CN104007347A - Vacuum low-temperature radiosensitivity electromagnetic compatibility experimentation method, system and testing device - Google Patents
Vacuum low-temperature radiosensitivity electromagnetic compatibility experimentation method, system and testing device Download PDFInfo
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- CN104007347A CN104007347A CN201410234569.4A CN201410234569A CN104007347A CN 104007347 A CN104007347 A CN 104007347A CN 201410234569 A CN201410234569 A CN 201410234569A CN 104007347 A CN104007347 A CN 104007347A
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Abstract
The invention discloses a vacuum low-temperature radiosensitivity electromagnetic compatibility experimentation system which comprises an antenna, an electronics system, a laboratory power supply, a monitoring system and a testing device. The testing device comprises a vacuum tank, a vacuum pump and temperature control equipment. The vacuum tank comprises a stainless steel tank body and a wave-transparent glass window which is arranged at one end of the stainless steel tank body. The vacuum pump is communicated with the vacuum tank and carries out vacuumizing on the vacuum tank. The temperature control equipment is communicated with the vacuum tank and carries out low temperature or temperature rising control over the vacuum tank. A detector is arranged in the testing device and is electrically connected with the electronics system. The laboratory power supply provides a power source for the electronics system. The monitoring system is electrically connected with the electronics system. The antenna corresponds to the testing device and is close to the wave-transparent glass window. The vacuum tank is used in the testing device, so that the detector is contained, the vacuum tank is subjected to vacuumizing through the vacuum pump, the inner portion of the vacuum tank is controlled to be in a low-temperature environment through the temperature control equipment, and accordingly the detector is in a vacuum low-temperature testing environment.
Description
Technical field
The present invention relates to radiosensitivity EMC test field, especially relevant with the structure of the proving installation using in radiosensitivity EMC test.
Background technology
Because domestic space astronomical observation development is more late, the research of the detector of use (or claiming sensor or probe) in complex space environment and corresponding ground environmental testing is less, and future development space is large.Along with greatly developing of China's scientific satellite, hard X-ray Modulation Telescope satellite (is called for short: the development of space astronomy scientific satellite and the carrying out of a collection of military pre-research project such as HXMT), the space application of X ray class detector is more and more.In addition, the astronomical sight satellite of its all band (as infrared, visible ray, gamma rays etc.) also under study for action.The common feature of astronomical telescope is: be all that the feeble signal receiving in space is studied, therefore, detector and relevant front-end electronics, in order to reduce thermonoise, are often operated at lower temperature.In addition, the electronic equipment kind on satellite is numerous and diverse, and the antenna that sends strong electromagnetic wave wherein loading often easily forms and disturbs the detector device electronics of other equipment, particularly weak signal.
The EMC test of radiation class refers to: while checking multiple instrument to work in common electromagnetic space, and the electromagnetic effect each other producing by radiative process (conduction relatively).EMC test (EMC) is to carry out the test that must carry out before the useful load transmitting of space exploration.Useful load need to be passed through strict ground detection, to meet the compatible needs of electromagnetic environment between satellite equipment.The performance of the low energy X ray detector in HXMT satellite only just can detect the in the situation that of low temperature (lower than-30 ℃) and vacuum.Current conventional EMC laboratory, can only provide the test environment under normal temperature and pressure; GJB152A-97 < < military equipment and subsystem Electromagnetic Launching and susceptibility test > > have also only carried out standard and explanation to conventional detection method.Therefore judge the compatibility issue of the strong electromagnetic field sources such as X-ray detector and satellite transmitter, need to develop targetedly testing apparatus and explore corresponding method of testing.
Summary of the invention
For problems of the prior art, object of the present invention is for providing a kind of vacuum and low temperature radiosensitivity EMC test method, system and proving installation that vacuum, low-temperature test environment can be provided.
For achieving the above object, the invention provides following technical scheme:
The proving installation that vacuum and low temperature radiosensitivity EMC test is used, comprising:
Vacuum tank, described vacuum tank comprises stainless steel tank body and wave transparent windowpane, described wave transparent windowpane is arranged on one end of described stainless steel tank body;
Vacuum pump, described vacuum pump is communicated with described vacuum tank, and described vacuum tank is vacuumized;
Temperature control device, described temperature control device is communicated with described vacuum tank, and described vacuum tank is carried out low temperature or heat up controlling.
Further, also comprise support, vacuum tank described in described stent support.
Further, described temperature control device is connected with cold plate, and described cold plate is placed in described vacuum tank.
Further, on one end that described vacuum tank is relative with described wave transparent windowpane, be provided with electric connector.
