CN104917461B - A kind of Satellite vapour image Orbital detection circuit - Google Patents
A kind of Satellite vapour image Orbital detection circuit Download PDFInfo
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- CN104917461B CN104917461B CN201510350430.0A CN201510350430A CN104917461B CN 104917461 B CN104917461 B CN 104917461B CN 201510350430 A CN201510350430 A CN 201510350430A CN 104917461 B CN104917461 B CN 104917461B
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- 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
- H02S50/00—Monitoring or testing of PV systems, e.g. load balancing or fault identification
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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
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- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
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Abstract
A kind of Satellite vapour image Orbital detection circuit, for the in-orbit IV curves test of Satellite vapour image, including information process unit, star ground communication unit on electronic equipment, star on star.After IV test circuits are connected, the in-orbit real time data such as solar battery array voltage x current, temperature can be obtained in real time by electronic equipment on star, the data down transmission is drawn by complete solar battery array IV characteristic curves by star ground communication unit after being processed by information process unit on star.The present invention solves the voltage x current that existing method can only count satellite bus operating point, can not intuitively, comprehensively reflect the defect of IV curves, improve the accuracy of solar battery array performance monitoring and comprehensive, complete IV calibration curve informations are provided for solar battery array Performance Evaluation, the efficiency of lifetime of satellite assessment is improve, and more succinct intuitively data is provided for the in-orbit management of Satellite vapour image and is supported.
Description
Technical field
The present invention relates to a kind of Satellite vapour image Orbital detection circuit, belongs to Satellite vapour image field tests.
Background technology
Existing each satellite employs joint topological structure of the solar battery array with reference to accumulator battery.Solar battery array conduct
The generating equipment of satellite, provides conversion of the solar energy to electric energy during for satellite in orbit.Due to receiving when running in space
Affect to factors such as space ion irradiation decay factor, ultraviolet irradiation decay factor, microfluid collision and alternating hot and colds
The impact of decay factor, the in-orbit power of solar battery array can decay.In addition earth light and celestial body are blocked can also affect
The in-orbit power of solar battery array.
Solar battery array output Orbital detection result can provide accurately in-orbit actual measurement foundation for design of satellites,
Full and accurate Data safeguard is provided for in-orbit use of satellite.From the drop coefficient that declines that in-orbit data analysiss are obtained, it is to defend the long-life
When star is designed, the design of sun battle array is supported there is provided reliable data, especially when the lifetime of satellite requires more and more longer, accurate reliable
The in-orbit data analysiss of sun battle array even more important.
Existing satellite without for IV curves special Orbital detection circuit, but using existing solar battery array electric current,
Busbar voltage and solar battery array remote temperature sensing etc. (as shown in Figure 1) data are analyzed process, and the method is utilized in sun electricity
The solar battery array output current that pond battle array deferent segment is adopted, the busbar voltage that adopts in primary power source bus and in solar cell
The critesistor collection correlation remote measurement that arranges in battle array.When sunlight is on solar battery array, microprocessor gathers the sun
The remote measurements such as cell array electric current, busbar voltage and solar battery array temperature are packaged into remote measurement bag, are sent to communication module per 1s, pass through
On-board processing module, star ground communication unit reach ground.Ground staff is according to the solar battery array electric current under in-orbit different mode
Telemetry, remote temperature sensing data and attitude data are calculated, and reject angle of incidence, the solar distance factor by method for normalizing
Deng the impact to solar battery array, so as to obtain the drop coefficient that declines.
In sum, complete IV curves (as shown in Figure 2) should be included from open-circuit voltage point until short circuit current flow point
Total data.And the data sampling point of existing method is few, the voltage x current of operating point is basicly stable constant, obtains data and is only
The several points isolated on IV curves, it is impossible to IV curves directly perceived, comprehensively reflecting whole piece solar cell, cannot more provide quantitative point
The total data that the solar battery array degradation of analysis institute needs.
In Fig. 5, abscissa is solar battery array output voltage, and vertical coordinate is solar battery array output current, and dotted line is whole piece
IV curve synoptic diagrams, circular segment are in-orbit solar battery array output voltage current datas.Obtained according to existing method in Fig. 5
Measurement result, is not a complete test curve, but operating point electricity of solar battery array when being operated in a busbar voltage
Current voltage, slightly changes with load change.Because a busbar voltage is regulated and controled in 28.5V ± 1V scopes by power-supply controller of electric
Interior, in Fig. 5 scope pointed by M be solar battery array output voltage in the range of 28.5V ± 1V when, corresponding partial trace exists
Position on IV curves.The partial trace is only a part for whole piece IV curves, it is impossible to show short circuit current flow, open-circuit voltage
Change, cannot more show overall drift of the solar battery array with IV curves caused by the change such as temperature, in-orbit life-span.Such as work as temperature
During change, IV curve constant current sections will shorten, while open-circuit voltage point is moved to left, but due to ensure that work when solar battery array is designed
Point can be operated in constant current section at different temperatures, then the data that the M in Fig. 5 is represented cannot represent moving to left for IV curves.
