CN107861086A - A kind of in-orbit calibration method of current sensor applied to space and device - Google Patents
A kind of in-orbit calibration method of current sensor applied to space and device Download PDFInfo
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- CN107861086A CN107861086A CN201711443210.8A CN201711443210A CN107861086A CN 107861086 A CN107861086 A CN 107861086A CN 201711443210 A CN201711443210 A CN 201711443210A CN 107861086 A CN107861086 A CN 107861086A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R35/00—Testing or calibrating of apparatus covered by the other groups of this subclass
- G01R35/005—Calibrating; Standards or reference devices, e.g. voltage or resistance standards, "golden" references
Abstract
The invention discloses a kind of in-orbit calibration method of current sensor applied to space and device, wherein calibrating installation to include：Encourage input module, current sensor, remote-control romote-sensing module；The excitation input module is connected with the current sensor, for exporting the exciting current signal of known amplitude to the current sensor according to default calibration intervals；The current sensor and prediction connection, for measuring the magnitude of current of the prediction circuit, and the electric signal that the magnitude of current is converted into be measured by the remote-control romote-sensing module；The remote-control romote-sensing module is connected with the current sensor, is compared for monitoring the numerical value change of the electric signal, and by the numerical value change and the known amplitude, obtains the error that the current sensor shows numerical value.The calibrating installation can lift the reliability of long-life space current sensor work and the ability of accuracy, the correlated performance change of current sensor after more directly reacting in orbit.
Description
Technical field
The present invention relates to space technology collimation technique field, exists more particularly to a kind of current sensor applied to space
Rail calibration method and device.
Background technology
Current measurement is a kind of significant data monitoring means during spacecraft running status, and current sensor is then
Spacecraft supplies measurement apparatus important in distribution subsystem.Space station, deep space probe engineering in, current sensor is having
Higher job requirement is proposed in effect working life, it is necessary to periodically in-orbit calibration.
However, actual conditions are current sensor longtime runnings after Spacecraft Launch is entered the orbit, it is no longer regular during this period
Calibration, or even ground very long AIT periods before transmission, cannot also be calibrated, the confidence level of its measurement result has risk.
Prove that its accuracy of measurement can not change in space environment currently without data and priori, can not prove that electric current passes
The performance indications of the long-term operation on orbit of sensor are consistent with ground.By current sensor in the calibrating operation on ground and in space environment
Calibrating operation caused by deviation be included in error range, if this cumulative errors can not calibrate in time, it would be possible to bring serious
Consequence.These errors are influenceed to caused by short-term space mission and unobvious, but in long-term space mission, if can not
Enough periodic calibrations, over time, the error of current sensor and drift will cause uncertainty of measurement to significantly increase, this
Risk will be brought to space mission decision-making.Space mission drop volume will be caused when serious or shorten the life-span.
If traditional current sensor calibration method is simply transplanted on spacecraft platform, be faced with huge transmitting into
Sheet and maintenance cost cost.
The content of the invention
The present invention proposes a kind of in-orbit calibrating installation of space current sensor that method is rung based on excitation, its general principle
It is the input to increment known to current sensor application, is responded by the increment in former measuring system, with current sensor coefficient
Theoretical incremental raio is compared with the deviation of calculating current sensor coefficient.
Specifically the invention provides a kind of in-orbit calibrating installation of the current sensor applied to space, including：Encourage defeated
Enter module, current sensor, remote-control romote-sensing module；
The excitation input module is connected with the current sensor, for according to default calibration intervals to the current sense
Device exports the exciting current signal of known amplitude；
The current sensor and prediction connection, for measuring the magnitude of current of the prediction circuit, and by the magnitude of current
It is converted into the electric signal that can be measured by the remote-control romote-sensing module；
The remote-control romote-sensing module is connected with the current sensor, for monitoring the numerical value change of the electric signal, and by institute
State numerical value change and the known amplitude compares, obtain the error that the current sensor shows numerical value.
Preferably, the excitation input module includes timed activation unit, relay and reference current source；
The timed activation unit links with relay, the break-make of control relay, and the timed activation unit is used for according to institute
Default calibration intervals are stated, activation command is sent to the relay；
The relay is used to be closed according to the activation command of the timed activation unit, to activate the reference current source work
Make；
The reference current source is connected with the relay, for being activated when the relay closes, produces the excitation electricity
Signal is flowed, is loaded onto on the current sensor.
Preferably, the timed activation unit includes counter, digital logic controller, relay drive circuit；
The counter is connected with the digital logic controller, for counting and exporting count signal；
The digital logic controller relay drive circuit connection, for the triggering letter in the count signal and reference clock
Under number, the break-make of the relay is controlled by relay drive circuit according to logic of propositions.