Further, described vacuum pump is communicated with described vacuum tank by vacuum corrugated pipe.
Further, described vacuum tank is cylinder tank body.
For achieving the above object, the present invention also provides following technical scheme:
A kind of vacuum and low temperature radiosensitivity EMC test system, comprise antenna, electronic system, laboratory power supply and supervisory system, also comprise proving installation as above, accommodating detector in described proving installation, described detector is electrically connected described electronic system, and described laboratory power supply provides power supply for described electronic system, and described supervisory system is electrically connected described electronic system, the corresponding described proving installation of described antenna, and near described wave transparent windowpane.
Further, also comprise testing table, between described laboratory power supply and described electronic system, be also connected with line impedance stabilization net work, described proving installation, electronic system and line impedance stabilization net work are all arranged on described testing table.
Further, described supervisory system is arranged on a test with barrier shield within doors, and described antenna, proving installation, electronic system, line impedance stabilization net work, testing table and laboratory power supply are arranged in a darkroom.
For achieving the above object, the present invention also provides following technical scheme:
A vacuum and low temperature radiosensitivity EMC test method, comprising:
All testing apparatuss are all placed in standard testing darkroom, and proving installation is placed on submarginal position on testing table, and antenna is over against the wave transparent windowpane of vacuum tank, and cable adopts the mode of copper shield;
Field intensity detection probe is put into separately to vacuum tank, carry out the real-time measurement of field intensity in tank, and implement field calibration;
Guarantee that field intensity detection probe is positioned at position identical while testing with UUT, regulate the field intensity of antenna, the field intensity that field intensity detection probe is received, meets GJB152 institute required value;
The monitor value of real time record field intensity detection probe records model, the length apart from vacuum tank, height and the intensity etc. of antenna simultaneously.
Unit under test is tested, by being placed on the supervisory system in test room, real time record test data, whether the field intensity that check UUT is subject to meets the requirement of GJB152 and space flight;
Vacuum tank is first heated up and rises the method for air pressure again, treat that in tank, environment returns to normal temperature and pressure, take out UUT, and carry out equipment arrangement and interpretation of result.
The present invention compared with prior art, proving installation of the present invention adopts vacuum tank, with accommodating detector, and by vacuum pump, this vacuum tank is vacuumized, by temperature control device by vacuum tank internal control under low temperature environment, make in the test environment of detector in vacuum and low temperature, guarantee radiosensitivity EMC test effect.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, the present invention is described in further detail:
Fig. 1 is vacuum and low temperature radiosensitivity EMC test system architecture schematic diagram of the present invention;
Fig. 2 is the proving installation structural representation that vacuum and low temperature radiosensitivity EMC test of the present invention is used;
Fig. 3 is the absorption loss schematic diagram of quartz glass;
When Fig. 4 is vertical polarization, transmitance and incident angle is related to schematic diagram;
Fig. 5 is the schematic diagram that is related to of horizontal polarization transmitance and incident angle;
Fig. 6 is stainless shield effectiveness estimation result schematic diagram.
Embodiment
The exemplary embodiments that embodies feature & benefits of the present invention will describe in detail in the following description.Be understood that the present invention can have various variations on different embodiment, it neither departs from the scope of the present invention, and explanation wherein and accompanying drawing be when the use that explain in itself, but not in order to limit the present invention.
As shown in Figure 1, vacuum and low temperature radiosensitivity EMC test system of the present invention comprises antenna 6, testing table 7, proving installation 1, electronic system 2, line impedance stabilization net work 3, laboratory power supply 4 and supervisory system 5, and proving installation 1, electronic system 2 and line impedance stabilization net work 3 are all arranged on testing table 7.Supervisory system 5 is arranged on one to be had in the test room 9 of barrier shield 91, and antenna 6, proving installation 1, electronic system 2, line impedance stabilization net work 3, testing table 7 and laboratory power supply 4 are arranged in a darkroom 8.Accommodating detector 10 in proving installation 1, detector 10 is electrically connected electronic system 2, laboratory power supply 4 provides power supply for electronic system 2, line impedance stabilization net work 3 is arranged between laboratory power supply 4 and electronic system 2, supervisory system 5 is electrically connected electronic system 2, the corresponding proving installation 1 of antenna 6, and one end (shown in figure 2) of the wave transparent windowpane 12 of close proving installation 1.
