CN103323668B - Spacecraft power source controller bus electromagnetic compatibility conducted emission frequency domain testing method - Google Patents
Spacecraft power source controller bus electromagnetic compatibility conducted emission frequency domain testing method Download PDFInfo
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- CN103323668B CN103323668B CN201310240871.6A CN201310240871A CN103323668B CN 103323668 B CN103323668 B CN 103323668B CN 201310240871 A CN201310240871 A CN 201310240871A CN 103323668 B CN103323668 B CN 103323668B
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Abstract
The invention discloses a spacecraft power source controller bus electromagnetic compatibility conducted emission frequency domain testing method. Bus electromagnetic compatibility conducted emission under two working conditions of a power source controller is tested, then the maximum influence of PCU power source bus conducted emission on spacecraft electromagnetic compatibility is acquired, and the testing result of PCU bus electromagnetic compatibility conducted emission can be effectively reflected to spacecraft electromagnetic compatibility analysis; the limiting value requirement of the spacecraft PCU bus electromagnetic compatibility conducted emission is determined and can be used as the foundation to determine whether the spacecraft PCU bus electromagnetic compatibility conducted emission meets requirements or not. In consideration of measuring accuracy and time cost, measuring bandwidths of a spectrum analyzer are set according to different measuring frequency ranges, and therefore measuring time can be saved and measuring efficiency can be improved on the premise that measuring accuracy of the spectrum analyzer is guaranteed.
Description
Technical field
The present invention relates to Electro Magnetic Compatibility conducted emission field tests, be specifically related to a kind of spacecraft power supply controller bus Electro Magnetic Compatibility conducted emission frequency domain test method.
Background technology
Power-supply controller of electric (PCU) is for controlling to spacecraft power supply subsystem, regulate, protect and provide the interface etc. of other subsystems of spacecraft; its normal work is the basis ensureing each subsystem normal power supply of spacecraft or electricity consumption, is one of most important subsystem of spacecraft.Because the power of PCU is very large, especially along with the development of large capacity satellite platform, the power of PCU constantly increases, and has reached a few myriawatt.Its conducted emission is the emphasis direction that spacecraft Electro Magnetic Compatibility is paid close attention to.
At present, be test based on standard-requireds such as MIL-STD-461 series standard and GJB151A-97, GJB152A-97 to the main method of testing of PCU bus Electro Magnetic Compatibility conducted emission.But above-mentioned standard is to the test request of equipment conducted emission and method for power receiving equipment, and inapplicable to power-supply unit, and PCU is power-supply unit, therefore, the method for carrying out PCU bus Electro Magnetic Compatibility conducted emission based on above-mentioned standard is irrational.Chinese Academy of Space Technology's Electro Magnetic Compatibility special interest group finds in Space Vehicle System for many years, subsystem and installation electromagnetical compatibility test work, when adopting above-mentioned standard to carry out spacecraft PCU bus Electro Magnetic Compatibility conducted emission, on the one hand, test macro cannot meet the high-power requirement of growing PCU; On the other hand, the limit value that the relatively above-mentioned standard of test result specifies all exceeds standard, and namely existing test result and general limit value cannot foundations as spacecraft PCU bus Electro Magnetic Compatibility conducted emission whether by requiring.And still lack now for this kind of power-supply unit Electro Magnetic Compatibility of spacecraft PCU conducted emission test foundation.And clear and definite regulation is not had to the operating mode of PCU in test process, is not enough to reflect that spacecraft PCU bus conducted emission is on the real impact of Electro Magnetic Compatibility.
Summary of the invention
In view of this, the invention provides a kind of spacecraft power supply controller bus Electro Magnetic Compatibility conducted emission frequency domain test method, can test the Electro Magnetic Compatibility conducted emission of spacecraft power-supply unit, and solve the operating mode offering question of PCU bus Electro Magnetic Compatibility conducted emission.
