CN108205089A - A kind of whole star Electro Magnetic Compatibility verification method and system based on electric propulsion radiation-emitting simulator - Google Patents
A kind of whole star Electro Magnetic Compatibility verification method and system based on electric propulsion radiation-emitting simulator Download PDFInfo
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- CN108205089A CN108205089A CN201711456394.1A CN201711456394A CN108205089A CN 108205089 A CN108205089 A CN 108205089A CN 201711456394 A CN201711456394 A CN 201711456394A CN 108205089 A CN108205089 A CN 108205089A
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- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
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Abstract
A kind of whole star Electro Magnetic Compatibility verification method and system based on electric propulsion radiation-emitting simulator, first under vacuum, obtain the radiation-emitting parameter of the electric propulsion system under true ignition condition；Next builds electric propulsion electromagnetic radiation simulator, which can generate the electromagnetic radiation identical with the radiation-emitting parameter under the true ignition condition of electric propulsion system；Finally in whole star emc testing, the electric propulsion radiation-emitting under the conditions of vacuum firing is substituted using electric propulsion radiation-emitting simulator, completes the test and assessment of the satellite Electro Magnetic Compatibility of configuration electric propulsion system.The present invention tests itself radiation interference strength range to satellite of electric thruster normal work, test frequency range covering 1GHz~31GHz frequency ranges, electric propulsion working electromagnet radiation interference magnitude confirmed by above-mentioned three phases test, the electromagnetic radiation effect of the electric propulsion course of work does not interfere with normal work of the whole star communication payload in L frequency ranges, C frequency ranges, Ku frequency ranges and Ka frequency ranges.
Description
Technical field
The present invention relates to a kind of whole star Electro Magnetic Compatibility verification method and system based on electric propulsion radiation-emitting simulator,
Belong to the technical field of electromagnetic compatibility experimentation for the satellite for being configured with electric propulsion system.
Background technology
Electric propulsion system has the characteristics that high specific impulse, low thrust as a kind of advanced satellite booster technology, can be effective
Promote the bearing capacity and control accuracy of spacecraft, it has also become the standard configuration of each advanced spacecraft of astropower.
Electric propulsion system igniting requirement carries out under conditions of vacuum environment and configuration plasma safeguard, and satellite
Electro Magnetic Compatibility verification should carry out in the Electro Magnetic Compatibility laboratory of profession.The Electro Magnetic Compatibility verification test equipment of profession cannot
There is provided vacuum environment, therefore can not under the true ignition condition of electric propulsion the satellite of direct measuring configuration electric propulsion system electricity
Magnetic compatibility.Electro Magnetic Compatibility verification for the satellite for completing configuration electric propulsion system, needs design to utilize ground-based simulation equipment
The scheme measured indirectly.
Its emc issue of electric propulsion applied satellite is currently a completely new research topic, since electric propulsion needs
Vacuum environment is operated in, therefore can not directly be obtained when assessing electric propulsion and whole star electromagnetic compatibility being influenced by measurement method.
In-orbit data assessment electric propulsion work can not still be accumulated at present influences the Electro Magnetic Compatibility of satellite, it is therefore desirable to more than solving not
Foot.
Invention content
Present invention solves the technical problem that it is：It overcomes the shortage of prior art, provides a kind of based on electric propulsion radiation-emitting mould
Intend the whole star Electro Magnetic Compatibility verification method and system of device, the need that electric propulsion system can only light a fire in vacuum environment can be solved
The contradiction that cannot be provided with existing satellite electromagnetic compatibility row experimental enviroment between vacuum environment is provided.The present invention proposes a kind of utilization
The whole star Electro Magnetic Compatibility verification method of electromagnetic radiation simulator is carried out suitable for the satellite for being configured with electric propulsion system on ground
The test of EMC test and appraisal procedure solve the Electro Magnetic Compatibility assessment problem of satellite application electric propulsion technology.
