CN114646806B - Spacecraft direct current load input impedance measurement method and device - Google Patents
Spacecraft direct current load input impedance measurement method and device Download PDFInfo
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- CN114646806B CN114646806B CN202011519812.9A CN202011519812A CN114646806B CN 114646806 B CN114646806 B CN 114646806B CN 202011519812 A CN202011519812 A CN 202011519812A CN 114646806 B CN114646806 B CN 114646806B
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- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
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- G01R27/02—Measuring real or complex resistance, reactance, impedance, or other two-pole characteristics derived therefrom, e.g. time constant
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02H—EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS
- H02H9/00—Emergency protective circuit arrangements for limiting excess current or voltage without disconnection
- H02H9/04—Emergency protective circuit arrangements for limiting excess current or voltage without disconnection responsive to excess voltage
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Abstract
The application discloses a method and a device for measuring direct current load input impedance of a spacecraft, wherein the method comprises the following steps: injecting alternating current disturbance voltage on a transmission line between a direct current power supply and a spacecraft direct current load to form alternating current disturbance current on the transmission line; and measuring alternating current disturbance current flowing into the direction of the direct current load of the spacecraft, and calculating fundamental wave phasor ratio of the alternating current disturbance voltage and the alternating current disturbance current in the direction of the direct current load of the spacecraft to obtain input impedance of the direct current load of the spacecraft. The accurate measurement result can guide the design and the debugging of the spacecraft power supply system, ensure the stability and the reliability of the power supply system, ensure the normal work of each power utilization load, and provide basis for the measurement, the calibration and the acceptance of the input impedance of each power utilization load of the spacecraft.
Description
Technical Field
The embodiment of the application relates to a spacecraft testing technology, in particular to a spacecraft direct current load input impedance measuring method and device.
Background
The input impedance of the direct current load of the spacecraft is one of key technical parameters of the direct current load of the spacecraft, a DC-DC converter and the like. The necessity of accurate measurement of the input impedance of the direct current load of the spacecraft is formed in common knowledge, and the overall units of all types of power supply systems are actively pushing the input impedance index of the direct current load of the spacecraft into technical acceptance index examination. The number of the direct current loads of the spacecraft is large, the types of the direct current loads are various, and the direct current loads of almost all types of units are related to each place and cooperation unit.
The existing input impedance measuring method is to connect disturbance voltage in series to a direct current loop by using a transformer, and adopts a high-power amplifier and a transformer capable of passing larger direct current, when the direct current saturates a magnetic core, the input impedance measuring method cannot be used. In addition, the output impedance matching of the current probe and the calculation of the conversion coefficient are relatively complex.
Disclosure of Invention
In view of this, the embodiment of the application provides a method and a device for measuring the input impedance of a direct current load of a spacecraft.
According to a first aspect of the present application, there is provided a method for measuring input impedance of a dc load of a spacecraft, including:
injecting alternating current disturbance voltage on a transmission line between a direct current power supply and a spacecraft direct current load to form alternating current disturbance current on the transmission line;
and measuring alternating current disturbance current flowing into the direction of the direct current load of the spacecraft, and calculating fundamental wave phasor ratio of the alternating current disturbance voltage and the alternating current disturbance current in the direction of the direct current load of the spacecraft to obtain input impedance of the direct current load of the spacecraft.
Optionally, the method further comprises:
setting a linear stabilized power supply for modulating the alternating current disturbance voltage, wherein the linear stabilized power supply meets the following conditions:
when the alternating-current disturbance voltage signal is not injected into the transmission line, the output of the linear stabilized power supply has no ripple and no oscillation;
when the alternating current disturbance voltage signal is injected into the transmission line, the output of the linear voltage stabilizing power supply can be overlapped with the alternating current disturbance voltage signal with the frequency equal to that of the alternating current disturbance voltage, and the frequency range of the alternating current disturbance voltage is 20 Hz-100 kHz;
the direct-current voltage output of the linear stabilized power supply is 2.5V-30V and is continuously adjustable, and the direct-current output range is 0A-10A.