Spacecraft power supply controller bus Electro Magnetic Compatibility conducted emission frequency domain test method of the present invention, comprises the steps:
Step 1, build proving installation:
Between two power output end points of power-supply controller of electric, adopt cable to connect into power-supply controller of electric bus by ground load, adopt difference oscillographic two difference detectors to be overlapped on the positive and negative end of power-supply controller of electric bus respectively, the oscillographic output terminal of difference is connected after 10 μ F electric capacity and is connected with the input port of spectrum analyzer; Regulate difference oscillograph to alternate current operation pattern;
Step 2, shut down by power-supply controller of electric, difference oscillograph and spectrum analyzer are all started shooting, and utilize spectrum analyzer to measure ground unrest in 30Hz ~ 100MHz frequency range;
Step 3, by power-supply controller of electric start shooting, the mode of operation of power-supply controller of electric is arranged to ground shadow phase duty;
Step 4, spectrum analyzer is utilized to test conducted emission frequency spectrum in 30Hz ~ 100MHz frequency range;
Step 5, Switching power controller mode of operation are to illumination period charging module duty, and the dutycycle regulating power-supply controller of electric internal shunt device switch is 50%;
Step 6, spectrum analyzer is utilized to test conducted emission frequency spectrum in 30Hz ~ 100MHz frequency range;
Step 7, step 4 tested the conducted emission frequency spectrum that obtains and step 6 and test the conducted emission frequency spectrum obtained and get rid of after step 2 tests the ground unrest obtained respectively, contrast with the limit value of bus Electro Magnetic Compatibility conducted emission frequency spectrum respectively again, if higher than limit value, then not by test, if lower than limit value, then by test.
Further, described difference detector is as far as possible near two power output end points of power-supply controller of electric.
Further, the distance of described power-supply controller of electric bus and ground plane is greater than or equal to 5cm.
Further, in step 4 and step 6, utilize spectrum analyzer to when conducted emission frequency spectrum is tested in 30Hz ~ 100MHz frequency range:
In 30Hz ~ 1kHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 10Hz;
In 1kHz ~ 10kHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 50Hz;
In 10kHz ~ 2.5MHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 500Hz;
In 2.5MHz ~ 25MHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 5kHz;
In 25MHz ~ 50MHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 50kHz;
In 50MHz ~ 100MHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 100kHz.
Further, the limit value of described step 7 median generatrix Electro Magnetic Compatibility conducted emission frequency spectrum is: in 30Hz ~ 1.5kHz frequency range, voltage is 110dB μ Vp; In 2kHz ~ 100MHz frequency range, voltage is 104dB μ Vp; In 1.5kHz ~ 2kHz frequency range, voltage is linear transitions between 110dB μ Vp-104dB μ Vp.
The present invention has following beneficial effect:
1), the invention provides the method for testing of this kind of power-supply unit bus of a kind of spacecraft PCU Electro Magnetic Compatibility conducted emission, there is provided and the bus Electro Magnetic Compatibility conducted emission under power-supply controller of electric two kinds of operating modes is tested, obtain PCU power source bus conducted emission to maximum effect of spacecraft Electro Magnetic Compatibility, PCU bus Electro Magnetic Compatibility conducted emission test result, effectively can be reflected in spacecraft electromagnetic compatibility analysis and go simultaneously.
2), the method for the invention, determining the requirement of spacecraft PCU bus Electro Magnetic Compatibility conducted emission limit value, can be used as the foundation of spacecraft PCU bus Electro Magnetic Compatibility conducted emission whether by requiring.
3), consider measuring accuracy and time cost, the present invention arranges the Measurement bandwidth of spectrum analyzer according to different test frequency ranges, under the prerequisite of measuring accuracy ensureing spectrum analyzer, can also save the test duration, improve testing efficiency.
Accompanying drawing explanation
Fig. 1 is the Electro Magnetic Compatibility conducted emission test configurations figure of the present invention to PCU bus.
Fig. 2 is the limit graph of bus Electro Magnetic Compatibility conducted emission frequency spectrum of the present invention.
Embodiment
To develop simultaneously embodiment below in conjunction with accompanying drawing, describe the present invention.
The invention provides a kind of spacecraft power supply controller bus Electro Magnetic Compatibility conducted emission frequency domain test method, the method comprises the steps:
Step 1, build proving installation:
As shown in Figure 1, between two power output end points of power-supply controller of electric, adopt cable to connect into power-supply controller of electric bus by ground load, adopt difference oscillographic two difference detectors to be overlapped on the positive and negative end of power-supply controller of electric bus respectively, the output terminal corresponding with difference oscillograph difference detector is connected after 10 μ F electric capacity and is connected with the input port of spectrum analyzer; Regulate difference oscillograph to alternate current operation pattern; Wherein electric capacity is used for filtering, cuts off direct current.