Content of the invention
The present invention technology solve problem be：Overcome the deficiencies in the prior art, it is proposed that a kind of Satellite vapour image exists
Rail test circuit, obtains the in-orbit delta data of solar battery array in real time, and the IV curves (Fig. 3) for obtaining can reflect covers short-circuit electricity
Stream, open-circuit voltage, the whole parameters of quiescent potential/electric current, visual assessment solar battery array on-orbit performance obtain in-orbit for a long time flying
Capable attenuation data.
The present invention technical solution be：A kind of Satellite vapour image Orbital detection circuit, including solar battery array,
Information process unit on electronic equipment, star, star ground communication unit on star.
Solar battery array includes the first solar battery array, the second solar battery array.
Electronic equipment on star, including switch switching circuit, temperature measurement circuit, IV test circuits, analog-digital converter, microprocessor
Device, communication module.
Wherein IV test circuits include voltage collection circuit, current collection circuit, load regulation circuit.
On outside star, electrical equipment is connected by primary power source bus and the first solar battery array.
During satellite operation on orbit, the first solar battery array is by after sunlight, to primary power source bussed supply, second too
Positive cell array is switched on-off circuit by after sunlight to primary power source bussed supply under the control of switching on-off circuit
Original state be that the second solar battery array is connected on primary power source bus, i.e., switching on-off circuit original state realize
First solar battery array and the second solar battery array are to primary power source bussed supply；
, in original state, current collection circuit is by switch switching circuit from the second solar battery array for switching on-off circuit
The electric current for collecting is 0, and the voltage that relevant voltage Acquisition Circuit is collected is 0, and temperature measurement circuit gathers the second solar battery array
Temperature transition is magnitude of voltage by temperature and be that 0～5V analog quantitys Vo pass to analog-digital converter by the voltage values, modulus turn
Voltage Vo is converted to digital quantity D1 by parallel operation, is then sent to microprocessor；
When communication module is received to go code from the IV test circuits of information process unit transmission on star, microprocessor
Command pulse is sent to switching on-off circuit, switching on-off circuit is switched to test mode, switching on-off circuit is in test shape
During state, the second solar battery array is linked into the current collection circuit in IV test circuits, now the second solar battery array, that is, test
Sun battle array, is connected in IV test circuits, powers to load regulation circuit.
After voltage collection circuit collection is switched under test mode from original state, the voltage of the second solar battery array
Vin, i.e., it is initial time to be just connected to the moment of IV test circuits in the second solar battery array, and Vin starts gradually to rise from 0V
Height, until load regulation circuit charges terminating, now Vin is increased to maximum voltage value, and the maximum voltage value is second sun
The open-circuit voltage of cell array；
After being switched under test mode from original state, current collection circuit gathers the electric current of the second solar battery array
Iin, i.e., the moment for being just connected to IV test circuits in the second solar battery array is initial time, and Iin is from maximum, i.e., second
The short circuit current flow of solar battery array, starts to reduce, until load regulation circuit charges terminating, now Iin is reduced to 0；
After being switched under test mode from original state, the Vin of 0V to maximum voltage value is converted by voltage collection circuit
Analog-digital converter is passed to for 0～5V analog quantitys Vout, voltage Vout is converted to digital quantity D2 by analog-digital converter, delivers to micro- place
Reason device；The current value is transformed to 0～5V analog quantitys and passes to mould by the electric current in current collection circuit collection load regulation circuit
The analog quantity is converted to digital quantity D3 by number converter, analog-digital converter；Temperature measurement circuit gathers the temperature of the second solar battery array,
It is magnitude of voltage by temperature transition and its voltage values is passed to analog-digital converter, analog digital conversion for 0～5V analog quantitys Vo
Voltage Vo is converted to digital quantity D1 by device, is then sent to microprocessor；
Microprocessor, sends command pulse, starts to count when switching on-off circuit is switched to test mode from original state
When, microprocessor by digital quantity D1, D2, D3 component devices remote measurement bag, was then sent out by communication module within each program loop
Give information process unit on star；
On star, information process unit identification judges the equipment remote measurement bag, is then sent to ground survey by star ground communication unit
Examination equipment, after ground checkout equipment receives the equipment remote measurement bag, decoding obtains temperature under the solar battery array test mode, defeated
Go out voltage, output current, choose at multiple temperature, the continuous data in the temperature that collects, output voltage, output current is painted
Make the IV curves of the solar battery array.
Each program loop described is 1s.
