CN110034613A - Satellite power system and satellite - Google Patents
Satellite power system and satellite Download PDFInfo
- Publication number
- CN110034613A CN110034613A CN201910321327.1A CN201910321327A CN110034613A CN 110034613 A CN110034613 A CN 110034613A CN 201910321327 A CN201910321327 A CN 201910321327A CN 110034613 A CN110034613 A CN 110034613A
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- satellite
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- radio energy
- emitting module
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- 238000006243 chemical reaction Methods 0.000 claims abstract description 7
- 239000000463 material Substances 0.000 claims description 12
- 239000010949 copper Substances 0.000 claims description 8
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- OSOKRZIXBNTTJX-UHFFFAOYSA-N [O].[Ca].[Cu].[Sr].[Bi] Chemical compound [O].[Ca].[Cu].[Sr].[Bi] OSOKRZIXBNTTJX-UHFFFAOYSA-N 0.000 claims description 5
- ZDCILOBQBRQMEQ-UHFFFAOYSA-N copper barium(2+) oxygen(2-) yttrium(3+) Chemical compound [Cu+2].[Ba+2].[O-2].[Y+3] ZDCILOBQBRQMEQ-UHFFFAOYSA-N 0.000 claims description 5
- 230000001678 irradiating effect Effects 0.000 claims description 5
- 230000008569 process Effects 0.000 claims description 5
- PZKRHHZKOQZHIO-UHFFFAOYSA-N [B].[B].[Mg] Chemical compound [B].[B].[Mg] PZKRHHZKOQZHIO-UHFFFAOYSA-N 0.000 claims description 4
- PACGUUNWTMTWCF-UHFFFAOYSA-N [Sr].[La] Chemical compound [Sr].[La] PACGUUNWTMTWCF-UHFFFAOYSA-N 0.000 claims description 4
- 238000009434 installation Methods 0.000 claims description 4
- IQONKZQQCCPWMS-UHFFFAOYSA-N barium lanthanum Chemical compound [Ba].[La] IQONKZQQCCPWMS-UHFFFAOYSA-N 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 abstract description 12
- 238000001514 detection method Methods 0.000 description 11
- 239000002887 superconductor Substances 0.000 description 8
- 230000008859 change Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000004804 winding Methods 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 230000032683 aging Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- QPLDLSVMHZLSFG-UHFFFAOYSA-N Copper oxide Chemical compound [Cu]=O QPLDLSVMHZLSFG-UHFFFAOYSA-N 0.000 description 1
- 239000005751 Copper oxide Substances 0.000 description 1
- 241001269238 Data Species 0.000 description 1
- 241000127225 Enceliopsis nudicaulis Species 0.000 description 1
- 206010033799 Paralysis Diseases 0.000 description 1
- ZNZPXPQFEOGASM-UHFFFAOYSA-N [Cu].[Ba].[La] Chemical compound [Cu].[Ba].[La] ZNZPXPQFEOGASM-UHFFFAOYSA-N 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910000431 copper oxide Inorganic materials 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000009123 feedback regulation Effects 0.000 description 1
- 230000004907 flux Effects 0.000 description 1
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- 229910052757 nitrogen Inorganic materials 0.000 description 1
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- 238000007254 oxidation reaction Methods 0.000 description 1
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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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/428—Power distribution and management
-
- 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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
- B64G1/443—Photovoltaic cell arrays
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J50/00—Circuit arrangements or systems for wireless supply or distribution of electric power
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J50/00—Circuit arrangements or systems for wireless supply or distribution of electric power
- H02J50/10—Circuit arrangements or systems for wireless supply or distribution of electric power using inductive coupling
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
- H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
- H02S20/00—Supporting structures for PV modules
- H02S20/30—Supporting structures being movable or adjustable, e.g. for angle adjustment
- H02S20/32—Supporting structures being movable or adjustable, e.g. for angle adjustment specially adapted for solar tracking
-
- 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
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Computer Networks & Wireless Communication (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Photovoltaic Devices (AREA)
Abstract
The present invention discloses a kind of satellite power system and satellite, the satellite power system includes solar components, battery, power-supply management system, radio energy emitting module and radio energy receiving unit, the battery, power-supply management system, radio energy emitting module are set on the solar components, and the battery is connect with the radio energy emitting module by the power-supply management system.The power-supply management system sends radio energy to the radio energy receiving unit for controlling the radio energy emitting module, and the Charge Management to battery, the radio energy receiving unit is installed on satellite, is received the radio energy of radio energy emitting module transmission and is carried out after voltage conversion to power satellite.The present invention is for solving the problems, such as that the line between solar panels and satellite main body easily winds and influence service life in the prior art.