Preferably, the electric current number of remote-control romote-sensing module current sensor according to the error calculation of acquisition
Value, and the current values are sent to earth station.
Preferably, the prediction circuit is the battery charging and discharging branch road of spacecraft power supply system, described branch road one end and electricity
Source bus connection, the other end are connected with battery.
Another aspect of the present invention, a kind of in-orbit calibration method of the current sensor applied to space is additionally provided, including
Following steps：
The exciting current signal of known amplitude is exported to current sensor according to default calibration intervals；
The magnitude of current of measurement prediction circuit, and the electric signal that the magnitude of current is converted into being measured；
The numerical value change of the electric signal is monitored, and the numerical value change and the known amplitude are compared, obtains the electric current
Sensor shows the error of numerical value.
Preferably, according to the error calculation of acquisition current sensor current values, and by the electric current number
Value is sent to earth station.
Preferably, the prediction circuit is the battery charging and discharging branch road of spacecraft power supply system, described branch road one end and electricity
Source bus connection, the other end are connected with battery.
Compared with prior art, beneficial effects of the present invention are as follows：
The in-orbit calibrating installation of a kind of current sensor applied to space provided by the invention, including：Encourage input module, electric current
Sensor, remote-control romote-sensing module；
The excitation input module is connected with the current sensor, for according to default calibration intervals to the current sense
Device exports the exciting current signal of known amplitude；
The current sensor and prediction connection, for measuring the magnitude of current of the prediction circuit, and by the magnitude of current
It is converted into the electric signal that can be measured by the remote-control romote-sensing module；
The remote-control romote-sensing module is connected with the current sensor, for monitoring the numerical value change of the electric signal, and by institute
State numerical value change and the known amplitude compares, obtain the error that the current sensor shows numerical value.
The present invention provides a kind of based on the in-orbit calibrating installation of space current sensor for encouraging corresponding method.In setting for NASA
Count in the in-orbit collimation technique means that guide proposes, with reference to " providing embedded reference data on Chosen Point in range is operated ", " make
Can be compared with many types of various sensor " and " by software correction and adjustment " three kinds of technological means, and utilize electric current
The characteristics of pick up calibration, proposition carry out the method that current sensor calibrating installation calibrated, the device with exciter response method
With advantages below and effect：
1）In face of the influence of spatial complex environment, the device is applicable to grow in-orbit cycle spacecraft, is a kind of space electric current
The in-orbit calibrating installation of sensor, the periodic calibration operation of manpower-free, platform is estimated relative to ground experiment, can more directly be reacted
The correlated performance change of current sensor after in orbit.
2）The device possesses the reliability of lifting long-life space current sensor work and the ability of accuracy.Pass through
Null offset and deviation from linearity to current sensor are modified, and realize the accurate measurement of spacecraft current parameters, and will be long
Phase, caused error and drift realization were estimated in orbit, the reliability and accuracy of lifting means work.
Present invention also offers a kind of in-orbit calibration method of the current sensor applied to space, this method can lift longevity
The reliability and the ability of accuracy that life space is worked with current sensor, current sense after more directly reacting in orbit
The correlated performance change of device.
Brief description of the drawings
Fig. 1 is the schematic diagram of current sensor in-orbit calibrating installation in space described herein；
Fig. 2 is the principle schematic of timed activation unit described herein；
Fig. 3 is the structural representation of excitation input module described herein.
Drawing reference numeral and the corresponding relation of each part are as follows：
1 excitation input module,
11 timed activation units,
111 counters,
112 digital logic controllers,
12 relays,
13 reference current sources,
2 current sensors,
3 remote-control romote-sensing modules,
4 prediction circuits,
5 power source bus,
6 batteries.
Embodiment
In order that those skilled in the art more fully understand the present invention program, with reference to the accompanying drawings and detailed description
The present invention is described in further detail.
The invention provides a kind of in-orbit calibrating installation of the current sensor applied to space, a kind of specific embodiment party
Formula, accompanying drawing 1 is refer to, including：Encourage input module, current sensor, remote-control romote-sensing module；
The excitation input module is connected with the current sensor, for defeated to current sensor according to default calibration intervals
Go out the exciting current signal of known amplitude；
Current sensor and prediction connection, for measuring the magnitude of current of prediction circuit, and the magnitude of current is converted into can be distant
Control the electric signal of telemetry module measurement；
Remote-control romote-sensing module is connected with current sensor, for monitoring the numerical value change of electric signal, and by numerical value change and known
Amplitude com parison, obtain the error that current sensor shows numerical value.