Multiple temperature of the selection include 0 DEG C, 20 DEG C, 60 DEG C, 90 DEG C.
The temperature measurement circuit includes critesistor RT and divider resistance R5, divider resistance R5 one end of temperature measurement circuit and+5V
Control source is connected, and the other end of divider resistance R5, used as the output end vo of temperature measurement circuit, one end phase with critesistor RT
Even, the other end of critesistor RT is connected with signal ground, and output end vo is connected with analog-digital converter；
Switch switching circuit includes switching switch K1, and switching switch K1 is single-pole double-throw switch (SPDT)；Switching switch K1's is motionless
The positive pole of the second solar battery array of end connection；Second moved end of switching switch K1, connects first respectively by primary power source bus
The positive pole of electrical equipment on the positive pole of solar battery array and outside star；On outside star, the negative pole of electrical equipment connects first too respectively
The negative pole of positive cell array and the negative pole of the second solar battery array；
Current collection circuit includes sampling resistor R1 and operational amplifier, and the first of one end connection switching switch K1 of R1 moves
End, one end Vin of resistance R2 in the other end connection voltage collection circuit of R1, and the two ends of R1 are input into operational amplifier respectively
End is connected, and operational amplifier output is connected with analog-digital converter；The power positive end V+ connection+12V of operational amplifier, power supply negative terminal
V- connection -12V；
Voltage collection circuit includes resistance R2, resistance R3；The other end phase of voltage collection circuit resistance R2 one end Vin and R1
Even, the other end Vout of resistance R2 is connected with one end of resistance R3 and analog-digital converter respectively；The other end of resistance R3 respectively with
One end of resistance R4 is connected with the negative pole of the second solar battery array；
Load regulation circuit, the one end including resistance R4, electric capacity C1 and electric capacity C2, one end of electric capacity C1 and electric capacity C2 connect
The other end of resistance R2 one end Vin, the other end of electric capacity C1 and electric capacity C2 connects the other end of resistance R4.
High precision operating amplifier of the current collection circuit from Xi'an microelectric technique institute, model
OP07.
The sampling resistor R1 that the current collection circuit is chosen chooses 2m Ω～10m Ω.The electricity that voltage collection circuit is chosen
Resistance R2 and R3 resistances select to meet the maximum voltage that R3 two ends partial pressure obtains and are less than 5V.The resistance R4 choosings of load regulation circuit
Take 0.5 Ω～2 Ω.
The electric capacity C1 and C2 of the load regulation circuit chooses 470 μ F.
Second solar battery array is made up of a string of solar cells, single string sun of total tablet number and the first solar battery array
Cell piece number is identical；The solar cell monomer that first solar battery array and the second solar battery array are selected is consistent, can meet directly
Requirement to a bussed supply.
Present invention advantage compared with prior art is：
(1) present invention utilizes electronic equipment such as microprocessor, temperature measurement circuit, remote measurement transmission channel on star, in conjunction with voltage
Collection, current acquisition and load regulation circuit, there is provided a kind of solar battery array Orbital detection circuit design method.The electricity for using
Sub- equipment acquisition precision is high, and input and output are controllable.The second solar battery array is accessed after IV test circuits by switching switch, profit
With the charge characteristic of electric capacity in load regulation circuit, realize each point on solar battery array IV curves (short circuit current flow, open-circuit voltage,
Quiescent potential electric current) collection.
(2) IV test circuits of the present invention can be realized accessing and exiting by being remotely-controlled the switch switching circuit of instruction control.
As ensure satellite main task, the second solar battery array is accessed by the telecommand independently sent on ground or star female
Line, for the solar battery array electric current that load operation provides maximum；Only do not work in load, or solar battery array electric current has affluence
During amount, just the second solar battery array is accessed Orbital detection circuit by the telecommand by independently sending on ground or star, is carried out
IV curves are tested.
(3) variation characteristic of the present invention using transient switching during load regulation circuit capacitance C1, C2 discharge and recharge to open circuit, real
The now collection to whole piece IV curves from short circuit current flow to open-circuit voltage, bent as IV is obtained without the need for additionally increasing adjustable electronic load
The solar battery array load of line, saves the device space, and control circuit principle is simple, safe and reliable, with low cost, it is adaptable to all kinds of
The satellite of solar battery array is installed.
(4) the in-orbit delta data of the solar battery array of present invention acquisition in real time includes solar battery array output voltage, electric current
With solar battery array temperature.The IV curves for obtaining can reflect that to cover short circuit current flow, open-circuit voltage, quiescent potential/electric current complete
Portion's parameter, be a complete IV curve, can visual assessment solar battery array on-orbit performance, obtain in-orbit flight for a long time and decline
Subtrahend evidence.