Description
Technical field
The present invention relates to charge and discharge electro-technical fields, in particular to satellite power system and satellite.
Background technique
Solar cell module is the module powered to the propeller of existing satellite in the prior art, in the mistake of satellite motion
Cheng Zhong, solar panels need to change and adjust the angle, so that solar panels and the sun face always, to get maximum hair
Electric flux, at this point, battery and solar panels face are arranged, battery is installed on the propeller of satellite, and in the process,
Often the problem of conducting wire between battery and solar panels is wound with the rotation of solar panels can occur, thus direct shadow
Operational safety and the service life of satellite are rung.
Summary of the invention
The main object of the present invention is to propose a kind of satellite power system, it is intended to be solved between satellite main body and solar panels
Conducting wire the problem of being wound with the rotation of solar panels.
To achieve the above object, the present invention proposes that a kind of satellite power system, the satellite power system include solar energy
Component, battery, power-supply management system, radio energy emitting module and radio energy receiving unit, the satellite include the sun
Energy component and satellite main body, the solar components and the satellite main body are mechanically connected；
The battery, power-supply management system, radio energy emitting module are set on the solar components, the electric power storage
Pond is connect with the radio energy emitting module by the power-supply management system；
The power-supply management system is sent out for controlling the radio energy emitting module to the radio energy receiving unit
Send radio energy；
The radio energy receiving unit receives the radio energy transmitting group for being installed on the satellite main body
The radio energy of part transmission, and carry out after voltage conversion process to power satellite.
Preferably, the solar components include solar panels and actuator, and the actuator is for adjusting the sun
The rotation angle of energy plate.
Preferably, the solar components further include control box, and the control box is used for according to the sun in the solar energy
Irradiating angle on plate controls the rotation angle that the actuator adjusts the solar panels.
Preferably, the radio energy receiving unit rotational installation is in the satellite main body；
And/or the radio energy emitting module rotational installation is on the solar panels.
Preferably, the radio energy emitting module includes transmitting coil, and the material of the transmitting coil is high-temperature superconductor
Material.
Preferably, the radio energy receiving unit includes receiving coil, and the material of the receiving coil is high-temperature superconductor
Material.
Preferably, the high temperature superconducting materia includes yttrium oxide barium copper, bismuth-strontium-calcium-copper-oxygen, magnesium diboride, the oxidation of barium lanthanum copper
Object and strontium lanthanum Cu oxide.
Preferably, the radio energy emitting module further includes modulating system, the input terminal of the modulating system with it is described
The input terminal of power-supply management system connects, and the output end of the modulating system is connect with the transmitting coil, the modulating system,
Power modulation for exporting the power-supply management system is high-frequency current signal.
Preferably, the size of current of the high-frequency current signal is 0-400A, 600A or 800A.
Preferably, the radio energy emitting module further includes demodulating system, the input terminal of the demodulating system with it is described
Receiving coil connection, the output end of the demodulating system are connect with the power input of the solar components, the demodulation system
System, the power modulation for exporting the receiving coil is the working power to work for satellite main body, and gives the satellite
Main body and the solar components provide working power.
Preferably, the control box includes control circuit, driving circuit and detection circuit, the test side of the detection circuit
It is connect with the detection signal input part of the control circuit, the control signal output of the control circuit and the driving circuit
Driving signal input connection, the output end of the driving circuit connect with the actuator, described in the actuator drives
Solar panels rotation.
To achieve the above object, the present invention proposes a kind of satellite, including satellite main body and satellite power system, the satellite
The radio energy receiving unit of power supply system is set in the satellite main body, and is electrically connected with the satellite main body, the satellite
The radio energy emitting module of power supply system is set on the solar panels.