The technical solution that the present invention solves is：A kind of whole star Electro Magnetic Compatibility based on electric propulsion radiation-emitting simulator is tested
Card method, it is characterised in that step is as follows：
(1) the radiation-emitting parameter under electric thruster fired state is obtained；
(2) electric propulsion radiation-emitting simulator is built according to the radiation-emitting parameter of step (1), makes electric propulsion radiation-emitting
Simulator has simulates radiation-emitting under electric thruster fired state in the satellite operation full frequency band of configuration electric propulsion system
Ability；
(3) whole star Electro Magnetic Compatibility laboratory to be configured electric propulsion system satellite Electro Magnetic Compatibility carry out test and
Assessment
(4) by the disturbed situation for the satellite that electric propulsion system is configured in detection process, judge electric propulsion system is configured
The Electro Magnetic Compatibility of satellite, the Electro Magnetic Compatibility of the complete satellite for being organized in pairs electric propulsion system are tested and are assessed.
Step (1) obtains the radiation-emitting parameter under electric thruster fired state, and step is as follows：
(1) electric thruster is placed in wave transparent cabin, to being vacuumized in wave transparent cabin, vacuum degree is better than 1 × 10-3Pa；
(2) electric thruster is lighted a fire under vacuum conditions, and electric thruster igniting requirement keeps power supply and the gas supply of stabilization
Environment,
Ensure that external environment reduces result of the test interference effect, and wave transparent is placed in out of my cabin by a reception antenna in this way, it is right
The back side of quasi- electric thruster, another reception antenna are placed in wave transparent out of my cabin, are directed toward perpendicular to the side of electric thruster；
(4) the radiation-emitting parameter of electric thruster received respectively using measuring instrument two reception antennas of measurement, test
Obtain radiation-emitting order magnitude range；
Step (2) builds electric propulsion radiation-emitting simulator according to the radiation-emitting parameter of step (1), radiates electric propulsion
Launching simulator has radiates hair in the satellite operation full frequency band of configuration electric propulsion system under simulation electric thruster fired state
The ability penetrated, step are as follows：
(1) electromagnetic interference receiver detects and controls the electric thruster radiation-emitting parameter of equipment acquisition according to ground, gives
Preamplifier provides the input of frequency and field strength；
(2) preamplifier externally emits electromagnetic wave according to frequency and field strength using antenna, that is, simulates electric thruster fired state
The ability of lower radiation-emitting.
Step (3) surveys the Electro Magnetic Compatibility that the satellite of electric propulsion system is configured in whole star Electro Magnetic Compatibility laboratory
Examination and assessment, step are as follows：
(1) satellite that electric propulsion system is configured is placed in whole star Electro Magnetic Compatibility laboratory, Satellite Simulation is in-orbit to be in
Normal operating conditions；
(2) radiation-emitting parameter amount of the electric propulsion radiation-emitting simulator according to electric thruster is used in satellite horizontal direction
Grade injects the Radiative EMI magnitude of 2 times of radiation-emitting parameter maximum values；
(3) it is set up at a distance into certain distance in the satellite of whole star Electro Magnetic Compatibility experiment indoor distances configuration electric propulsion system
Field intensity probe measures and confirms the field strength applied in setting frequency range；
(4) whole star Electro Magnetic Compatibility is detected by antenna and tests indoor radiation-emitting characteristic, pass through collection analysis electromagnetism
Wave field confirms by force the disturbed magnitude of satellite with the variation of frequency.
Step (4) judges electric propulsion system is configured by the disturbed situation of the satellite of configuration electric propulsion system in detection process
The Electro Magnetic Compatibility of the satellite of system, the Electro Magnetic Compatibility of the complete satellite for being organized in pairs electric propulsion system are tested and are assessed, step
It is rapid as follows：
(1) interference field strength threshold value is set in frequency band of detection, when the radio field intensity of step (3) antenna detection is higher than setting
Interference field strength threshold value when, judgement configuration electric propulsion system satellite Electro Magnetic Compatibility it is unqualified；Otherwise, it is determined that configuration electricity pushes away
Electro Magnetic Compatibility into the satellite of system is qualified.
Electric propulsion radiation-emitting simulator has tranmitting frequency more than or equal to 30MHz and less than electromagnetic wave in the range of 40GHz
Radiation-emitting ability, wherein more than or equal to 30MHz and less than 1GHz band radiations launching simulation using in advance putting and period logarithm
Antenna is realized, is realized more than or equal to 1GHz and less than 18GHz band radiations launching simulation using pre- put with double-ridged horn antenna, greatly
It realizes, is more than or equal to electromagnetic horn in equal to 18GHz and less than 26.5GHz band radiations launching simulation using pre- put
26.5GHz and less than 40GHz band radiations launching simulation using in advance put and electromagnetic horn realize.