Optionally, the transfer function of the linear stabilized power supply is: y=h 1 (x 1 ,f)+h 2 (x 2 F) is carried out; wherein h is 1 (x 1 F) is the transfer function of the DC converter, the frequency characteristic of the DC converter is low-pass filtering, and the cut-off frequency<1Hz；h 2 (x 2 F) is a transfer function of the alternating current disturbance voltage, the alternating current disturbance voltage of 20 Hz-100 kHz can be superimposed on the output of the linear stabilized power supply, the frequency characteristic is a band-pass filter, and the band-pass frequency range is 20 Hz-100 kHz.
Optionally, before injecting the alternating disturbance voltage on the transmission line between the direct current power supply and the spacecraft direct current load, the method further comprises:
and loading overcurrent and overvoltage protection on the spacecraft direct-current load, connecting with a related voltage source for input impedance measurement, and establishing a test current working point by the spacecraft direct-current load.
Optionally, the method further comprises:
and acquiring the amplitude value and the impedance angle of the input impedance, and outputting the amplitude value and the impedance angle in a baud pattern.
According to a second aspect of the present application, there is provided a spacecraft dc load input impedance measurement device, comprising:
the injection unit is used for injecting alternating current disturbance voltage on a transmission line between the direct current power supply and the spacecraft direct current load so as to form alternating current disturbance current on the transmission line;
the measuring unit is used for measuring alternating current disturbance current flowing into the direction of the direct current load of the spacecraft, calculating fundamental wave phasor ratio of the alternating current disturbance voltage to the alternating current disturbance current in the direction of the direct current load of the spacecraft, and obtaining input impedance of the direct current load of the spacecraft.
Optionally, the apparatus further comprises:
the setting unit is used for setting a linear stabilized power supply for modulating the alternating current disturbance voltage, and the linear stabilized power supply meets the following conditions:
when the alternating-current disturbance voltage signal is not injected into the transmission line, the output of the linear stabilized power supply has no ripple and no oscillation;
when the alternating current disturbance voltage signal is injected into the transmission line, the output of the linear voltage stabilizing power supply can be overlapped with the alternating current disturbance voltage signal with the frequency equal to that of the alternating current disturbance voltage, and the frequency range of the alternating current disturbance voltage is 20 Hz-100 kHz;
the direct-current voltage output of the linear stabilized power supply is 2.5V-30V and is continuously adjustable, and the direct-current output range is 0A-10A.
Optionally, the transfer function of the linear stabilized power supply is: y=h 1 (x 1 ,f)+h 2 (x 2 F) is carried out; wherein h is 1 (x 1 F) is the transfer function of the DC converter, the frequency characteristic of the DC converter is low-pass filtering, and the cut-off frequency<1Hz；h 2 (x 2 F) is a transfer function of the alternating current disturbance voltage, the alternating current disturbance voltage of 20 Hz-100 kHz can be superimposed on the output of the linear stabilized power supply, the frequency characteristic is a band-pass filter, and the band-pass frequency range is 20 Hz-100 kHz.
Optionally, the apparatus further comprises:
the protection unit is used for loading overcurrent and overvoltage protection on the spacecraft direct-current load, then is connected with a related voltage source for input impedance measurement, and establishes a test current working point by the spacecraft direct-current load.
Optionally, the apparatus further comprises:
and the output unit is used for acquiring the amplitude value and the impedance angle of the input impedance and outputting the amplitude value and the impedance angle in a baud pattern.