(5) present invention sends instruction controlling switch switching circuit K1 by microprocessor and can realize that solar battery array is tested
The access of circuit and exit.Only do not work in load, or solar battery array electric current is when having surplus, just by ground or star
Second solar battery array is accessed Orbital detection circuit by the telecommand for independently sending, and carries out IV curve tests.
(6) the first solar battery array of the invention and the second solar battery array are independent two parts, the first solar battery array
Dedicated for power supply, the second solar battery array realizes the purpose for taking into account power supply and Orbital detection by switch switching circuit K1.For
Ensure satellite main task, when load operation, two parts solar battery array accesses bus, maximum is provided for load operation
Solar battery array electric current.
Description of the drawings
Fig. 1 is existing satellite solar cell current/voltage Acquisition Circuit topological structure schematic diagram；
Fig. 2 is the preferable solar battery array IV curve charts of solar cell Orbital detection circuit of the invention；
Fig. 3 is the solar cell Orbital detection circuit topological structure schematic diagram of the present invention；
Fig. 4 is the solar cell Orbital detection circuit design schematic diagram of the present invention；
Fig. 5 is position view of the data of prior art collection on IV curves；
Fig. 6 is the schematic diagram that IV curves are varied with temperature.
Specific embodiment
Below in conjunction with the accompanying drawings and specific embodiment that the present invention is described in detail is as follows.
As shown in figure 3, the Satellite vapour image Orbital detection circuit of the present invention includes that electronics sets on solar battery array, star
Information process unit, star ground communication unit on standby, star；Solar battery array includes the first solar battery array, the second solar battery array；
Electronic equipment on star, including switch switching circuit, temperature measurement circuit, IV test circuits, analog-digital converter, microprocessor, communication mould
Block.Wherein IV test circuits include voltage collection circuit, current collection circuit, load regulation circuit, electrical equipment on outside star
Connected by primary power source bus and the first solar battery array.The electronic equipment acquisition precision that the present invention is used is high, input and output
Controllable.The second solar battery array is accessed after IV test circuits by switching switch, filled using electric capacity in load regulation circuit
Electrical characteristics, realize the collection of each point on solar battery array IV curves (short circuit current flow, open-circuit voltage, quiescent potential electric current).
After communication module receives on star information process unit instruction, microprocessor sends instruction and first connects IV test circuits
Switch, testing solar battery is switched in IV test circuits from bus.Charged for load capacitance by IV test circuits；Voltage is adopted
Collector collection IV test circuits are powered magnitude of voltage between positive and negative busbar, and the voltage is converted to digital quantity by analog-digital converter；
Current collection circuit gathers IV test circuit supply access current values, and the magnitude of current is converted to digital quantity by analog-digital converter；
Microprocessor is constantly stored in voltage, current digital amount in data storage.When the voltage digital amount that microprocessor is collected
Drop to 0V and continue constant after, then send instruction and disconnect IV test circuits switch, testing solar battery is linked to bus.Micro-
Above-mentioned digital quantity is packed in processor, remote measurement bag is sent to by information process unit on star by communication module；Information on star
The remote measurement bag containing voltage true form that the equipment sends is packaged after process by processing unit, is sent to star ground communication unit
The remote measurement bag of information process unit output on star is sent to ground checkout equipment by unit, star ground communication unit.Second solar cell
Battle array main track passes through to be powered anode by switching on-off circuit and be connected to testing capacitor circuit, and the second solar battery array negative wire is directly connected to
Power on negative terminal to testing capacitor circuit, voltage collection circuit is connected between positive negative wire, and current collection circuit is connected on main track
On.
As shown in figure 4, described solar battery array includes the first solar battery array and the second solar battery array, first sun
Cell array is used for being power satellite that the second solar battery array to be used for power satellite and IV curves are tested.First sun electricity of the invention
Chi Zhen and the second solar battery array are independent two parts, the first solar battery array dedicated for power supply, the second solar battery array
The purpose for taking into account power supply and Orbital detection is realized by switch switching circuit K1.It is intended that for ensureing satellite main task,
When load operation, two parts solar battery array accesses bus, for the solar battery array electric current that load operation provides maximum.
The temperature measurement circuit includes critesistor RT and divider resistance R5, divider resistance R5 one end of temperature measurement circuit and+5V
Control source is connected, and the other end of divider resistance R5, used as the output end vo of temperature measurement circuit, one end phase with critesistor RT
Even, the other end of critesistor RT is connected with signal ground, and output end vo is connected with analog-digital converter；Temperature measurement circuit achieves temperature
The Real-time Collection of data, there is provided the solar cell temperature data of IV curve plottings, can detect solar cell under different temperatures
Battle array performance data.