As shown in Figure 2, the proving installation 1 that vacuum and low temperature radiosensitivity EMC test of the present invention is used comprises vacuum tank 11, vacuum pump 13, temperature control device 14, support 15, cold plate 17 and electric connector 18.Vacuum tank 11 is cylinder tank body, and vacuum tank 11 comprises stainless steel tank body and wave transparent windowpane 12, and wave transparent windowpane 12 is arranged on one end of stainless steel tank body.Vacuum pump 13 is communicated with vacuum tank 11 by vacuum corrugated pipe 16, and vacuum tank 11 is vacuumized.Temperature control device 14 is connected with cold plate 17, and cold plate 17 is placed in vacuum tank 11, and 14 pairs of vacuum tanks of temperature control device 11 carry out low temperature or heat up controlling.Support 15 supports vacuum tank 11, so that proving installation 1 is positioned on testing table 7.Electric connector 16 is arranged on one end that vacuum tank 11 is relative with wave transparent windowpane 12, as test probe insert port.
Proving installation 1 of the present invention meets GJB152 test frequency range and meets cryogenic vacuum environmental testing, can be carried into easily in darkroom 8 and test.The present invention meets the measurement of RS103 electromagnetic radiation sensitivity, 10k-40G Hz (GJB152A-97 < < military equipment and subsystem Electromagnetic Launching and susceptibility test > >.The applicable less tested equipment of the present invention (is called for short: EUT), special volume is: 10cm * 10cm * 2cm and following object.Vacuum tank 11 of the present invention adopts helium pulse refrigeration minimum reaching-100 ℃, while adopting conventional semiconductor refrigerating, can reach-30 ℃.Rapid and convenient of the present invention, because vacuum tank 11 volumes are less, when unloaded, the pumpdown time is no more than 2 hours, can arrive below 10-3Pa, during with load, is no more than 3 hours.
In proving installation of the present invention, vacuum tank 11 possesses 4 characteristics, specific as follows:
1. the design of vacuum tank 11 comprises electromagnetic transmission and reflection.Require 12 pairs of electromagnetic decay of wave transparent windowpane as far as possible little, select silica glass material for better; The main part of tank body 11 adopts stainless steel, to the conductivity of material and magnetic permeability without specific (special) requirements.
Quartz glass, dielectric coefficient is: 3.7; Relative permeability is: 1.
The transmitance of glass is supposed quartz glass relativepermeabilityμr=1 in calculating; The real part of specific inductive capacity: ∈ '=4; Imaginary part is ∈, and "=0.02. is losstangenttanδ=0.01 (in theory,, with frequency change, gets maximal value and consider in therefore calculating); Thickness is 0.012m.
1). absorption loss
Theoretical according to Plane electromagnetic field, unbounded evenly has electromagnetic loss in consumption ature of coal to be:
Wherein ω is angular frequency,
According to the RS103 regulation in GJB152A, calculate 10k-40GHz,
Quartz glass to electromagnetic decay, as shown in Figure 3: the absorption loss of visible glass itself is very little.
2). reflection loss
According to Fresnel law.
Z in formula
1, z
2be respectively the wave impedance of air and quartz glass.
θ
i, θ
tincident angle and angle of transmission while being respectively total transmissivity.
As shown in Figure 4, Figure 5, select different incident angles to have impact to transmitance, the incident angle of selecting in test is 0 °.
Stainless relative conductivity is about: 0.6; Relative permeability is: >1; Without specific (special) requirements.The shielding of stainless steel tank body 11 and reflection: as shown in Figure 6, the shield effectiveness of totally-enclosed stainless steel cavity slightly changes with frequency, draws, according to the shield effectiveness computing formula of metal material in the scope of 10kHz-40GHz, the minimum 60DB that reaches, can reflect all electromagnetic waves substantially.
2. vacuum tank 11 has good leakproofness, and vacuum tightness can reach below 10-3Pa.
Meanwhile, select the need of electric connector to guarantee diameter >30cm, be suitable for field intensity meter test probe and pass from outside, carry out field strength measurement.
3. whole vacuum tank 11 adopts syllogic design, and wave transparent windowpane 12 and miscellaneous part all can be dismantled separately, facilitate experimental test parts (being EUT equipment etc.) to be connected with test probe.
4. prevent from producing resonance under specific frequency, the inhomogeneous problem of field intensity in vacuum tank 11 tanks that cause, is therefore placed on UUT 10 (detector) as far as possible the place near wave transparent windowpane 12.
In addition, cold plate 17 adopts metal material, easily and between the rear plate of vacuum tank 11 form resonance, so between is not placed electronic unit and wire.