According to the spacecraft direct current load input impedance measuring method and device, the spacecraft direct current load input impedance can be accurately measured, technical data can be provided for stability design, stability analysis and stability margin estimation of a spacecraft power supply system, and the method and device have important significance for evaluating the quality of the spacecraft power supply system. The accurate measurement result can guide the design and the debugging of the spacecraft power supply system, ensure the stability and the reliability of the power supply system, ensure the normal work of each power utilization load, and provide basis for the measurement, the calibration and the acceptance of the input impedance of each power utilization load of the spacecraft. The embodiment of the application has a vital meaning for evaluating the quality of the direct current power supply system and the load, can guide the design and the debugging of the power supply system, check and accept power supply and load products, ensure the stability and the reliability of the power supply system, ensure the normal work of the power utilization load, can be popularized and applied to the power load test analysis of other industries such as aviation, ships, electronics, electric power and the like, and can generate larger economic benefits.
Drawings
Fig. 1 is a schematic flow chart of a method for measuring input impedance of a direct current load of a spacecraft according to an embodiment of the application;
fig. 2 is a schematic diagram of a measurement principle of a dc load input impedance of a spacecraft according to an embodiment of the present application;
fig. 3 is a schematic diagram of injection of an ac disturbance voltage into a series voltage-controlled resistive element according to an embodiment of the present disclosure;
FIG. 4 is a schematic diagram of a transfer function of an AC perturbation voltage provided in an embodiment of the present application;
fig. 5 is a schematic diagram of a composition structure of a spacecraft dc load input impedance measurement device according to an embodiment of the present application.
Detailed Description
The method and the device are mainly used for solving the problem of measurement of the direct current load input impedance of the spacecraft, aiming at the basic requirement that the safety and reliability of the measured equipment must be ensured in the measurement process of the spacecraft, according to the characteristics of the amplitude value, the phase range, the type diversification and the like of the direct current load input impedance of the measured spacecraft.
Fig. 1 is a schematic flow chart of a method for measuring dc load input impedance of a spacecraft according to an embodiment of the application, and as shown in fig. 1, the method for measuring dc load input impedance of a spacecraft according to an embodiment of the application includes the following processing steps:
and step 101, injecting alternating current disturbance voltage on a transmission line between a direct current power supply and a spacecraft direct current load, so that alternating current disturbance current is formed on the transmission line.
As an implementation, the method further includes:
setting a linear stabilized power supply for modulating the alternating current disturbance voltage, wherein the linear stabilized power supply meets the following conditions:
when the alternating-current disturbance voltage signal is not injected into the transmission line, the output of the linear stabilized power supply has no ripple and no oscillation;
when the alternating current disturbance voltage signal is injected into the transmission line, the output of the linear voltage stabilizing power supply can be overlapped with the alternating current disturbance voltage signal with the frequency equal to that of the alternating current disturbance voltage, and the frequency range of the alternating current disturbance voltage is 20 Hz-100 kHz;
the direct-current voltage output of the linear stabilized power supply is 2.5V-30V and is continuously adjustable, and the direct-current output range is 0A-10A.
As one implementation, the transfer function of the linear regulated power supply is: y=h 1 (x 1 ,f)+h 2 (x 2 F) is carried out; wherein h is 1 (x 1 F) is the transfer function of the DC converter, the frequency characteristic of the DC converter is low-pass filtering, and the cut-off frequency<1Hz；h 2 (x 2 F) is a transfer function of the alternating current disturbance voltage, the alternating current disturbance voltage of 20 Hz-100 kHz can be superimposed on the output of the linear stabilized power supply, the frequency characteristic is a band-pass filter, and the band-pass frequency range is 20 Hz-100 kHz.
As an implementation manner, before the alternating-current disturbance voltage is injected into the transmission line between the direct-current power supply and the spacecraft direct-current load, the spacecraft direct-current load is loaded with overcurrent and overvoltage protection, then connected with a relevant voltage source for input impedance measurement, and a test current working point is established by the spacecraft direct-current load.
As an implementation manner, after the input impedance of the spacecraft dc load is measured, the amplitude and the impedance angle of the input impedance are obtained, and the amplitude and the impedance angle are output in a baud pattern.