Switch switching circuit includes switching switch K1, and switching switch K1 is single-pole double-throw switch (SPDT)；Switching switch K1's is motionless
The positive pole of end connection solar battery array 2；Second moved end of switching switch K1, connects solar cell respectively by primary power source bus
The positive pole of electrical equipment on the positive pole of battle array 1 and outside star；On outside star, the negative pole of electrical equipment connects solar battery array 1 respectively
Negative pole and the negative pole of solar battery array 2.Switch switching circuit achieve the second solar battery array for power supply and test two kinds
Pattern switching, is effectively utilized the limited resource of satellite, has taken into account power supply and test function.As ensure satellite main task,
Second solar battery array is accessed by bus by the telecommand independently sent on ground or star, maximum is provided for load operation
Solar battery array electric current；Only do not work in load, or solar battery array electric current be when having surplus, just by ground or star from
Second solar battery array is accessed Orbital detection circuit by the telecommand that master sends, and carries out IV curve tests.
Current collection circuit includes sampling resistor R1 and operational amplifier, and the first of one end connection switching switch K1 of R1 moves
End, one end Vin of resistance R2 in the other end connection voltage collection circuit of R1, and the two ends of R1 are input into operational amplifier respectively
End is connected, and operational amplifier output is connected with analog-digital converter, the power positive end V+ connection+12V of operational amplifier, power supply negative terminal
V- connection -12V；Current collection circuit achieves the high speed of solar battery array supply current, high precision collecting.
Voltage collection circuit includes resistance R2, resistance R3；The other end phase of voltage collection circuit resistance R2 one end Vin and R1
Even, the other end Vout of resistance R2 is connected with one end of resistance R3 and analog-digital converter respectively；The other end of resistance R3 respectively with
One end of resistance R4 is connected with the negative pole of solar battery array 2；Voltage collection circuit achieves the height of solar battery array supply voltage
Speed, high precision collecting.
Load regulation circuit includes one end connection of resistance R4, electric capacity C1 and electric capacity C2, one end of electric capacity C1 and electric capacity C2
The other end of resistance R2 one end Vin, the other end of electric capacity C1 and electric capacity C2 connects the other end of resistance R4.Load regulation circuit is made
For the load regulation part of IV test circuits, it is achieved that whole exporting change of the solar battery array from short circuit current flow to open-circuit voltage
Process.Using the variation characteristic of transient switching during load regulation circuit capacitance C1, C2 discharge and recharge to open circuit, realize bent to whole piece IV
Collection of the line from short circuit current flow to open-circuit voltage, without the need for additionally increasing adjustable electronic load as the solar cell for obtaining IV curves
Battle array load, saves the device space, and control circuit principle is simple, safe and reliable, with low cost, it is adaptable to all kinds of be provided with sun electricity
The satellite of Chi Zhen.
The course of work of circuit of the present invention is：
During satellite operation on orbit, solar battery array 1 by after sunlight to primary power source bussed supply, solar battery array
2, by after sunlight, to primary power source bussed supply under the control of switching on-off circuit, switch the initial shape of on-off circuit
State is that solar battery array 2 is connected on primary power source bus, i.e. the original state of switching on-off circuit realizes solar battery array 1
With solar battery array 2 to primary power source bussed supply.
Switching on-off circuit in original state, adopted from solar battery array 2 by switch switching circuit by current collection circuit
The electric current for collecting is 0, and the voltage that relevant voltage Acquisition Circuit is collected is 0, and temperature measurement circuit gathers the temperature of solar battery array 2,
It is magnitude of voltage by temperature transition and the voltage values is passed to analog-digital converter, analog-digital converter for 0～5V analog quantitys Vo
Voltage Vo is converted to digital quantity D1, microprocessor is then sent to.
When communication module is received to go code from the IV test circuits of information process unit transmission on star, microprocessor
Command pulse is sent to switching on-off circuit, switching on-off circuit is switched to test mode, switching on-off circuit is in test shape
During state, solar battery array 2 is linked into the current collection circuit in IV test circuits, now solar battery array 2, that is, test the sun
Battle array, is connected in IV test circuits, powers to load regulation circuit.
After voltage collection circuit collection is switched under test mode from original state, the voltage Vin of solar battery array 2,
It is initial time to be just connected to the moment of IV test circuits in solar battery array 2, and Vin starts to gradually rise from 0V, until
Load regulation circuit charges and terminates, and now Vin is increased to maximum voltage value, and the maximum voltage value is opening for solar battery array 2
Road voltage.
After being switched under test mode from original state, current collection circuit gathers the electric current Iin of solar battery array 2,
The moment for being just connected to IV test circuits in solar battery array 2 is initial time, and Iin is from maximum, i.e. solar battery array 2
Short circuit current flow, start to reduce, until load regulation circuit charge terminate, now Iin is reduced to 0.
