and the work of all these instrument and equipment has been required for energy supply.For Mu Qian, the energy supply of satellite
All for being supplied by the series connection of the cell piece on solar battery array.When satellite enters earth occlusion area namely side at night,
Solar cell can not provide energy supply for satellite, and solar cell has and makes due to the impact of Space Particle irradiation
Become the problem that output gradually fails.
The earth all also exists magnetic field therein due to its architectural characteristic with surrounding space, and magnetic direction is by geographical south
Set out to north geographic pole and close at earth interior in pole.Running on the electric charge in the conductor of Earth Week confining space can be due to
Being moved to the direction being perpendicular to magnetic field of the earth by the Lorentz force action in magnetic field of the earth, this can cause at conductor
There is electromotive force in two ends.Therefore, by conductor two ends are connected with the power-supply system of satellite can be just satellite provide
Power supply is supplied.
Summary of the invention
It is an object of the invention to, the side at night existed when being power satellite for solution currently with solar cell cannot supply
The problem that electricity and solar cell can gradually fail, the present invention provides a kind of by installing cable in order to cut at satellite surface
Cede territory magnetic field produce electromotive force come for satellite provide power supply supply device.
To achieve these goals, the invention provides a kind of low-orbit satellite electric supply installation, including: cable, should
Cable one end is installed on satellite external surface and other end is unsettled, and this cable is made up of metal core wire and cable cover,
Metal core wire is connected through satellite eyelid covering with the power regulator of satellite.
According to one embodiment of present invention, between length and the length of cable cover of the metal core wire of described cable
Error is within 5%, to avoid metal core wire to contact with space plasma too much.
According to one embodiment of present invention, the radical of the metal core wire of described cable is no less than 2, to avoid
Owing in work process, electric current is excessive and make metal core wire overheated.
According to one embodiment of present invention, the surface of the heart yearn terminal of the metal core wire of described cable is round and smooth,
To avoid causing pulsation of current due to point discharge etc..
It is an advantage of the current invention that: utilize the low-orbit satellite electric supply installation of the present invention, can be that satellite provides power supply
Supply, thus power supply supply can be provided when being in the regions such as ground shadow at satellite.
Accompanying drawing explanation
Fig. 1 is to show the schematic diagram that the electric supply installation of the Seeds of First Post-flight present invention runs on Earth's orbit and cutting magnetic line.
Fig. 2 is the structural representation of the electric supply installation of the present invention.
Fig. 3 is the A-A directional profile schematic diagram of Fig. 2.
Fig. 4 is the generalized section of the cable of the electric supply installation of the present invention.
Fig. 5 is the structural representation of the cable terminations of the electric supply installation of the present invention.
Reference:
1, satellite 2, earth magnetism field wire 3, cable
4, satellite structure 5, power regulator 6, live load
7, cable cover 8, metal core wire 9, heart yearn terminal
Detailed description of the invention
With preferred embodiment, the low-orbit satellite electric supply installation of the present invention is described in detail below in conjunction with the accompanying drawings.
Fig. 1 is to show the schematic diagram that the electric supply installation of the Seeds of First Post-flight present invention runs on Earth's orbit and cutting magnetic line.
As it can be seen, when satellite 1 in orbit time, the cable 3 of this electric supply installation cuts earth magnetism field wire 2, thus at cable
Metal core wire 8 two ends of 3 produce electromotive force.
Fig. 2 is the structural representation of the electric supply installation of the present invention.Cable 3 is by satellite structure 4 and power regulator
5 are connected, and power regulator 5 is connected with live load 6, live load 6 then with being connected structurally of satellite.Figure
3 is the generalized section in the A-A direction of Fig. 2, i.e. electric loop figure.By electromotive force output produced by cable 3
Electric current forms electric loop by space plasma with satellite structure 4, live load 6 and power regulator 5.Deng
Electronics in gas ions and ion will terminal or satellite structure 4 towards cable 3 move respectively, thus constantly
Realize the closed loop of electric supply installation.
Fig. 4 is the cable generalized section of the electric supply installation of the present invention, wherein metal core wire 8 be placed in cable cover 7 it
In.Preferably, the radical of metal core wire 7 is no less than 2, to avoid electric current excessive, in the fig. 4 embodiment
Have employed 8 metal core wire.