The method of EMC test, is divided into 4 steps, specific as follows:
1. the layout of experimental enviroment;
All testing apparatuss are all placed in standard testing darkroom 8, and wherein, proving installation 1 is placed on submarginal position on testing table 7, and antenna 6 is over against the wave transparent windowpane 12 of vacuum tank 11.And, need adopt to cable the mode of copper shield.
2. inner field intensity is demarcated environment in vacuum tank 11 tanks
Principle: adopt same position pairing comparision, guarantee that EUT is subject to field intensity identical with probe place is subject to before.Field intensity detection probe (detector) is put into separately to vacuum tank 11, carry out the real-time measurement of field intensity in tank.
Implement field calibration:
Place antenna 6 in suitable position, guarantee that field intensity detection probe is positioned at position identical while testing with EUT, regulates the field intensity of antenna 6, the field intensity that field strength measurement probe is received, meet GJB152 institute required value, if when field intensity is crossed by force or mistake is weak, the intensity of equal adjustable antenna 6 and position etc.
The monitor value of real time record field intensity detection probe records model, the length apart from vacuum tank 11, height and the intensity etc. of antenna simultaneously.
3. pair unit under test 10 is tested
By being placed on the supervisory system in test room, real time record test data, proves that field intensity that detector 10 is subject to meets the requirement of GJB152 and space flight.
4. after test, equipment arranges and interpretation of result
Vacuum tank 11 first heats up and rises the method for air pressure again, treats that in tank, environment returns to normal temperature and pressure, can take out EUT and complete test.
The present invention compared with prior art, proving installation of the present invention adopts vacuum tank 11, with accommodating detector 10, and vacuumize by 13 pairs of these vacuum tanks 11 of vacuum pump, by temperature control device 14 by vacuum tank 11 internal controls under low temperature environment, make in the test environment of detector 10 in vacuum and low temperature, guarantee radiosensitivity EMC test effect.
Technical scheme of the present invention is disclosed as above by preferred embodiment.Those skilled in the art should recognize in the situation that do not depart from change and the retouching that scope and spirit of the present invention that the appended claim of the present invention discloses are done, within all belonging to the protection domain of claim of the present invention.
Claims (10)
1. the proving installation that vacuum and low temperature radiosensitivity EMC test is used, is characterized in that, comprising:
Vacuum tank, described vacuum tank comprises stainless steel tank body and wave transparent windowpane, described wave transparent windowpane is arranged on one end of described stainless steel tank body;
Vacuum pump, described vacuum pump is communicated with described vacuum tank, and described vacuum tank is vacuumized;
Temperature control device, described temperature control device is communicated with described vacuum tank, and described vacuum tank is carried out low temperature or heat up controlling.
2. the proving installation that vacuum and low temperature radiosensitivity EMC test as claimed in claim 1 is used, is characterized in that, also comprises support, vacuum tank described in described stent support.
3. the proving installation that vacuum and low temperature radiosensitivity EMC test as claimed in claim 1 is used, is characterized in that, described temperature control device is connected with cold plate, and described cold plate is placed in described vacuum tank.
4. the proving installation that vacuum and low temperature radiosensitivity EMC test as claimed in claim 1 is used, is characterized in that, described vacuum tank is provided with electric connector on one end relative with described wave transparent windowpane.
5. the proving installation that vacuum and low temperature radiosensitivity EMC test as claimed in claim 1 is used, is characterized in that, described vacuum pump is communicated with described vacuum tank by vacuum corrugated pipe.
6. the proving installation that vacuum and low temperature radiosensitivity EMC test as claimed in claim 1 is used, is characterized in that, described vacuum tank is cylinder tank body.
7. a vacuum and low temperature radiosensitivity EMC test system, comprise antenna, electronic system, laboratory power supply and supervisory system, it is characterized in that, also comprise the proving installation as described in as arbitrary in claim 1-6, accommodating detector in described proving installation, described detector is electrically connected described electronic system, described laboratory power supply provides power supply for described electronic system, described supervisory system is electrically connected described electronic system, the corresponding described proving installation of described antenna, and near described wave transparent windowpane.
8. vacuum and low temperature radiosensitivity EMC test system as claimed in claim 7, it is characterized in that, also comprise testing table, between described laboratory power supply and described electronic system, be also connected with line impedance stabilization net work, described proving installation, electronic system and line impedance stabilization net work are all arranged on described testing table.
9. vacuum and low temperature radiosensitivity EMC test system as claimed in claim 8, it is characterized in that, described supervisory system is arranged on a test with barrier shield within doors, and described antenna, proving installation, electronic system, line impedance stabilization net work, testing table and laboratory power supply are arranged in a darkroom.