After being switched under test mode from original state, the Vin of 0V to maximum voltage value is converted by voltage collection circuit
Analog-digital converter is passed to for 0～5V analog quantitys Vout, voltage Vout is converted to digital quantity D2 by analog-digital converter, delivers to micro- place
Reason device；The current value is transformed to 0～5V analog quantitys and passes to mould by the electric current in current collection circuit collection load regulation circuit
The analog quantity is converted to digital quantity D3 by number converter, analog-digital converter；Temperature measurement circuit gathers the temperature of solar battery array 2, will
Temperature transition is magnitude of voltage and its voltage values is passed to analog-digital converter, analog-digital converter for 0～5V analog quantitys Vo
Voltage Vo is converted to digital quantity D1, microprocessor is then sent to.
Microprocessor sends command pulse, starts to count when switching on-off circuit is switched to test mode from original state
When, microprocessor by digital quantity D1, D2, D3 component devices remote measurement bag, was then sent out by communication module within each program loop
Give information process unit on star.
On star, information process unit identification judges the equipment remote measurement bag, is then sent to ground survey by star ground communication unit
Examination equipment, after ground checkout equipment receives the equipment remote measurement bag, decoding obtains temperature under the solar battery array test mode, defeated
Go out voltage, output current, choose at multiple temperature, the continuous data in the temperature that collects, output voltage, output current is painted
Make the IV curves of the solar battery array.
The IV J curve effectJs that the present invention is collected are as shown in Fig. 2 can be with continuous acquisition no less than 1000 points, so as to obtain
Whole exporting change process IV curve from short circuit current flow to open-circuit voltage, the measurement data obtained than existing method is (such as Fig. 5 institutes
Show) more full and accurate.
In Fig. 2, abscissa is solar battery array output voltage, and vertical coordinate is solar battery array output current.The starting point of curve
It is that the short circuit current flow point of the leftmost side, i.e. solar battery array output voltage are 0V, solar battery array output current is maximum.Afterwards
Solar battery array output voltage gradually increases, until it reaches the open-circuit voltage point of the curve rightmost side, i.e. solar battery array output electricity
Press as maximum, solar battery array output current is 0.From on the IV curves that Fig. 2 is obtained, short circuit current flow, open circuit electricity can be shown
Pressure point, can be calculated the sign sun electricity such as quiescent potential, electric current, maximum power point voltage, electric current by reading data
The characteristic point of pond battle array IV curve.Sampled point number that the curve is included, characteristic point information are more than prior art.When sun electricity
Pond battle array performance by temperature, in orbit time, spatial environmentss affected and decline drop when, features described above point (short circuit current flow point, open circuit
Electrical voltage point, quiescent potential, operating point electric current, maximum power point voltage, maximum power point electric current) can intactly characterize IV songs
Line drift trend.On the one hand data full and accurate in a large number are obtained, another aspect visual assessment solar battery array performance change is grown
The attenuation data of phase in-orbit flight.
So that IV curves are with temperature drift as an example, as solar battery array ensures that quiescent potential, electric current in design
Keep constant at different temperatures, but open-circuit voltage can be moved to left as temperature is raised, while maximum power point position moves to left.
Fig. 6 is the schematic diagram that the IV curves of solar cell are varied with temperature.In Fig. 6, abscissa is solar battery array output voltage, indulges and sits
Mark is solar battery array output current, and T represents that the operating temperature of solar cell, the direction of arrow of T represent that temperature gradually rises.Such as
IV curves shown in Fig. 6 are raised with temperature, and constant current section shortens, and open-circuit voltage point is moved to left.Complete IV curve is only symbolized
Method just can show such change, possess the irrealizable function of existing method (as shown in Figure 5).