Preferably, the error between length and the length of cable cover 7 of metal core wire 8 is within 5%, to avoid gold
Belong to heart yearn 8 to contact with space plasma too much.
According to an embodiment, if satellite transit empty 600km height on earth, magnetic field intensity is 0.4Gauss,
The a length of 100m magnitude of then required cable 3 magnetic line of force keeping cable 3 to be perpendicular to earth's magnetic field can be just
Satellite provides the power supply supply of 28V.
Fig. 5 is the structural representation of the cable terminations of the electric supply installation of the present invention, wherein the heart yearn end of metal core wire 8
The surface of son 9 is round and smooth, preferably by spherical structure, in order to avoid point discharge occurring and causing electric current arteries and veins
Punching.
It should be noted last that, above example is only in order to illustrate technical scheme and unrestricted.Although
With reference to embodiment, the present invention is described in detail, it will be understood by those within the art that, to the present invention
Technical scheme modify or equivalent, without departure from the spirit and scope of technical solution of the present invention, it is equal
Should contain in the middle of scope of the presently claimed invention.
Claims (5)
1. a low-orbit satellite electric supply installation, including: cable, this cable one end is installed on satellite external surface and another
Outer one end is unsettled, and this cable is made up of metal core wire and cable cover, and metal core wire is through satellite eyelid covering and satellite
Power regulator is connected.
Electric supply installation the most according to claim 1, it is characterised in that: the length of the metal core wire of described cable
With the error between the length of cable cover is within 5%.
Electric supply installation the most according to claim 1, it is characterised in that: the radical of the metal core wire of described cable
For no less than 2.
Electric supply installation the most according to claim 1, it is characterised in that: the heart yearn of the metal core wire of described cable
The surface of terminal is round and smooth.
Electric supply installation the most according to claim 4, it is characterised in that: the heart yearn of the metal core wire of described cable
Terminal is spherical structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510044347.0A CN105984594A (en) | 2015-01-28 | 2015-01-28 | Low-orbit satellite power supply device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510044347.0A CN105984594A (en) | 2015-01-28 | 2015-01-28 | Low-orbit satellite power supply device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105984594A true CN105984594A (en) | 2016-10-05 |
Family
ID=57036453
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510044347.0A Pending CN105984594A (en) | 2015-01-28 | 2015-01-28 | Low-orbit satellite power supply device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105984594A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109823574A (en) * | 2019-02-18 | 2019-05-31 | 中国科学院国家空间科学中心 | A kind of spaceborne intermittence service load system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2838102A1 (en) * | 2002-04-08 | 2003-10-10 | Agence Spatiale Europeenne | Combined ion-electric propulsion system for a space vehicle, combines tether conductor wire propulsion system with an electric propulsion system |
| US7118074B1 (en) * | 2003-10-17 | 2006-10-10 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Electrodynamic tether |
| CN200981645Y (en) * | 2006-02-09 | 2007-11-28 | 韩光熙 | Power supply and stretching mechanism for simple moonlet |
| US20100084512A1 (en) * | 2008-10-02 | 2010-04-08 | Michael Pindrik | Luno Geo Wind Mill |
| CN101938076A (en) * | 2010-08-13 | 2011-01-05 | 航天东方红卫星有限公司 | Microsatellite unplugged cable network |
-
2015
- 2015-01-28 CN CN201510044347.0A patent/CN105984594A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2838102A1 (en) * | 2002-04-08 | 2003-10-10 | Agence Spatiale Europeenne | Combined ion-electric propulsion system for a space vehicle, combines tether conductor wire propulsion system with an electric propulsion system |
| US7118074B1 (en) * | 2003-10-17 | 2006-10-10 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Electrodynamic tether |
| CN200981645Y (en) * | 2006-02-09 | 2007-11-28 | 韩光熙 | Power supply and stretching mechanism for simple moonlet |
| US20100084512A1 (en) * | 2008-10-02 | 2010-04-08 | Michael Pindrik | Luno Geo Wind Mill |
| CN101938076A (en) * | 2010-08-13 | 2011-01-05 | 航天东方红卫星有限公司 | Microsatellite unplugged cable network |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109823574A (en) * | 2019-02-18 | 2019-05-31 | 中国科学院国家空间科学中心 | A kind of spaceborne intermittence service load system |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161005 |