According to the embodiment of the application, the tested spacecraft direct current load is connected with a voltage source related to testing after overcurrent and overvoltage protection, and a test current working point is established by the tested spacecraft direct current load; superposing a sinusoidal disturbance voltage in a direct current reference standard in the test voltage source, superposing a sinusoidal disturbance small signal on the direct current voltage output by the test voltage source, realizing undistorted injection of the test voltage, realizing measurement of weak alternating current by using a related technology, and calculating to obtain the amplitude and phase of the input impedance of the direct current load of the spacecraft by measuring the phasor of the input alternating voltage and the phasor of the input alternating current at two ends of the direct current load of the spacecraft; and measuring the direct current load of the spacecraft in the whole frequency range by changing the frequency of the disturbance signal, so as to obtain the amplitude-frequency characteristic and the phase-frequency characteristic of the input impedance of the direct current load of the spacecraft.
As an implementation manner, the embodiment of the application adopts a frequency response analyzer-based scheme to measure the direct current load input impedance of the spacecraft. Fig. 2 is a schematic diagram of a measurement principle of a dc load input impedance of a spacecraft according to an embodiment of the application, and as shown in fig. 2, a measurement system may be composed of a frequency response analyzer, a disturbance injection signal conversion unit, a linear stabilized voltage supply, an oscilloscope, computer test software, and the like. In the embodiment of the application, the spacecraft direct current load input impedance testing means can be implemented in a testing mode of the prior art, and alternating current disturbance voltage is required to be injected into a transmission line between a direct current power supply and the spacecraft direct current load to achieve measurement of input impedance. Specifically, in the embodiment of the application, when the direct-current power supply and the spacecraft direct-current load work together on a direct-current working point, a measuring section is selected on a transmission line between the direct-current power supply and the spacecraft direct-current load, and a sinusoidal alternating-current disturbance voltage signal is injected into the transmission line of the direct-current power supply and the spacecraft direct-current load; the ac perturbation voltage causes an ac perturbation current on the transmission line of the dc power supply and the spacecraft dc load. The method is characterized by comprising the steps of ensuring that alternating-current disturbance voltage and current are small enough, so that disturbance phenomenon occurs in a linear region near a working point, and measuring the fundamental wave phasor ratio of the alternating-current disturbance voltage to alternating-current disturbance current flowing into a spacecraft direct-current load direction under the condition that the disturbance current and the disturbance voltage are not obviously distorted, so as to obtain the input impedance of the spacecraft direct-current load. The measurement results are given in the form of a baud plot of the impedance magnitude and impedance angle. After the measuring lines are connected, the measuring system can eliminate the influences of the distributed capacitance of the measuring lines and the inductance of the measuring leads by using open-circuit experiments and short-circuit experiments.
In the embodiment of the application, the input impedance of the spacecraft direct current load is an active nonlinear impedance, measurement is required under the condition that the spacecraft direct current load has a large input current, the input current is often disturbed greatly, and the technical safety of a tested power supply is ensured. During measurement, the tested spacecraft direct current load is connected with a voltage source related to the test after overcurrent and overvoltage protection, and a test current working point is established by the tested spacecraft direct current load; superposing a sinusoidal disturbance voltage in a direct current reference standard in the test voltage source, superposing a sinusoidal disturbance small signal on the direct current voltage output by the test voltage source, realizing undistorted injection of the test alternating current disturbance voltage, realizing measurement of weak alternating current by using a related technology, and calculating to obtain the amplitude and phase of the input impedance of the direct current load of the spacecraft by measuring the phasor of the input alternating voltage and the phasor of the input alternating current at two ends of the load; and measuring the direct current load of the spacecraft in the whole frequency range by changing the frequency of the disturbance signal, so as to obtain the amplitude-frequency characteristic and the phase-frequency characteristic of the input impedance of the direct current load of the spacecraft.