The present invention is sent out by the way that solar components, battery, power-supply management system, radio energy is arranged in satellite power system
Penetrate component and radio energy receiving unit.Satellite includes solar components and satellite main body, solar components and satellite main body machine
Tool connection.The battery, power-supply management system, radio energy emitting module are set on the solar components, the electric power storage
Pond is connect with the radio energy emitting module by the power-supply management system.The power-supply management system is used to control institute
It states radio energy emitting module and sends radio energy to the radio energy receiving unit, and by the radio energy receiving unit
It is installed on satelloid, receives the radio energy of the radio energy emitting module transmission, and given after carrying out voltage conversion process
Power satellite, so that by wirelessly transmitting electrical energy between solar components and satellite main body, to solve solar panels and satellite
The problem of conducting wire between main body is wound with the rotation of solar panels, extends the service life of satellite, prevent conducting wire with
The rotation of solar panels and wind accelerated ageing.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
The structure shown according to these attached drawings obtains other attached drawings.
Fig. 1 is the module diagram of satellite power system of the present invention；
Fig. 2 is that satellite power system of the present invention is set to the structural schematic diagram on satellite；
Fig. 3 is the transmitting coil of satellite power system of the present invention and the position view of receiving coil.
The embodiments will be further described with reference to the accompanying drawings for the realization, the function and the advantages of the object of the present invention.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiment is only a part of the embodiments of the present invention, instead of all the embodiments.Base
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts it is all its
His embodiment, shall fall within the protection scope of the present invention.
It is to be appreciated that if relating to directionality instruction (such as up, down, left, right, before and after ...) in the embodiment of the present invention,
Then directionality instruction be only used for explain under a certain particular pose (as shown in the picture) between each component relative positional relationship,
Motion conditions etc., if the particular pose changes, directionality instruction is also correspondingly changed correspondingly.
In addition, being somebody's turn to do " first ", " second " etc. if relating to the description of " first ", " second " etc. in the embodiment of the present invention
Description be used for description purposes only, be not understood to indicate or imply its relative importance or implicitly indicate indicated skill
The quantity of art feature." first " is defined as a result, the feature of " second " can explicitly or implicitly include at least one spy
Sign.It in addition, the technical solution between each embodiment can be combined with each other, but must be with those of ordinary skill in the art's energy
It is enough realize based on, will be understood that the knot of this technical solution when conflicting or cannot achieve when occurs in the combination of technical solution
Conjunction is not present, also not the present invention claims protection scope within.
In order to solve the problems, such as that the conducting wire between solar panels and satellite main body is wound with the rotation of solar panels, this
Invention proposes a kind of satellite power system, is applied to satellite.
In one embodiment, as shown in Figure 1, 2, the present invention proposes that a kind of satellite power system, satellite power system include
Solar components 110, battery 111, power-supply management system 112, radio energy emitting module 113 and radio energy receiving unit
114, satellite includes solar components 110 and satellite main body 115, and solar components 110 and satellite main body 115 are mechanically connected；Too
Positive energy component 110 includes solar panels 1101.Wherein, battery 111, power-supply management system 112, radio energy emitting module
113 are set on solar components 110, and battery 111 is connect with radio energy emitting module 113 by power-supply management system 112.
Radio energy receiving unit 114 is installed in satellite main body 115.