Electric propulsion radiation-emitting simulator externally export electromagnetic wave frequency and field strength under electric propulsion fired state
Radiation-emitting parameter is consistent, and the field strength parameter of frequency is obtained, and need to be true by the radiation emission test result of electric propulsion
It is tested under null point fire environment.
When the test of satellite radiosensitivity is carried out, field intensity probe is being set up at a distance apart from electric propulsion 1m, satellite is penetrated
When frequency frequency acceptance band is observing and controlling frequency acceptance band, interference field strength threshold value is set to be not lower than 2V/m in the test frequency range；Communication relates to
And the satellite RF frequency acceptance band arrived be communication band when, in the test frequency range set interference field strength threshold value be not lower than 4V/
m；Field intensity probe is located at quick position, and whole star power-up procedures maximum field strength threshold value is not lower than 3V/m.
Measurand is that the satellite of electric propulsion system is configured, including：Electric thruster and its power supply, air supply system；Electric thrust
Device is located at outside the deck board of satellite.
Whole star Electro Magnetic Compatibility laboratory, is non-closed environment, has the ability of shielding outside electromagnetic interference, the electricity of satellite
Magnetic compatibility test is normal temperature and pressure conditions.
Electric propulsion radiation-emitting simulator, including：Electromagnetic interference receiver, multiple preamplifiers, mutiple antennas；It can also wrap
Include wave filter；
Ground detection and control device obtain the radiation-emitting parameter of point thruster；
Electromagnetic interference receiver detects and controls the radiation-emitting parameter of equipment acquisition according to ground, and frequency is provided to preamplifier
The input of rate and field strength, preamplifier externally emit electromagnetic wave according to frequency and field strength using antenna.
A kind of whole star Electro Magnetic Compatibility verification system based on electric propulsion radiation-emitting simulator, including：Acquisition module is taken
Model block, test and evaluation module, judgment module；
Acquisition module obtains the radiation-emitting parameter under electric thruster fired state；
It builds module and electric propulsion radiation-emitting simulator is built according to the radiation-emitting parameter of step (1), make electric propulsion spoke
Penetrate launching simulator have configuration electric propulsion system satellite operation full frequency band in simulation electric thruster fired state under radiate
The ability of transmitting；
Test and evaluation module are in whole star Electro Magnetic Compatibility laboratory to the electromagnetic compatibility of the satellite of configuration electric propulsion system
Property is tested and is assessed
Judgment module judges electric propulsion system is configured by the disturbed situation of the satellite of configuration electric propulsion system in detection process
The Electro Magnetic Compatibility of the satellite of system, the Electro Magnetic Compatibility of the complete satellite for being organized in pairs electric propulsion system are tested and are assessed.
The advantages of the present invention over the prior art are that：
(1) present invention solves demand that electric propulsion system can only light a fire in vacuum environment and existing satellite electromagnetism is simultaneous
Compatibility test environment cannot provide the contradiction between vacuum environment, and the satellite for electric propulsion system is configured carries out whole star electromagnetic compatibility
The test and assessment of property provide approach.
(2) the present invention provides the radiation-emittings that 225MHz~31GHz range tests obtain electric thruster operated under vacuum
Magnitude realizes that the Electro Magnetic Compatibility under whole star environment is assessed in 10~70dB μ V/m ranges, and according to this condition.
(3) the present invention provides satellite electromagnetic compatibility judgment criterions, and survey is provided for satellite and electric thruster electromagnetic compatibility
Try interpretation foundation.
(4) the present invention provides assessment electric propulsion to the anti-interference threshold value of other subsystem compatibility tests of satellite, at this
It may determine that the satellite other equipment course of work will not be influenced by electric propulsion work under threshold value as defined in invention.
Description of the drawings
Fig. 1 is the schematic layout pattern that the present invention obtains radiation-emitting parameter under electric propulsion fired state using wave transparent cabin；
Fig. 2 is electric thruster electromagnetic radiation simulator operating diagram of the present invention；
Fig. 3 is the satellite Electro Magnetic Compatibility that the present invention carries out configuration electric propulsion system using electric propulsion radiation-emitting simulator
The schematic layout pattern of experiment；
Fig. 4 is radiation-emitting simulator reality output frequency range of the present invention and intensity.