In the embodiment of the application, the alternating current disturbance signal injected into the transmission line of the spacecraft direct current load needs to meet the small signal condition, nonlinear distortion cannot occur, and the impedance component of the measured spacecraft direct current load is not changed as much as possible. The spacecraft power supply system is a typical nonlinear system, wherein the direct current load impedance of the spacecraft is related to the working current and the working voltage, and the nonlinear system can generate a broadband response signal under the action of a single-frequency excitation signal. Therefore, the system can be equivalent to a linear system only in a very small range near the working point, and the alternating disturbance signal can be usedThe ratio of the input to output responses defines the impedance of the system. Therefore, the alternating current disturbance signal injection technology is one of the technical difficulties in the measurement of the direct current load input impedance of the spacecraft. The embodiment of the application designs an alternating current disturbance injection method based on a series voltage-controlled resistor element, which injects alternating current voltage disturbance signals into a bus of a spacecraft. Fig. 3 is a schematic diagram of the principle of injecting alternating current disturbance voltage into a series voltage-controlled resistive element provided in the embodiment of the present application, as shown in fig. 3, after amplifying and adjusting an alternating current signal output by a standard alternating current source (or digital bridge alternating current excitation), the alternating current signal is added to two ends of the voltage-controlled resistive element, so that an alternating current disturbance signal is injected into a transmission line of a spacecraft. Due to the adoption of the mode of series injection voltage disturbance, the input impedance Z of the spacecraft direct current load is not limited L Far greater than the output impedance Z of the power supply s But the alternating current disturbance current signal flowing into the spacecraft direct current load can be properly improved through the voltage-controlled resistance element, so that the impedance measuring unit can accurately measure the alternating current disturbance current signal.
From the perspective of the DC load of the tested spacecraft, according to the basic principle of the DC load input impedance measurement of the spacecraft, when the DC load input impedance of the spacecraft is tested, a set of alternating current disturbance signal modulation linear voltage-stabilized power supply with small signal injection is required as key equipment, and the transfer function of the alternating current disturbance signal modulation linear voltage-stabilized power supply is shown in figure 4. The technical requirements of the linear stabilized voltage supply include:
when the alternating-current disturbance voltage signal is not injected into the transmission line, the output of the linear stabilized power supply has no ripple and no oscillation;
when the alternating current disturbance voltage signal is injected into the transmission line, the output of the linear voltage stabilizing power supply can be overlapped with the alternating current disturbance voltage signal with the frequency equal to that of the alternating current disturbance voltage, and the frequency range of the alternating current disturbance voltage is 20 Hz-100 kHz;
the direct-current voltage output of the linear stabilized power supply is 2.5V-30V and is continuously adjustable, and the direct-current output range is 0A-10A.
The transfer function of the linear stabilized voltage power supply modulated by the alternating current disturbance voltage signal is as follows: y=h 1 (x 1 ,f)+h 2 (x 2 F). Wherein h is 1 (x 1 F) is a transfer function of the DC converter, which is consistent with that of the linear stabilized power supply, and the frequency characteristic is a low-pass filter, a cut-off frequency<1Hz；h 2 (x 2 F) is a transfer function of an alternating current disturbance voltage signal, and is required to be capable of superposing the alternating current disturbance voltage signal of 20 Hz-100 kHz on the output of the linear stabilized power supply, wherein the frequency characteristic is a band-pass filter, and the band-pass frequency range is 20 Hz-100 kHz. Based on the analysis, the embodiment of the application designs an alternating current disturbance signal modulation linear voltage-stabilized power supply based on small signal injection of feedback adjustment.
The method and the device are directly applied to stability evaluation of the power supply and distribution system of the spacecraft. Each load of the spacecraft is developed by different cooperative units, and stability design requirements must be put forward on load input impedance in order to ensure stability of the power bus after integral integration. According to the invention, the spacecraft direct current load input impedance measuring device is developed, accurate measurement of the spacecraft direct current load input impedance is carried out, technical data can be provided for stability design, stability analysis and stability margin estimation of a spacecraft power supply system, and the method has a vital significance for evaluating the quality of the spacecraft power supply system. The accurate measurement result can guide the design and the debugging of the spacecraft power supply system, ensure the stability and the reliability of the power supply system, ensure the normal work of each power utilization load, and provide basis for the measurement, the calibration and the acceptance of the input impedance of each power utilization load of the spacecraft.