Wherein, solar components 110 and satellite main body 115 are mechanically connected, and mechanical connection herein includes being not limited to
It is fixedly connected or is rotatablely connected, only need to realize basic mechanical connection, the group of the satellite power system after specific connection
Figure is as shown in Fig. 2, in one embodiment, solar components 110 are the component for converting the solar into electric energy, power-supply management system
112 control radio energy emitting modules 113 send radio energy to radio energy receiving unit 114.Radio energy receiving unit
114 are installed in satellite main body 115, receive the radio energy that radio energy emitting module 113 transmits, and carry out at voltage conversion
Power satellite is given after reason.At this point, radio energy receiving unit 114 and radio energy emitting module 113 are respectively arranged in satellite
In main body 115 and solar components 110, actual conducting wire connection is had no between the two, and radio energy emitting module 113 passes through electricity
Electric energy is transmitted to radio energy receiving unit 114 by the coupling in magnetic field, to be power satellite, thus solves solar energy
The problem of conducting wire between plate and satellite main body is wound with the rotation of solar panels, it is thus also avoided that caused by conducting wire winding
The problems such as accelerated ageing caused by wire insulation rupture and winding.In addition, being provided with battery on solar panels 1101
111, it on the one hand can guarantee output power when radio energy emitting module 113 works, power-supply management system 112 can be passed through
Design parameter (voltage, electric current and frequency) to be achieved needed for setting is sent improves the output electricity of radio energy emitting module 113
The stability of energy.When radio energy emitting module 113 does not work, radio energy emitting module 113 and radio energy reception group
Without carrying out electric energy transmission between part 114, moreover it is possible to improve the electric power storage speed of battery 111.
Optionally, as shown in Fig. 2, solar components 110 include solar panels 1101 and actuator 1102, actuator 1102
It is fixedly connected or is rotatablely connected with solar panels 1101.
In order to improve the energy conversion efficiency of solar panels 1101, in one embodiment, actuator 1102 and solar panels
1101 are fixedly connected, and actuator 1102 and satellite main body 115 are then rotation connection.In another embodiment, actuator 1102 with
Solar panels 1101 are rotatablely connected, and actuator 1102 can be rotation connection with satellite main body 115 or be fixedly connected.Above-mentioned
In two embodiments, it is rotatablely connected and is fixedly connected and be merely to illustrate actuator 1102 and solar panels 1101 and actuator 1102
With the relationship between satellite main body 115, it is rotatablely connected and is not limited to gear connection, is slidably connected and other implementations, it is fixed to connect
It connects and threaded connection can also be used, in addition there are also the connection types such as key connection, pin connection and riveting.At this point, actuator 1102 is used for
Adjust the rotational angle of solar panels 1101.The actuator 1102 is rotatablely connected with solar panels 1101, can be according to the sun
Can plate 1101 and sunray angulation realize and follow, i.e., too can the rotational angle of plate received according to solar panels 1101
Light angulation change so that solar panels 1101 are kept with the angle of light received in a certain range, to increase
Add the transfer efficiency of solar panels 1101, so that solar panels 1101 convert the solar into the energy of electric energy within the same time
Amount is more, completes the thermal energy storage process of battery 111 faster.
Optionally, in order to accelerate too can plate rotational angle adjustment speed, actuator 1102 include adjusting rod, the adjusting
One end of bar is connect with solar panels 1101.Actuator 1102 further include motor perhaps one end of cylinder motor or cylinder with
The other end of the adjusting rod is rotatablely connected, that is, passes through gear or the connection of the embodiment of other rotation connections.The motor
The other end or the other end of cylinder be fixedly connected with satellite main body 115.
Wherein, by motor, perhaps cylinder adjusting adjusting rod can be adjusted by the work of control motor or cylinder
Can plate rotational angle, thus realized in structure too can plate rotational angle adjusting, actuator 1102 adjust solar panels 1101
Rotation angle.Meanwhile also speeded up too can plate rotational angle adjustment speed and realize the flexible of solar panels 1101, from
And facilitate the operations such as avoiding barrier, diminution volume.
In the above-described embodiments, in the first situation, as shown in Fig. 2, actuator 1102 is set to the satellite main body 115
On, at this point it is possible to which increasing satellite adjusts integrally-built stability, optionally, moreover it is possible to using the control system of satellite come into one
The rotation angle of the fine adjusting solar panels 1101 of step, to further increase the working efficiency of solar panels 1101, with this into
The working efficiency of one step raising satellite.In second situation, actuator 1102, which is set on the solar panels 1101, (schemes not
Show), at this point, actuator be set to solar panels 1101 can it is more flexible adjust solar panels 1101 rotation angle.
Optionally, as shown in Fig. 2, solar components 110 further include control box 1103, control box 1103 and actuator 1102
Connection.