Fig. 5 is the flow chart of the present invention
Specific embodiment
The present invention is described in further detail in the following with reference to the drawings and specific embodiments.
A kind of whole star Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator of the present invention, first true
Under empty condition, emc testing is individually carried out to configuring standby electric propulsion system, is obtained electric under true ignition condition
The radiation-emitting parameter of propulsion system；Next builds electric propulsion electromagnetic radiation simulator, which can generate and electricity
The identical electromagnetic radiation of radiation-emitting parameter under the true ignition condition of propulsion system；Finally surveyed in whole star Electro Magnetic Compatibility
During examination, the electric propulsion radiation-emitting under the conditions of vacuum firing is substituted using electric propulsion radiation-emitting simulator, configuration electricity is completed and pushes away
Into the test and assessment of the satellite Electro Magnetic Compatibility of system.Add the test request of tight frequency range according to satellite, carry out whole star in electricity
Promote Electromagnetic Launching test (the Radiated emission test before and after work:RE102), the normal work of electric thruster is tested
Itself the radiation interference strength range to satellite made, test frequency range covering 1GHz~31GHz frequency ranges, passes through three above-mentioned ranks
Section test confirmed electric propulsion working electromagnet radiation interference magnitude in 10~60dB μ V/m ranges, the electromagnetism of the electric propulsion course of work
Radiation effect does not interfere with normal work of the whole star communication payload in L frequency ranges, C frequency ranges, Ku frequency ranges and Ka frequency ranges.
A kind of whole star Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator of the present invention, step is such as
Under：
(1) the radiation-emitting parameter under electric thruster fired state is obtained；
(2) electric propulsion radiation-emitting simulator is built according to the radiation-emitting parameter of step (1), makes electric propulsion radiation-emitting
Simulator has simulates radiation-emitting under electric thruster fired state in the satellite operation full frequency band of configuration electric propulsion system
Ability；
(3) whole star Electro Magnetic Compatibility laboratory to be configured electric propulsion system satellite Electro Magnetic Compatibility carry out test and
Assessment
(4) by the disturbed situation for the satellite that electric propulsion system is configured in detection process, judge electric propulsion system is configured
The Electro Magnetic Compatibility of satellite, the Electro Magnetic Compatibility of the complete satellite for being organized in pairs electric propulsion system are tested and are assessed.
Step (1) obtains the radiation-emitting parameter under electric thruster fired state, and step is as follows：
(1) electric thruster is placed in wave transparent cabin, to being vacuumized in wave transparent cabin, vacuum degree is better than 1 × 10-3Pa；
(2) electric thruster is lighted a fire under vacuum conditions, and electric thruster igniting requirement keeps power supply and the gas supply of stabilization
Environment, in 1000V ± 10V, screen-grid current stabilization exists power supply screen-grid voltage stabilization in 0.8A ± 0.05A, total gas supply flow stabilization
1.362 ± 5%mg/s；
(3) thruster electromagnetic property test is implemented in shielded anechoic chamber, ensures that external environment interferes result of the test in this way
It influences to reduce, a reception antenna is placed in wave transparent out of my cabin, the back side for being directed at electric thruster (refers to electric thruster vacuum firing spray
Penetrate the negative direction of gas ions), another reception antenna is placed in wave transparent out of my cabin, is directed toward that (side is perpendicular to the side of electric thruster
Refer to the parallel direction of plasma line)；
(4) the radiation-emitting parameter of electric thruster received respectively using measuring instrument two reception antennas of measurement,
225MHz~31GHz range tests obtain radiation-emitting magnitude in 10~70dB μ V/m ranges；
Step (2) builds electric propulsion radiation-emitting simulator according to the radiation-emitting parameter of step (1), radiates electric propulsion
Launching simulator has radiates hair in the satellite operation full frequency band of configuration electric propulsion system under simulation electric thruster fired state
The ability penetrated, step are as follows：
(1) electromagnetic interference receiver detects and controls the electric thruster radiation-emitting parameter of equipment acquisition according to ground, gives
Preamplifier provides the input of frequency and field strength；
(2) preamplifier externally emits electromagnetism according to frequency and field strength (before transmitting first by filter filtering after) using antenna
Wave simulates the ability of radiation-emitting under electric thruster fired state.