In addition, the embodiment of the application has a very important meaning for evaluating the quality of the direct current power supply system and the load, can guide the design and the debugging of the power supply system, check and accept power supply and load products, ensure the stability and the reliability of the power supply system, ensure the normal work of the power utilization load, can be popularized and applied to the direct current load test analysis of other industries such as aviation, ships, electronics, electric power and the like, and generates great economic benefits.
Fig. 5 is a schematic structural diagram of a spacecraft dc load input impedance measurement device provided in an embodiment of the present application, and as shown in fig. 5, the spacecraft dc load input impedance measurement device in an embodiment of the present application includes:
an injection unit 50 for injecting an ac disturbance voltage on a transmission line between a dc power supply and a dc load of a spacecraft, so as to form an ac disturbance current on the transmission line;
the measurement unit 51 is configured to measure an ac perturbation current flowing into the direction of the dc load of the spacecraft, calculate a fundamental phasor ratio of the ac perturbation voltage to the ac perturbation current flowing into the direction of the dc load of the spacecraft, and obtain an input impedance of the dc load of the spacecraft.
On the basis of the spacecraft direct current load input impedance measuring device shown in fig. 5, the spacecraft direct current load input impedance measuring device of the embodiment of the application further comprises:
a setting unit (not shown in fig. 5) for setting a linear stabilized power supply modulating the alternating-current disturbance voltage, the linear stabilized power supply satisfying the following conditions:
when the alternating-current disturbance voltage signal is not injected into the transmission line, the output of the linear stabilized power supply has no ripple and no oscillation;
when the alternating current disturbance voltage signal is injected into the transmission line, the output of the linear voltage stabilizing power supply can be overlapped with the alternating current disturbance voltage signal with the frequency equal to that of the alternating current disturbance voltage, and the frequency range of the alternating current disturbance voltage is 20 Hz-100 kHz;
the direct-current voltage output of the linear stabilized power supply is 2.5V-30V and is continuously adjustable, and the direct-current output range is 0A-10A.
As one implementation, the transfer function of the linear regulated power supply is: y=h 1 (x 1 ,f)+h 2 (x 2 F) is carried out; wherein h is 1 (x 1 F) is the transfer function of the DC converter, the frequency characteristic of the DC converter is low-pass filtering, and the cut-off frequency<1Hz；h 2 (x 2 F) is a transfer function of the alternating current disturbance voltage, the alternating current disturbance voltage of 20 Hz-100 kHz can be superimposed on the output of the linear stabilized power supply, the frequency characteristic is a band-pass filter, and the band-pass frequency range is 20 Hz-100 kHz.
On the basis of the spacecraft direct current load input impedance measuring device shown in fig. 5, the spacecraft direct current load input impedance measuring device of the embodiment of the application further comprises:
and the protection unit (not shown in fig. 5) is used for loading overcurrent and overvoltage protection on the spacecraft direct-current load, then is connected with a voltage source related to input impedance measurement, and establishes a test current working point by the spacecraft direct-current load.
On the basis of the spacecraft direct current load input impedance measuring device shown in fig. 5, the spacecraft direct current load input impedance measuring device of the embodiment of the application further comprises:
and an output unit (not shown in fig. 5) for acquiring the magnitude and the impedance angle of the input impedance and outputting the magnitude and the impedance angle in a baud pattern.