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (8)
1. a kind of Satellite vapour image Orbital detection circuit, it is characterised in that：Including electronic equipment on solar battery array, star,
Information process unit, star ground communication unit on star；
Solar battery array includes the first solar battery array, the second solar battery array；
Electronic equipment on star, including switch switching circuit, temperature measurement circuit, IV test circuits, analog-digital converter, microprocessor, logical
Letter module；
Wherein IV test circuits include voltage collection circuit, current collection circuit, load regulation circuit；
On outside star, electrical equipment is connected by primary power source bus and the first solar battery array；
During satellite operation on orbit, the first solar battery array is by after sunlight, to primary power source bussed supply, second sun is electric
Chi Zhen is switched the first of on-off circuit by after sunlight to primary power source bussed supply under the control of switching on-off circuit
Beginning state is that the second solar battery array is connected on primary power source bus, i.e. the original state of switching on-off circuit realizes first
Solar battery array and the second solar battery array are to primary power source bussed supply；
In original state, current collection circuit is gathered from the second solar battery array switching on-off circuit by switch switching circuit
The electric current for arriving is 0, and the voltage that relevant voltage Acquisition Circuit is collected is 0, and temperature measurement circuit gathers the temperature of the second solar battery array,
It is magnitude of voltage by temperature transition and the voltage values is passed to analog-digital converter, analog-digital converter for 0～5V analog quantitys Vo
Voltage Vo is converted to digital quantity D1, microprocessor is then sent to；
When communication module receives the IV test circuits that send from information process unit on star to go code, microprocessor is to cutting
Change on-off circuit and send command pulse, switching on-off circuit is switched to test mode, switching on-off circuit in test mode,
Second solar battery array is linked into the current collection circuit in IV test circuits, now the second solar battery array, that is, test the sun
Battle array, is connected in IV test circuits, powers to load regulation circuit；
After voltage collection circuit collection is switched under test mode from original state, the voltage Vin of the second solar battery array, i.e.,
The moment for being just connected to IV test circuits in the second solar battery array is initial time, and Vin starts to gradually rise from 0V, until
Load regulation circuit charges and terminates, and now Vin is increased to maximum voltage value, and the maximum voltage value is the second solar battery array
Open-circuit voltage；
After being switched under test mode from original state, current collection circuit gathers the electric current Iin of the second solar battery array, i.e.,
The moment that IV test circuits have just been connected in the second solar battery array is initial time, and Iin is from maximum, i.e. second sun electricity
The short circuit current flow of Chi Zhen, starts to reduce, until load regulation circuit charges terminating, now Iin is reduced to 0；
After being switched under test mode from original state, the Vin of 0V to maximum voltage value is transformed to 0 by voltage collection circuit～
5V analog quantitys Vout pass to analog-digital converter, and voltage Vout is converted to digital quantity D2, delivers to microprocessor by analog-digital converter；
The current value is transformed to 0～5V analog quantitys and passes to modulus turn by the electric current in current collection circuit collection load regulation circuit
The analog quantity is converted to digital quantity D3 by parallel operation, analog-digital converter；Temperature measurement circuit gathers the temperature of the second solar battery array, by temperature
Degree is converted to magnitude of voltage and its voltage values is passed to analog-digital converter for 0～5V analog quantitys Vo, and analog-digital converter will
Voltage Vo is converted to digital quantity D1 ', is then sent to microprocessor；
Microprocessor, sends command pulse, starts timing when switching on-off circuit is switched to test mode from original state, micro-
Processor by digital quantity D1 ', D2, D3 component devices remote measurement bag, was then sent to by communication module within each program loop
Information process unit on star；
On star, information process unit identification judges the equipment remote measurement bag, is then sent to ground test by star ground communication unit and sets
Standby, after ground checkout equipment receives the equipment remote measurement bag, decode temperature, the output electricity obtained under the solar battery array test mode
Pressure, output current, choose at multiple temperature, the continuous data in the temperature that collects, output voltage, output current, and drawing should
The IV curves of solar battery array.
2. a kind of Satellite vapour image Orbital detection circuit according to claim 1, it is characterised in that：Each program week
Phase is 1s.
3. a kind of Satellite vapour image Orbital detection circuit according to claim 1, it is characterised in that：That chosen is multiple
Temperature includes 0 DEG C, 20 DEG C, 60 DEG C, 90 DEG C.
4. a kind of Satellite vapour image Orbital detection circuit according to claim 1, it is characterised in that：The thermometric electricity
Road includes that critesistor RT and divider resistance R5, divider resistance R5 one end of temperature measurement circuit are connected with+5V control sources, partial pressure electricity
The other end of resistance R5, as the output end vo of temperature measurement circuit, is connected with one end of critesistor RT, the other end of critesistor RT
It is connected with signal ground, output end vo is connected with analog-digital converter；
Switch switching circuit includes switching switch K1, and switching switch K1 is single-pole double-throw switch (SPDT)；The not moved end of switching switch K1 connects
Connect the positive pole of the second solar battery array；Second moved end of switching switch K1, connects first sun respectively by primary power source bus
The positive pole of electrical equipment on the positive pole of cell array and outside star；On outside star, the negative pole of electrical equipment connects first sun electricity respectively
The negative pole of Chi Zhen and the negative pole of the second solar battery array；
Current collection circuit includes that sampling resistor R1 and operational amplifier, one end connection switching of R1 switch first moved end of K1,
One end Vin of resistance R2 in the other end connection voltage collection circuit of R1, and the reverse input of one end of R1 and operational amplifier
End is connected, and the other end of R1 is connected with the input in the same direction of operational amplifier, and operational amplifier output is connected with analog-digital converter,
The power positive end V+ connection+12V of operational amplifier, power supply negative terminal V- connection -12V；
Voltage collection circuit includes resistance R2, resistance R3；Voltage collection circuit resistance R2 one end Vin are connected with the other end of R1,
The other end Vout of resistance R2 is connected with one end of resistance R3 and analog-digital converter respectively；The other end of resistance R3 respectively with resistance
One end of R4 is connected with the negative pole of the second solar battery array；
Load regulation circuit, including one end connection resistance of resistance R4, electric capacity C1 and electric capacity C2, one end of electric capacity C1 and electric capacity C2
The other end of R2 one end Vin, the other end of electric capacity C1 and electric capacity C2 connects the other end of resistance R4.