Wherein, control box 1103 is used for the irradiating angle control tune of actuator 1102 according to the sun on solar panels 1101
The rotation angle of node solar plate 1101.At this point, control box 1103 can detecte irradiation of the sun on solar panels 1101
Angle, specific detection method can be control box 1103 by detection the sun solar panels 1101 electric current, by with it is pre-
The parameter set compares, to obtain irradiating angle of the sun on solar panels 1101, and then issues control signal control driving
Part 1102, to change the rotation angle of solar panels 1101, so that realizing solar panels 1101 can utilize to the full extent
To solar energy, high utilization efficiency is reached.
In the above-described embodiments, in the first situation, as shown in Fig. 2, control box 1103 and actuator 1102 are respectively provided with
In on solar panels 1101, thus under conditions of electric energy wireless transmission, without between solar panels and satellite main body 115
Other wire rod is set to control its rotation angle to ensure that the safety of satellite entirety and prevent wire rod from damaging because of rotation
It is bad, to extend the service life of satellite power system.In second situation, controls box 1103 and actuator 1102 is equal
It is set in satellite main body 115, controls it without other wire rod is arranged between solar panels and satellite main body 115
Rotate angle prevents wire rod from damaging because of rotation to ensure that the safety of satellite entirety, to extend power satellite system
The service life of system.Control box 1103, which can detecte irradiating angle of the sun on solar panels 1101, at this time can pass through light
The equipment radio detection such as illuminance transducer.
Optionally, as shown in figure 3, radio energy emitting module 113 includes transmitting coil 1141, the material of transmitting coil 1141
Matter is high temperature superconducting materia.
Wherein, high temperature superconducting materia is set by the material of transmitting coil 1141, because of the characteristic of superconductor, in high temperature
Resistance is almost not present under environment, has good electric conductivity, electric energy efficiency of transmission can be promoted.It is used at this time as conducting wire, it can
To be suitable for high temperature space environment locating for satellite, also solving existing wireless charging system cannot be used for asking for hot environment
Topic, so that without making biggish improvement to the power-supply system of satellite, it is special without being made to radio energy emitting module 113
Protection to guarantee normal operating conditions.To save research cost and design cost.
Optionally, as shown in figure 3, radio energy receiving unit 114 includes receiving coil 1151, the material of receiving coil 1151
Matter is high temperature superconducting materia.
Wherein, high temperature superconducting materia is set by the material of receiving coil 1151, because of the characteristic of superconductor, in high temperature
Resistance is almost not present under environment, has good electric conductivity, electric energy efficiency of transmission can be promoted.It is used at this time as conducting wire, also
It can be adapted for high temperature space environment locating for satellite, also solving existing wireless charging system cannot be used for hot environment
Problem, so that making spy without to radio energy emitting module 113 without making biggish improvement to the power-supply system of satellite
Different protection is to guarantee normal operating conditions.To save research cost and design cost.
Optionally, high temperature superconducting materia includes yttrium oxide barium copper, bismuth-strontium-calcium-copper-oxygen, magnesium diboride, barium lanthanum Cu oxide and
Strontium lanthanum Cu oxide.
Wherein, high-temperature superconductor refers to some substances with the critical-temperature relatively high compared with other superconducting materials in liquid nitrogen
In the environment of the superconducting phenomenon that generates, high temperature superconducting materia is one of superconducting material same clan, has general structure feature
And relatively on the Cu oxide plane that is moderately spaced.They are also referred to as copper oxide superconductor.Some chemical combination in this same clan
In object, the critical-temperature that superconductivity occurs is highest in known superconductor.At this point, superconductor be set as yttrium oxide barium copper,
Bismuth-strontium-calcium-copper-oxygen, magnesium diboride, when barium lanthanum Cu oxide and strontium lanthanum Cu oxide, by yttrium oxide barium copper and bismuth-strontium-calcium-copper-oxygen application
The efficiency of transmission of radio energy receiving unit 114 and wireless chips can be greatlyd improve when superconducting coil.
Optionally, transmitting coil is strip, can be preferably solid with solar panels 1101 when transmitting coil is strip
Fixed, the dropping situations occurred when so as to avoid satellite launch cause the paralysis of entire power-supply system.