In an exemplary embodiment, the injection unit 50, the measurement unit 51, the setting unit, the protection unit, the output unit, etc. may be implemented by one or more central processing units (CPU, central Processing Unit), graphics processors (GPU, graphics Processing Unit), baseband processors (BP, base Processor), application specific integrated circuits (ASIC, application Specific Integrated Circuit), digital signal processors (Digital Signal Processor, DSP), programmable logic devices (PLD, programmable Logic Device), complex programmable logic devices (CPLD, complex Programmable Logic Device), field programmable gate arrays (FPGA, field-Programmable Gate Array), general purpose processors, controllers, microcontrollers (MCU, micro Controller Unit), microprocessors (Microprocessor), or other electronic components.
In the embodiment of the present application, the specific manner in which the units in the spacecraft dc load input impedance measuring device shown in fig. 5 perform the operation is described in detail in the embodiment of the method, and will not be described in detail herein.
It should be appreciated that reference throughout this specification to "one embodiment" or "an embodiment" means that a particular feature, structure or characteristic described in connection with the embodiment is included in at least one embodiment of the present invention. Thus, the appearances of the phrases "in one embodiment" or "in an embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, the particular features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. It should be understood that, in various embodiments of the present invention, the sequence numbers of the foregoing processes do not mean the order of execution, and the order of execution of the processes should be determined by the functions and internal logic thereof, and should not constitute any limitation on the implementation process of the embodiments of the present invention. The foregoing embodiment numbers of the present invention are merely for the purpose of description, and do not represent the advantages or disadvantages of the embodiments.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
In the several embodiments provided in this application, it should be understood that the disclosed apparatus and method may be implemented in other ways. The above described device embodiments are only illustrative, e.g. the division of the units is only one logical function division, and there may be other divisions in practice, such as: multiple units or components may be combined or may be integrated into another system, or some features may be omitted, or not performed. In addition, the various components shown or discussed may be coupled or directly coupled or communicatively coupled to each other via some interface, whether indirectly coupled or communicatively coupled to devices or units, whether electrically, mechanically, or otherwise.
The units described above as separate components may or may not be physically separate, and components shown as units may or may not be physical units; can be located in one place or distributed to a plurality of network units; some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.
In addition, each functional unit in each embodiment of the present invention may be integrated in one processing unit, or each unit may be separately used as one unit, or two or more units may be integrated in one unit; the integrated units may be implemented in hardware or in hardware plus software functional units.
The foregoing is merely an embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily think about changes or substitutions within the technical scope of the present invention, and the changes and substitutions are intended to be covered by the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. A method for measuring the input impedance of a direct current load of a spacecraft, the method comprising:
injecting alternating-current disturbance voltage on a transmission line between a direct-current power supply and a spacecraft direct-current load through a linear stabilized power supply, so that alternating-current disturbance current is formed on the transmission line; a voltage-controlled resistance element is connected in series between the linear voltage-stabilized power supply and the spacecraft direct current load; the linear stabilized power supply is an alternating current disturbance signal modulation linear stabilized power supply with small signal injection, the direct current voltage output of the linear stabilized power supply is 2.5V-30V, and the direct current output range is 0A-10A; the transfer function of the linear stabilized power supply is as follows: y=h 1 (x 1 ,f)+h 2 (x 2 F) is carried out; wherein h is 1 (x 1 F) is the transfer function of the DC converter; h is a 2 (x 2 F) is a transfer function of the alternating disturbance voltage;
and measuring alternating current disturbance current flowing into the direction of the direct current load of the spacecraft, and calculating fundamental wave phasor ratio of the alternating current disturbance voltage and the alternating current disturbance current in the direction of the direct current load of the spacecraft to obtain input impedance of the direct current load of the spacecraft.
2. The input impedance measurement method of claim 1, further comprising:
setting the linear stabilized power supply for modulating the alternating current disturbance voltage, wherein the linear stabilized power supply meets the following conditions:
when the alternating-current disturbance voltage signal is not injected into the transmission line, the output of the linear stabilized power supply has no ripple and no oscillation;
when the alternating current disturbance voltage signal is injected into the transmission line, the output of the linear stabilized power supply can be overlapped with the alternating current disturbance voltage signal with the same frequency as the alternating current disturbance voltage, and the frequency range of the alternating current disturbance voltage is 20 Hz-100 kHz.