Step 2, shut down by power-supply controller of electric, difference oscillograph and spectrum analyzer are all started shooting, and utilize spectrum analyzer to measure ground unrest in 30Hz ~ 100MHz frequency range;
Step 3, power-supply controller of electric to be started shooting, the mode of operation of power-supply controller of electric is arranged to ground shadow phase duty, and waits for that power-supply controller of electric enters steady-working state;
After step 4, power-supply controller of electric stable working state, spectrum analyzer is utilized to test conducted emission frequency spectrum in 30Hz ~ 100MHz frequency range;
Step 5, Switching power controller mode of operation are to illumination period charging module duty, and the dutycycle regulating power-supply controller of electric internal shunt device switch is 50%, wait for that power-supply controller of electric enters steady-working state;
Step 6, spectrum analyzer is utilized to test conducted emission frequency spectrum in 30Hz ~ 100MHz frequency range;
Step 7, step 4 tested the conducted emission frequency spectrum that obtains and step 6 and test the conducted emission frequency spectrum obtained and get rid of after step 2 tests the ground unrest obtained respectively, contrast with the limit value of bus Electro Magnetic Compatibility conducted emission frequency spectrum respectively again, if higher than limit value, then not by test, if lower than limit value, then by test.
In order to reduce the impact of external cable, difference detector is as far as possible near two power output end points of power-supply controller of electric.
For the coupling reducing power-supply controller of electric bus and ground plane affects, the distance of power-supply controller of electric bus and ground plane is greater than or equal to 5cm.
In step 4 and step 6, utilize spectrum analyzer to when conducted emission frequency spectrum is tested in 30Hz ~ 100MHz frequency range, because test frequency range is wider, if the Measurement bandwidth arranging spectrum analyzer is too little, although can measuring accuracy be improved, but a lot of test duration can be wasted, in like manner, if test bandwidth is arranged larger, then can to lose measuring accuracy for cost, therefore, take into account measuring accuracy and time cost, the present invention adopts different frequency range to adopt the method for different test bandwidth, specific as follows:
In 30Hz ~ 1kHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 10Hz;
In 1kHz ~ 10kHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 50Hz;
In 10kHz ~ 2.5MHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 500Hz;
In 2.5MHz ~ 25MHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 5kHz;
In 25MHz ~ 50MHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 50kHz;
In 50MHz ~ 100MHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 100kHz.
Combine electromagnetic Compatibility Design experience for many years according to repeatedly test result, the limit value of step 7 median generatrix Electro Magnetic Compatibility conducted emission frequency spectrum is: in 30Hz ~ 1.5kHz frequency range, and voltage is 110dB μ Vp; In 2kHz ~ 100MHz frequency range, voltage is 104dB μ Vp; In 1.5kHz ~ 2kHz frequency range, voltage is linear transitions between 110dB μ Vp-104dB μ Vp.
In sum, these are only preferred embodiment of the present invention, be not intended to limit protection scope of the present invention.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (4)
1. spacecraft power supply controller bus Electro Magnetic Compatibility conducted emission frequency domain test method, is characterized in that, comprise the steps:
Step 1, build proving installation:
Between two power output end points of power-supply controller of electric, adopt cable to connect into power-supply controller of electric bus by ground load, adopt difference oscillographic two difference detectors to be overlapped on the positive and negative end of power-supply controller of electric bus respectively, the oscillographic output terminal of difference is connected after 10 μ F electric capacity and is connected with the input port of spectrum analyzer; Regulate difference oscillograph to alternate current operation pattern;
Step 2, shut down by power-supply controller of electric, difference oscillograph and spectrum analyzer are all started shooting, and utilize spectrum analyzer to measure ground unrest in 30Hz ~ 100MHz frequency range;
Step 3, by power-supply controller of electric start shooting, the mode of operation of power-supply controller of electric is arranged to ground shadow phase duty;
Step 4, spectrum analyzer is utilized to test conducted emission frequency spectrum in 30Hz ~ 100MHz frequency range;
Step 5, Switching power controller mode of operation are to illumination period charging module duty, and the dutycycle regulating power-supply controller of electric internal shunt device switch is 50%;
Step 6, spectrum analyzer is utilized to test conducted emission frequency spectrum in 30Hz ~ 100MHz frequency range;
Step 7, step 4 tested the conducted emission frequency spectrum that obtains and step 6 and test the conducted emission frequency spectrum obtained and get rid of after step 2 tests the ground unrest obtained respectively, contrast with the limit value of bus Electro Magnetic Compatibility conducted emission frequency spectrum respectively again, if higher than limit value, then not by test, if lower than limit value, then by test;
Wherein, in step 4 and step 6, utilize spectrum analyzer to when conducted emission frequency spectrum is tested in 30Hz ~ 100MHz frequency range:
In 30Hz ~ 1kHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 10Hz;
In 1kHz ~ 10kHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 50Hz;
In 10kHz ~ 2.5MHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 500Hz;
In 2.5MHz ~ 25MHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 5kHz;
In 25MHz ~ 50MHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 50kHz;
In 50MHz ~ 100MHz frequency range, the Measurement bandwidth arranging spectrum analyzer is 100kHz.