Optionally, radio energy emitting module 113 further includes modulating system, the input terminal of modulating system and power management system
The input terminal connection of system 112, the output end of modulating system are connect with transmitting coil.
Wherein, modulating system can be general various inverter systems, and modulating system exports power-supply management system 112
Power modulation be high-frequency current signal.
Optionally, power-supply management system 112 for available various electric power management circuits in the prior art and can match
Control method constitute power-supply management system 112, for realizing battery 111 charge and discharge, adjust battery 111 power supply
(voltage, electric current and frequency) output size and the output time for controlling battery 111, to realize intelligence transmitting.
Optionally, high-frequency current signal can be selected as 0-400A, 0-600A, 800A.When the current strength of transmitting coil is
When high-frequency heavy-current within the scope of these, electric energy can be transmitted to the full extent, efficiency of transmission can achieve 95% or more, several
It is equal to the efficiency of transmission of wire transmission electric energy, and having compared to wire transmission prevents conducting wire winding, extension satellite from making
With the effect in service life.
Optionally, radio energy emitting module 113 further includes demodulating system, and the input terminal and receiving coil of demodulating system connect
It connects, the output end of demodulating system is connect with the power input of solar components 110, demodulating system, for receiving coil is defeated
Power modulation out is high-frequency current signal, and provides working power to solar components 110.
Wherein, demodulating system can be according to the suitable voltage output of different adjustment of the satellite operation module of connection, can be with
For existing various general voltage modulation circuits.
Optionally, control box 1103 includes control circuit, driving circuit and detection circuit, the test side of detection circuit and control
The detection signal input part of circuit processed connects, the control signal output of control circuit and the driving signal input of driving circuit
Connection, the output end of driving circuit are connect with actuator 1102, and actuator 1102 drives solar panels 1101 to rotate.
Wherein, the incident angle for the sunlight that detection circuit detection solar panels 1101 receive, and be converted to corresponding
For electric signal transmission to control circuit, control circuit exports corresponding control signal to control solar panels according to the electric signal
1101 rotation angle, so that the solar panels are in the suitable position that maximum can convert the solar into electric energy, tool
The incident angle of the sunlight of body can be obtained according to various experimental datas in the prior art.At this point, by feedback regulation, it is real
Existing 1101 solar energy of solar panels follows, realizes maximum solar energy conversion.
It is worth noting that, can to select existing various control chips, driving circuit that can select existing for control circuit
Cylinder driving circuit and motor-drive circuit, detection circuit can be existing various sensors, such as current sensor.
To achieve the above object, as shown in Fig. 2, the present invention proposes a kind of satellite, including satellite main body and power satellite system
The radio receiver of system, satellite power system is set in satellite main body, and is electrically connected with satellite main body.
Due to a kind of satellite of the invention, all embodiments of above-mentioned satellite power system are contained, therefore also has and defends
All beneficial effects of star power supply system, details are not described herein again.
The above is only a preferred embodiment of the present invention, is not intended to limit the scope of the invention, all in the present invention
Inventive concept under, using equivalent structure transformation made by description of the invention and accompanying drawing content, or directly/be used in it indirectly
He is included in scope of patent protection of the invention relevant technical field.
Claims (10)
1. a kind of satellite power system, which is characterized in that the satellite power system includes battery, power-supply management system, nothing
Line electric energy emitting module and radio energy receiving unit, the satellite include solar components and satellite main body, the solar energy
Component and the satellite main body are mechanically connected；The solar components include solar panels；
The battery, power-supply management system, radio energy emitting module be set to the solar components on, the battery with
The radio energy emitting module is connected by the power-supply management system；
The power-supply management system sends nothing to the radio energy receiving unit for controlling the radio energy emitting module
Line electric energy；
The radio energy receiving unit receives the radio energy emitting module and passes for being installed on the satellite main body
Defeated radio energy, and carry out after voltage conversion process to power satellite.
2. satellite power system as described in claim 1, which is characterized in that the solar components further include actuator, institute
Actuator is stated for adjusting the rotation angle of the solar panels.