10. a vacuum and low temperature radiosensitivity EMC test method, is characterized in that, comprising:
All testing apparatuss are all placed in standard testing darkroom, and proving installation is placed on submarginal position on testing table, and antenna is over against the wave transparent windowpane of vacuum tank, and cable adopts the mode of copper shield;
Field intensity detection probe is put into separately to vacuum tank, carry out the real-time measurement of field intensity in tank, and implement field calibration;
Guarantee that field intensity detection probe is positioned at position identical while testing with UUT, regulate the field intensity of antenna, the field intensity that field intensity detection probe is received, meets GJB152 institute required value;
The monitor value of real time record field intensity detection probe records model, the length apart from vacuum tank, height and the intensity etc. of antenna simultaneously.
Unit under test is tested, by being placed on the supervisory system in test room, real time record test data, whether the field intensity that check UUT is subject to meets the requirement of GJB152 and space flight;
Vacuum tank is first heated up and rises the method for air pressure again, treat that in tank, environment returns to normal temperature and pressure, take out UUT, and carry out equipment arrangement and interpretation of result.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106291189A (en) * | 2016-08-15 | 2017-01-04 | 北京航空航天大学 | A kind of undisturbed reconfigurable type multiple electromagnetic interference detecting device simulating real border and detection method |
| CN108761217A (en) * | 2018-05-22 | 2018-11-06 | 西安空间无线电技术研究所 | It is a kind of that system is tested based on the micro discharge for inhaling wave darkroom |
| CN110086550A (en) * | 2018-01-22 | 2019-08-02 | 中国移动通信有限公司研究院 | A kind of full temperature OTA test device and method |
| CN113009250A (en) * | 2021-02-23 | 2021-06-22 | 航天科工空间工程发展有限公司 | Testing arrangement of wire current-carrying capacity under low pressure environment |
| CN113295939A (en) * | 2021-03-29 | 2021-08-24 | 一汽奔腾轿车有限公司 | Vacuum pump electromagnetic compatibility test system and control method thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN102323507A (en) * | 2011-09-06 | 2012-01-18 | 航天东方红卫星有限公司 | Radiation electromagnetic compatibility test method for electric propulsion system and on-star radio frequency equipment |
| CN102435872A (en) * | 2011-09-06 | 2012-05-02 | 航天东方红卫星有限公司 | Method for verifying radiation electromagnetic compatibility of electric propulsion system and satellite |
| CN203858313U (en) * | 2014-05-29 | 2014-10-01 | 中国科学院高能物理研究所 | Vacuum low-temperature radiation susceptibility electromagnetic compatible test system and testing device |
-
2014
- 2014-05-29 CN CN201410234569.4A patent/CN104007347B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN102323507A (en) * | 2011-09-06 | 2012-01-18 | 航天东方红卫星有限公司 | Radiation electromagnetic compatibility test method for electric propulsion system and on-star radio frequency equipment |
| CN102435872A (en) * | 2011-09-06 | 2012-05-02 | 航天东方红卫星有限公司 | Method for verifying radiation electromagnetic compatibility of electric propulsion system and satellite |
| CN203858313U (en) * | 2014-05-29 | 2014-10-01 | 中国科学院高能物理研究所 | Vacuum low-temperature radiation susceptibility electromagnetic compatible test system and testing device |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106291189A (en) * | 2016-08-15 | 2017-01-04 | 北京航空航天大学 | A kind of undisturbed reconfigurable type multiple electromagnetic interference detecting device simulating real border and detection method |
| CN106291189B (en) * | 2016-08-15 | 2019-01-25 | 北京航空航天大学 | Simulate the undisturbed reconfigurable type multiple electromagnetic interference detecting device and method of real border |
| CN110086550A (en) * | 2018-01-22 | 2019-08-02 | 中国移动通信有限公司研究院 | A kind of full temperature OTA test device and method |
| CN110086550B (en) * | 2018-01-22 | 2022-04-08 | 中国移动通信有限公司研究院 | Full-temperature OTA testing device and method |
| CN108761217A (en) * | 2018-05-22 | 2018-11-06 | 西安空间无线电技术研究所 | It is a kind of that system is tested based on the micro discharge for inhaling wave darkroom |
| CN113009250A (en) * | 2021-02-23 | 2021-06-22 | 航天科工空间工程发展有限公司 | Testing arrangement of wire current-carrying capacity under low pressure environment |
| CN113295939A (en) * | 2021-03-29 | 2021-08-24 | 一汽奔腾轿车有限公司 | Vacuum pump electromagnetic compatibility test system and control method thereof |
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