The operation principle of the device is as follows：
The device applies the principle on all prediction circuits all identical.Herein, to measure battery current discharge and recharge branch road
Exemplified by current sensor, actuating input unit is loaded onto on the current sensor, is standby in most run times
State, after preset interval of calibration, by timed activation Circuit activation reference current source, produced by reference current source
Pumping signal known to amplitude, is loaded onto on current sensor, the battery current discharge and recharge that remote-control romote-sensing unit passes through monitoring
Excitation signal amplitude known to the reading change and actuating input unit output of branch road is compared, and obtains current sensor indicating value mistake
The deviation situation of difference.
It is provided by the invention a kind of based on the in-orbit calibrating installation of space current sensor for encouraging corresponding method.NASA's
In the in-orbit collimation technique means that design guidelines propose, with reference to " in range operate on Chosen Point provide embed reference data ",
" can be compared using many types of various sensor " and " by software correction and adjustment " three kinds of technological means, and utilize electricity
The characteristics of flow sensor is calibrated, proposition carry out the method that current sensor calibrating installation calibrated, the dress with exciter response method
Put with advantages below and effect：
1）In face of the influence of spatial complex environment, the device is applicable to grow in-orbit cycle spacecraft, is a kind of space electric current
The in-orbit calibrating installation of sensor, the periodic calibration operation of manpower-free, platform is estimated relative to ground experiment, can more directly be reacted
The correlated performance change of current sensor after in orbit.
2）The device possesses the reliability of lifting long-life space current sensor work and the ability of accuracy.Pass through
Null offset and deviation from linearity to current sensor are modified, and realize the accurate measurement of spacecraft current parameters, and will be long
Phase, caused error and drift realization were estimated in orbit, the reliability and accuracy of lifting means work.
In the prior art in spacecraft power supply system, including power source bus, power source bus, which plays, to be collected, distribute and transmits
The effect of electric energy, it is the transmission tie of generating equipment, energy storage device and electrical equipment.
Current sensor is current measuring device, for being converted into the tested magnitude of current to be remotely-controlled remote unit measurement
Electric signal.
Remote-control romote-sensing module is used for the secondary output signal for measuring current sensor, i.e., the electricity of above-mentioned current sensor output
Signal, calculating current indicating value, and send to earth station.
Current sensor is a kind of electrical signal conversion device, it is impossible to independently realizes current measurement function, it is will be tested
Current signal is converted into the voltage signal of corresponding ratio, and this voltage signal is exactly " secondary output signal ", i.e., above-mentioned telecommunications
Number.
Remote-control romote-sensing module measure this " secondary output signal " and with the proportionate relationship phase of preset current sensor
Multiply, electric current indicating value can be calculated.
Input module timing is encouraged to produce to calibrating excitation current signal by school current sensor.It includes three parts,
Timed activation unit, relay and reference current source；
Timed activation unit links with relay, the break-make of control relay, and timed activation unit is used for according to default calibration
Interval, activation command is sent to relay；
Relay is used to be closed according to the activation command of timed activation unit, to activate reference current source work；
Reference current source is connected with relay, for being activated when relay closes, is produced exciting current signal, is loaded onto electric current
On sensor.
During using excitation input module calibration current sensor, output drive current signal is loaded onto simultaneously with normal signal
On current sensor, after preset prover time, turned on by timed activation unit activating relay, reference current source activation,
The pumping signal as known to reference current source produces amplitude, is loaded onto on current sensor.Monitoring is passed through by remote-control romote-sensing unit
Current sensor reading change, and with timed activation unit output known to excitation signal amplitude compare, current sense is calculated
The deviation situation of the device error of indication.
Reference current source is by Zener diode regulator, operational amplifier using precision metallic paper tinsel resistance as sampling feedback
With the voltage feedback type current source of FET composition.
Reference current source is controlled by timed activation unit, timed activation unit include counter, digital logic controller with
Relay drive circuit, that realizes output reference current signal switches on and off function.
Specifically, counter is connected with digital logic controller, for counting and exporting count signal；
Digital logic controller relay drive circuit connects, under the trigger signal of count signal and reference clock, root
Break-make according to logic of propositions by relay drive circuit control relay, so as to realize the connection of output reference current signal and
Break function.
Control principle is as follows：
It refer to accompanying drawing 2, counter, digital logic controller, relay drive circuit connection, for controlling reference current source work
Work or stop working state.The calibration intervals of setting are converted into preset number N, inserted in counter, in the excitation of reference clock
Under, technology its output state, bar of the digital logic controller in counter output signal edging trigger are converted after the n-th cycle
Under part, according to logic of propositions control relay break-make, make reference current source work and output drive current signal, start to calibrate
Journey.