5. a kind of Satellite vapour image Orbital detection circuit according to claim 4, it is characterised in that：Current acquisition electricity
High precision operating amplifier of the operational amplifier that road is chosen from Xi'an microelectric technique institute, model OP07.
6. a kind of Satellite vapour image Orbital detection circuit according to claim 4, it is characterised in that：Current acquisition electricity
The sampling resistor R1 that road is chosen selects 2m Ω～10m Ω, the resistance R2 and R3 resistance that voltage collection circuit is chosen to select to meet
The maximum voltage that R3 two ends partial pressure is obtained is less than 5V, and the resistance R4 of load regulation circuit chooses 0.5 Ω～2 Ω.
7. a kind of Satellite vapour image Orbital detection circuit according to claim 4, it is characterised in that：Load regulation electricity
The electric capacity C1 and C2 on road chooses 470 μ F.
8. a kind of Satellite vapour image Orbital detection circuit according to claim 1 or 4, it is characterised in that：Second too
Positive cell array is composed in series a string of solar cells by multi-disc solar cell, the first solar battery array by go here and there more solar cell in parallel and
Into often string solar cell is composed in series by multi-disc solar cell；The total tablet number and the first solar battery array of the second solar battery array
A string of solar cell piece numbers identical；The complete phase of every solar cell that first solar battery array and the second solar battery array are selected
With, making the first solar battery array and the second solar battery array output voltage unanimously, satisfaction is directly to primary power source bussed supply
Require.
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| CN107332511A (en) * | 2017-05-18 | 2017-11-07 | 上海卫星工程研究所 | The solar cell array simulation system and its monitoring method of satellite standard |
| CN107703353B (en) * | 2017-09-11 | 2020-04-07 | 北京空间飞行器总体设计部 | Spacecraft solar wing on-orbit full-life-cycle output power prediction method and system |
| CN108183474B (en) * | 2017-12-26 | 2020-08-14 | 航天东方红卫星有限公司 | Construction method of ground power supply and distribution test equipment for small satellite combined power supply |
| CN108549355B (en) * | 2018-03-16 | 2019-11-19 | 西北工业大学 | A kind of cube star generalization ground fast testing system |
| CN108957176B (en) * | 2018-06-20 | 2021-04-06 | 上海卫星工程研究所 | Analog array standard type automatic testing method |
| CN109254213B (en) * | 2018-10-12 | 2021-03-16 | 合肥阳光新能源科技有限公司 | Electrical property detection device and method for intelligent assembly |
| CN109687824B (en) * | 2018-12-06 | 2020-06-02 | 上海空间电源研究所 | On-orbit satellite solar cell circuit working state monitoring method |
| CN110988688A (en) * | 2019-12-10 | 2020-04-10 | 中国电子科技集团公司第十八研究所 | Circuit system of satellite carried reference single solar cell |
| CN111337779A (en) * | 2020-03-26 | 2020-06-26 | 上海精密计量测试研究所 | Component on-orbit flight evaluation verification method |
| CN112953386B (en) * | 2021-03-17 | 2024-01-26 | 中国科学院微小卫星创新研究院 | Method for measuring volt-ampere characteristic of solar cell array of satellite |
| CN115542823B (en) * | 2022-11-25 | 2023-03-07 | 北京布局未来教育科技有限公司 | Satellite monitoring control circuit |
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| US8159238B1 (en) * | 2009-09-30 | 2012-04-17 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method and apparatus for in-situ health monitoring of solar cells in space |
| US9419558B2 (en) * | 2009-09-30 | 2016-08-16 | The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration | Method and apparatus for in-situ health monitoring of solar cells in space |
| FR3000220B1 (en) * | 2012-12-21 | 2015-02-20 | Astrium Sas | SYSTEM AND METHOD FOR DETECTING AND LOCATING ISOLATION FAULT OF A SPACE-MOUNT SOLAR GENERATOR |
| CN103235270B (en) * | 2013-04-15 | 2015-02-18 | 北京空间飞行器总体设计部 | Reliability testing device for star power system of lunar probe |
| CN104378067A (en) * | 2014-11-05 | 2015-02-25 | 北京卫星环境工程研究所 | Solar cell module unit elemental oxygen effect testing system |
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