Step (3) surveys the Electro Magnetic Compatibility that the satellite of electric propulsion system is configured in whole star Electro Magnetic Compatibility laboratory
Examination and assessment, step are as follows：
(1) satellite that electric propulsion system is configured is placed in whole star Electro Magnetic Compatibility laboratory, Satellite Simulation is in-orbit to be in
Normal operating conditions.
(2) in satellite horizontal direction (horizontal direction refers to direction parallel to the ground) using electric propulsion radiation-emitting simulator
According to the radiation-emitting parameter ranges (simulation context 10~65dB μ V/m) of electric thruster, the radiation electric of 2 times of maximum values is injected
Magnetic disturbance magnitude, i.e. 130dB μ V/m (3V/m).
(3) whole star Electro Magnetic Compatibility experiment indoor distances configuration electric propulsion system satellite into certain distance (0.1m~
3m) setting up field intensity probe at a distance, (isotropism electric field probe covers 10kHz-40GHz ranges, and resolution ratio 0.01v/m measures model
Enclose 0.15-3000V/m, 1V/m=log10 (10e6 × 20) dB μ V/m), it measures and confirms in the application of 30MHz~31GHz frequency ranges
Field strength for 3V/m,.
(4) whole star Electro Magnetic Compatibility is detected by antenna and tests indoor radiation-emitting characteristic, pass through collection analysis electromagnetism
Wave field confirms by force the disturbed magnitude of satellite with the variation of frequency.
Step (4) judges electric propulsion system is configured by the disturbed situation of the satellite of configuration electric propulsion system in detection process
The Electro Magnetic Compatibility of the satellite of system, the Electro Magnetic Compatibility of the complete satellite for being organized in pairs electric propulsion system are tested and are assessed, step
It is rapid as follows：
(1) interference field strength threshold value is set in frequency band of detection, when the radio field intensity of step (3) antenna detection is higher than setting
Interference field strength threshold value when, judgement configuration electric propulsion system satellite Electro Magnetic Compatibility it is unqualified；Otherwise, it is determined that configuration electricity pushes away
Electro Magnetic Compatibility into the satellite of system is qualified.
Electric propulsion radiation-emitting simulator has tranmitting frequency more than or equal to 30MHz and less than electromagnetic wave in the range of 40GHz
Radiation-emitting ability, wherein more than or equal to 30MHz and less than 1GHz band radiations launching simulation using in advance putting and period logarithm
Antenna is realized, is realized more than or equal to 1GHz and less than 18GHz band radiations launching simulation using pre- put with double-ridged horn antenna, greatly
It realizes, is more than or equal to electromagnetic horn in equal to 18GHz and less than 26.5GHz band radiations launching simulation using pre- put
26.5GHz and less than 40GHz band radiations launching simulation using in advance put and electromagnetic horn realize.
Electric propulsion radiation-emitting simulator externally export electromagnetic wave frequency and field strength under electric propulsion fired state
Radiation-emitting parameter is consistent, and the field strength parameter of frequency is obtained, and need to be true by the radiation emission test result of electric propulsion
It is tested under null point fire environment.
When the test of satellite radiosensitivity is carried out, field intensity probe is being set up at a distance apart from electric propulsion 1m, satellite is penetrated
When frequency frequency acceptance band is observing and controlling frequency acceptance band, interference field strength threshold value is set to be not lower than 2V/m in the test frequency range；Communication relates to
And the satellite RF frequency acceptance band arrived be communication band when, in the test frequency range set interference field strength threshold value be not lower than 4V/
m；Field intensity probe is located at quick position, and whole star power-up procedures maximum field strength threshold value is not lower than 3V/m.
Measurand is that the satellite of electric propulsion system is configured, including：Electric thruster and its power supply, air supply system；Electric thrust
Device is located at outside the deck board of satellite,；
Whole star Electro Magnetic Compatibility laboratory, is non-closed environment, has the ability of shielding outside electromagnetic interference, the electricity of satellite
Magnetic compatibility test is normal temperature and pressure conditions.