It should be noted that exciting circuit can by any circuit realiration, as long as meet can dormancy, caused exciting current is steady
It is qualitative higher than can be traced to the source by school current sensor, current magnitude.
Optionally, remote-control romote-sensing module is according to the current values of the error calculation current sensor of acquisition, and by electric current number
Value is sent to earth station.
Or error is sent directly to earth station by remote-control romote-sensing module, by the electric current of earth station's calculating current sensor
Numerical value.
The in-orbit calibration of current sensor can be achieved in above two mode, earth station is obtained or is calculated accurately
Current values.
Specifically, prediction circuit can be the battery charging and discharging branch road of spacecraft power supply system, branch road one end is female with power supply
Line is connected, and the other end is connected with battery.
In another specific embodiment, refer to accompanying drawing 2, system include excitation input module, current sensor,
Remote-control romote-sensing module, in addition to power source bus, battery charging and discharging branch road, battery module, the function and relationship description of each module
It is as follows：
Power source bus：In spacecraft power supply system, power source bus plays a part of collecting, distribute and transmitting electric energy, is to generate electricity
The transmission tie of equipment, energy storage device and electrical equipment.
Encourage input module：Input module timing is encouraged to produce to calibrating excitation current signal by school current sensor.
During using excitation input module calibration current sensor, output current signal is loaded onto electric current simultaneously with normal signal
On sensor, after preset prover time, by timed activation Circuit activation reference current source, amplitude is produced by reference current source
Known pumping signal, is loaded onto on current sensor.Changed by remote-control romote-sensing unit by monitoring current sensor reading, and
With excitation input module output known to excitation signal amplitude compare, the deviation situation of the current sensor error of indication is calculated.
Remote-control romote-sensing unit：The secondary output signal of current sensor, calculating current indicating value are measured, and is sent to ground
Stand.
Battery：Spaceborne electric energy energy-storage module.
Battery charging and discharging branch road：Circuit namely to be measured, the charging and discharging currents transmission line of spacecraft power supply system battery,
It is the important component of power-supply system for realizing accumulator cell charging and discharging function.Herein as pre- where the tested magnitude of current
Survey line road.
Current sensor：Current measuring device, for being converted into the tested magnitude of current to be remotely-controlled remote unit measurement
Electric signal.
Above shown in each module relation diagram refer to the attached drawing 3, when carrying out in-orbit calibration, carried out according to following 3 steps：
Step 1：
Above-mentioned each module is after transmitting, and in unmanned maintenance state, excitation input module is in holding state, and timing therein swashs
Encourage circuit and be in timer counter state.
Step 2：
After reaching preset calibration interval period.Input module activation is encouraged, is sent according to preset program to current sensor sharp
Current signal is encouraged, remote-control romote-sensing unit is changed by monitoring current sensor reading.
Step 3：
Compare remote-control romote-sensing unit and measure reading change, by excitation input module output compared with known excitation signal amplitude, meter
Calculation obtains the deviation situation of the current sensor error of indication.
After completing calibration, system returns to step 1 state.
Another aspect of the present invention, a kind of in-orbit calibration method of the current sensor applied to space is additionally provided, including
Following steps：
The exciting current signal of known amplitude is exported to current sensor according to default calibration intervals；
The magnitude of current of measurement prediction circuit, and the electric signal that the magnitude of current is converted into being measured；
The numerical value change of electric signal is monitored, and numerical value change and known amplitude are compared, current sensor is obtained and shows numerical value
Error.
This method can lift the reliability of long-life space current sensor work and the ability of accuracy, can be more direct
The correlated performance change of current sensor after ground reaction in orbit.
Preferably, according to the current values of the error calculation current sensor of acquisition, and current values are sent to ground
Stand；Or error is sent directly to earth station by remote-control romote-sensing module, by the current values of earth station's calculating current sensor.
Specifically, prediction circuit can be the battery charging and discharging branch road of spacecraft power supply system, branch road one end is female with power supply
Line is connected, and the other end is connected with battery.
Prediction circuit can also be All other routes, and the in-orbit calibration of current sensor can be all realized using the calibration method.
In several embodiments that the embodiment of the present invention is provided, it should be understood that disclosed system, device and side
Method, it can realize by another way.For example, device embodiment described above is only schematical, for example, described
The division of unit, only a kind of division of logic function, can there are other dividing mode, such as multiple units when actually realizing
Or component can combine or be desirably integrated into another system, or some features can be ignored, or not perform.It is another, institute
Display or the mutual coupling discussed or direct-coupling or communication connection can be by some interfaces, device or unit
INDIRECT COUPLING or communication connection, can be electrical, mechanical or other forms.