3. The method of claim 2, wherein the frequency characteristic of the dc converter is low pass filtering with a cut-off frequency <1Hz; the transfer function of the alternating current disturbance voltage can superimpose the alternating current disturbance voltage of 20 Hz-100 kHz on the output of the linear stabilized power supply, the frequency characteristic is a band-pass filter, and the band-pass frequency range is 20 Hz-100 kHz.
4. The method of claim 1, wherein prior to injecting the ac perturbation voltage on the transmission line between the dc power source and the spacecraft dc load, the method further comprises:
and loading overcurrent and overvoltage protection on the spacecraft direct-current load, connecting with a related voltage source for input impedance measurement, and establishing a test current working point by the spacecraft direct-current load.
5. The input impedance measurement method according to any one of claims 1 to 4, further comprising:
and acquiring the amplitude value and the impedance angle of the input impedance, and outputting the amplitude value and the impedance angle in a baud pattern.
6. A spacecraft dc load input impedance measurement device, the device comprising:
the injection unit is used for injecting alternating current disturbance voltage on a transmission line between a direct current power supply and a spacecraft direct current load through a linear stabilized voltage supply so as to form alternating current disturbance current on the transmission line; a voltage-controlled resistance element is connected in series between the linear voltage-stabilized power supply and the spacecraft direct current load; the linear stabilized power supply is an alternating current disturbance signal modulation linear stabilized power supply with small signal injection, the direct current voltage output of the linear stabilized power supply is 2.5V-30V, and the direct current output range is 0A-10A; the transfer function of the linear stabilized power supply is as follows: y=h 1 (x 1 ,f)+h 2 (x 2 F) is carried out; wherein h is 1 (x 1 F) is the transfer function of the DC converter; h is a 2 (x 2 F) is a transfer function of the alternating disturbance voltage; the measuring unit is used for measuring alternating current disturbance current flowing into the direction of the direct current load of the spacecraft, calculating fundamental wave phasor ratio of the alternating current disturbance voltage to the alternating current disturbance current in the direction of the direct current load of the spacecraft, and obtaining input impedance of the direct current load of the spacecraft.
7. The input impedance measurement device of claim 6, wherein the device further comprises:
a setting unit configured to set the linear stabilized power supply that modulates the ac disturbance voltage, the linear stabilized power supply satisfying the following condition:
when the alternating-current disturbance voltage signal is not injected into the transmission line, the output of the linear stabilized power supply has no ripple and no oscillation;
when the alternating current disturbance voltage signal is injected into the transmission line, the output of the linear stabilized power supply can be overlapped with the alternating current disturbance voltage signal with the same frequency as the alternating current disturbance voltage, and the frequency range of the alternating current disturbance voltage is 20 Hz-100 kHz.
8. The input impedance measurement device of claim 7 wherein the frequency characteristic of the dc converter is low pass filtering with a cut-off frequency <1Hz; the transfer function of the alternating current disturbance voltage can superimpose the alternating current disturbance voltage of 20 Hz-100 kHz on the output of the linear stabilized power supply, the frequency characteristic is a band-pass filter, and the band-pass frequency range is 20 Hz-100 kHz.
9. The input impedance measurement device of claim 6, wherein the device further comprises:
the protection unit is used for loading overcurrent and overvoltage protection on the spacecraft direct-current load, then is connected with a related voltage source for input impedance measurement, and establishes a test current working point by the spacecraft direct-current load.
10. The input impedance measurement device of any of claims 6 to 9, wherein the device further comprises:
and the output unit is used for acquiring the amplitude value and the impedance angle of the input impedance and outputting the amplitude value and the impedance angle in a baud pattern.
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