3. satellite power system as claimed in claim 2, which is characterized in that the solar components further include control box, institute
It states the irradiating angle that control box is used for according to the sun on the solar panels and controls the actuator adjusting solar panels
Rotation angle.
4. satellite power system as claimed in claim 2, which is characterized in that radio energy receiving unit rotational installation in
In the satellite main body；
And/or the radio energy emitting module rotational installation is on the solar panels.
5. satellite power system as described in claim 1, which is characterized in that the radio energy emitting module includes emission lines
Circle, the material of the transmitting coil are high temperature superconducting materia；
The radio energy receiving unit includes receiving coil, and the material of the receiving coil is high temperature superconducting materia.
6. satellite power system as claimed in claim 4, which is characterized in that the high temperature superconducting materia includes yttrium oxide barium
Copper, bismuth-strontium-calcium-copper-oxygen, magnesium diboride, barium lanthanum Cu oxide and strontium lanthanum Cu oxide.
7. satellite power system as described in claim 1, which is characterized in that the radio energy emitting module further includes modulation
System, the input terminal of the modulating system are connect with the input terminal of the power-supply management system, the output end of the modulating system
It is connect with the transmitting coil, the modulating system, the power modulation for exporting the power-supply management system is high-frequency electrical
Flow signal.
8. satellite power system as claimed in claim 6, which is characterized in that the size of current of the high-frequency current signal is 0-
400A, 600A or 800A.
9. satellite power system as described in claim 1, which is characterized in that the radio energy receiving unit further includes demodulation
System, the input terminal of the demodulating system are connect with the receiving coil, the output end of the demodulating system and the solar energy
The power input of component connects, the demodulating system, and the power modulation for exporting the receiving coil is for satellite
The working power of work, and working power is provided to the satellite main body and the solar components.
10. a kind of satellite, which is characterized in that including satellite main body and satellite power system, the satellite power system it is wireless
Electric energy receiving unit is set in the satellite main body, and is electrically connected with the satellite main body, the satellite power system it is wireless
Electric energy emitting module is set on the solar panels.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910321327.1A CN110034613A (en) | 2019-04-19 | 2019-04-19 | Satellite power system and satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910321327.1A CN110034613A (en) | 2019-04-19 | 2019-04-19 | Satellite power system and satellite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110034613A true CN110034613A (en) | 2019-07-19 |
Family
ID=67239554
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910321327.1A Pending CN110034613A (en) | 2019-04-19 | 2019-04-19 | Satellite power system and satellite |
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| Country | Link |
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| CN (1) | CN110034613A (en) |
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| CN107483099A (en) * | 2017-08-30 | 2017-12-15 | 长光卫星技术有限公司 | Satellite borne equipment is isolated and safeguards system |
| CN108649710A (en) * | 2018-06-12 | 2018-10-12 | 哈尔滨工业大学 | A kind of how small coil coupling device for slewing wireless power transmission |
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| CN103729507A (en) * | 2013-12-23 | 2014-04-16 | 上海卫星工程研究所 | Magic cube satellite and designing method for same |
| CN106877470A (en) * | 2017-04-18 | 2017-06-20 | 四川省科学城帝威电气有限公司 | The radio energy transmission system that city train charges is used for based on high temperature superconductor coil |
| CN107483099A (en) * | 2017-08-30 | 2017-12-15 | 长光卫星技术有限公司 | Satellite borne equipment is isolated and safeguards system |
| CN108649710A (en) * | 2018-06-12 | 2018-10-12 | 哈尔滨工业大学 | A kind of how small coil coupling device for slewing wireless power transmission |
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Effective date of registration: 20210201 Address after: 518000 A4 101-108, Fuhai information port, Qiaotou community, Fuhai street, Shenzhen, Guangdong, China. Applicant after: Shenzhen nahongyi Optical Technology Co.,Ltd. Address before: 518000 Fuhai Information Port 126, Qiaotou community, Fuhai street, Bao'an District, Shenzhen City, Guangdong Province Applicant before: SHENZHEN WEILAN WUXIAN TECHNOLOGY Co.,Ltd. |
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Application publication date: 20190719 |