The unit illustrated as separating component can be or may not be physically separate, show as unit
The part shown can be or may not be physical location, you can with positioned at a place, or can also be distributed to multiple
On NE.Some or all of unit therein can be selected to realize the mesh of this embodiment scheme according to the actual needs
's.
In addition, each functional unit in each embodiment of the present invention can be integrated in a processing unit, can also
That unit is individually physically present, can also two or more units it is integrated in a unit.Above-mentioned integrated list
Member can both be realized in the form of hardware, can also be realized in the form of SFU software functional unit.
If the integrated unit is realized in the form of SFU software functional unit and is used as independent production marketing or use
When, it can be stored in a computer read/write memory medium.Based on such understanding, technical scheme is substantially
The part to be contributed in other words to prior art or all or part of the technical scheme can be in the form of software products
Embody, the computer software product is stored in a storage medium, including some instructions are causing a computer
Equipment（Can be personal computer, server, or network equipment etc.）Perform the complete of each embodiment methods described of the present invention
Portion or part steps.And foregoing storage medium includes：USB flash disk, mobile hard disk, read-only storage（ROM, Read-Only
Memory）, random access memory（RAM, Random Access Memory）, magnetic disc or CD etc. are various can store journey
The medium of sequence code.
Described above, the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although with reference to before
Embodiment is stated the present invention is described in detail, it will be understood by those within the art that：It still can be to preceding
State the technical scheme described in each embodiment to modify, or equivalent substitution is carried out to which part technical characteristic；And these
Modification is replaced, and the essence of appropriate technical solution is departed from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (8)
- A kind of 1. in-orbit calibrating installation of current sensor applied to space, it is characterised in that including：Encourage input module, electricity Flow sensor, remote-control romote-sensing module；The excitation input module is connected with the current sensor, for according to default calibration intervals to the current sense Device exports the exciting current signal of known amplitude；The current sensor and prediction connection, for measuring the magnitude of current of the prediction circuit, and by the magnitude of current It is converted into the electric signal that can be measured by the remote-control romote-sensing module；The remote-control romote-sensing module is connected with the current sensor, for monitoring the numerical value change of the electric signal, and by institute State numerical value change and the known amplitude compares, obtain the error that the current sensor shows numerical value.
- 2. device according to claim 1, it is characterised in that it is described excitation input module include timed activation unit, after Electrical equipment and reference current source；The timed activation unit links with relay, the break-make of control relay, and the timed activation unit is used for according to institute Default calibration intervals are stated, activation command is sent to the relay；The relay is used to be closed according to the activation command of the timed activation unit, to activate the reference current source work Make；The reference current source is connected with the relay, for being activated when the relay closes, produces the excitation electricity Signal is flowed, is loaded onto on the current sensor.
- 3. device according to claim 2, it is characterised in that the timed activation unit includes counter, Digital Logic Controller, relay drive circuit；The counter is connected with the digital logic controller, for counting and exporting count signal；The digital logic controller relay drive circuit connection, for the triggering letter in the count signal and reference clock Under number, the break-make of the relay is controlled by relay drive circuit according to logic of propositions.
- 4. device according to claim 1, it is characterised in that the remote-control romote-sensing module is according to the error meter of acquisition The current values of the current sensor are calculated, and the current values are sent to earth station.
- 5. device according to claim 1, it is characterised in that the prediction circuit fills for the battery of spacecraft power supply system Discharge paths, described branch road one end are connected with power source bus, and the other end is connected with battery.
- 6. the in-orbit calibration method of a kind of current sensor applied to space, it is characterised in that comprise the following steps：The exciting current signal of known amplitude is exported to current sensor according to default calibration intervals；The magnitude of current of measurement prediction circuit, and the electric signal that the magnitude of current is converted into being measured；The numerical value change of the electric signal is monitored, and the numerical value change and the known amplitude are compared, obtains the electric current Sensor shows the error of numerical value.
- 7. according to the method for claim 6, it is characterised in that according to current sensor described in the error calculation of acquisition Current values, and the current values are sent to earth station.
- 8. according to the method for claim 6, it is characterised in that the prediction circuit fills for the battery of spacecraft power supply system Discharge paths, described branch road one end are connected with power source bus, and the other end is connected with battery.
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| CN112327235A (en) * | 2020-09-23 | 2021-02-05 | 广州智光电气技术有限公司 | Current transformer fault detection method and device, electronic equipment and storage medium |
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