2. spacecraft power supply controller bus Electro Magnetic Compatibility conducted emission frequency domain test method as claimed in claim 1, it is characterized in that, described difference detector is as far as possible near two power output end points of power-supply controller of electric.
3. spacecraft power supply controller bus Electro Magnetic Compatibility conducted emission frequency domain test method as claimed in claim 1, it is characterized in that, the distance of described power-supply controller of electric bus and ground plane is greater than or equal to 5cm.
4. spacecraft power supply controller bus Electro Magnetic Compatibility conducted emission frequency domain test method as claimed in claim 1, it is characterized in that, the limit value of described step 7 median generatrix Electro Magnetic Compatibility conducted emission frequency spectrum is: in 30Hz ~ 1.5kHz frequency range, voltage is 110dB μ Vp; In 2kHz ~ 100MHz frequency range, voltage is 104dB μ Vp; In 1.5kHz ~ 2kHz frequency range, voltage is linear transitions between 110dB μ Vp-104dB μ Vp.
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| CN106526390A (en) * | 2016-12-23 | 2017-03-22 | 安徽华东光电技术研究所 | Electronic compatible EMC conduction simple test method |
| CN108875239B (en) * | 2018-06-28 | 2022-04-22 | 天津航天机电设备研究所 | Spacecraft radio frequency electromagnetic compatibility analysis system |
| CN111781457A (en) * | 2020-07-24 | 2020-10-16 | 上海擎度汽车科技有限公司 | Test system and method for EMC conduction emission of electronic product |
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| DE10136626A1 (en) * | 2001-07-26 | 2003-02-20 | Siemens Ag | Determination of the spectral behavior of electromagnetic signals within a given frequency range, for interference assessment, using a FFT to convert the signal into the frequency domain thus drastically reducing measurement time |
| CN101750545A (en) * | 2009-12-15 | 2010-06-23 | 北京空间飞行器总体设计部 | Electromagnetic compatibility test method for electric propulsion system |
| CN201909815U (en) * | 2010-12-14 | 2011-07-27 | 中国航空无线电电子研究所 | CS101 monitoring device |
| CN102723756A (en) * | 2012-06-18 | 2012-10-10 | 上海卫星工程研究所 | Full-digital power controller for satellite |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH06324098A (en) * | 1993-05-14 | 1994-11-25 | Nippon Telegr & Teleph Corp <Ntt> | Electromagnetic-interference-wave measuring instrument |
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| DE10136626A1 (en) * | 2001-07-26 | 2003-02-20 | Siemens Ag | Determination of the spectral behavior of electromagnetic signals within a given frequency range, for interference assessment, using a FFT to convert the signal into the frequency domain thus drastically reducing measurement time |
| CN101750545A (en) * | 2009-12-15 | 2010-06-23 | 北京空间飞行器总体设计部 | Electromagnetic compatibility test method for electric propulsion system |
| CN201909815U (en) * | 2010-12-14 | 2011-07-27 | 中国航空无线电电子研究所 | CS101 monitoring device |
| CN102723756A (en) * | 2012-06-18 | 2012-10-10 | 上海卫星工程研究所 | Full-digital power controller for satellite |
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