Electric propulsion radiation-emitting simulator, including：Electromagnetic interference receiver (EMI receivers), multiple preamplifiers, Duo Getian
Line；It can also include wave filter；
Ground detection and control device obtain the radiation-emitting parameter of point thruster；
Electromagnetic interference receiver detects and controls the radiation-emitting parameter of equipment acquisition according to ground, and frequency is provided to preamplifier
The input of rate and field strength, preamplifier externally emit electromagnetic wave according to frequency and field strength (after filter filtering) using antenna.
A kind of currently preferred whole star Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator, step
It is rapid as follows：
(1) thruster electromagnetic property test is implemented in shielded anechoic chamber, ensures that external environment interferes result of the test in this way
It influences to reduce, as shown in Figure 1.First, electric thruster is placed in wave transparent cabin, test antenna is arranged in shielded anechoic chamber,
In a reception antenna be placed in wave transparent out of my cabin, be aligned at the back side of electric thruster (refer to electric thruster vacuum firing injection ion
The negative direction of body), distance 1m, another reception antenna is placed in wave transparent out of my cabin, is directed toward that (side is perpendicular to the side of electric thruster
Refer to the parallel direction of plasma line), distance 1m；Secondly, to being vacuumized in wave transparent cabin, vacuum degree is better than 1 × 10-3Pa；So
Electric thruster is lighted a fire under vacuum conditions afterwards, and electric thruster igniting requirement keeps the power supply of stabilization and gas supply environment, power supply
Screen-grid voltage stabilization is in 1000V ± 10V, and screen-grid current stabilization is in 0.8A ± 0.05A, and total gas supply flow stabilization is 1.362 ± 5%
mg/s。
(2) the radiation-emitting parameter of electric thruster received respectively using measuring instrument two reception antennas of measurement,
225MHz~31GHz range tests obtain radiation-emitting magnitude in 10~70dB μ V/m ranges, so as to obtain electric thruster igniting
Radiation-emitting parameter under state；
(3) electric propulsion radiation-emitting simulator is built according to the radiation-emitting parameter of step (2), makes electric propulsion radiation-emitting
Simulator has simulates radiation-emitting under electric thruster fired state in the satellite operation full frequency band of configuration electric propulsion system
Ability；
(4) it realizes and the Electro Magnetic Compatibility that the satellite of electric propulsion system is configured is surveyed in whole star Electro Magnetic Compatibility laboratory
Examination and the process description of assessment.The satellite Electro Magnetic Compatibility assessment content that electric propulsion system is configured is in-orbit section of radiation-emitting of simulation
When period investigates satellite operation under main part operating mode and maximum configured operating mode, can whole star be compatible with sex work, remember simultaneously
Satellite generated electromagnetic radiation situation in itself is recorded, data are provided for later EMC analysis work.It is whole such as Fig. 2
Shown in star emc testing schematic diagram, the satellite (abbreviation electric propulsion satellite) of the configuration electric propulsion system of test is arranged in electricity
Magnetic compatibility laboratory center is setting up test electric propulsion radiation-emitting simulator away from celestial body 1m, and real during the test at a distance
The electromagnetic radiation data of Shi Jilu 30MHz~31GHz frequency ranges.
In-orbit section of radiation emission test principle is simulated as shown in figure 3, electric propulsion radiation-emitting simulator includes covering difference
The multichannel preamplifier and wave filter of frequency range demand, while mating a variety of antennas.The realization method of antenna is：Electric propulsion radiation hair
It penetrates simulator and has tranmitting frequency more than or equal to 30MHz and less than the radiation-emitting ability of electromagnetic wave in the range of 40GHz, wherein greatly
It is realized in equal to 30MHz and less than 1GHz band radiations launching simulation using pre- put with period logarithm antenna, more than or equal to 1GHz
And realized less than 18GHz band radiations launching simulation using pre- put with double-ridged horn antenna, more than or equal to 18GHz and it is less than
26.5GHz band radiations launching simulation is realized using pre- put with electromagnetic horn, more than or equal to 26.5GHz and less than 40GHz frequency ranges
Radiation-emitting simulation utilization is put in advance and electromagnetic horn is realized.
Specific whole star electromagnetic compatibility test realization method is as follows：Test process sets up test days at a distance away from celestial body 1m first
Line, records the electromagnetic radiation data of 30MHz~31GHz frequency ranges, and antenna polarization requirement is equal for horizontal polarization and vertical polarization
It is tested；Secondly, during test, satellite is in maximum configured working condition, respectively at satellite+X faces and-X identity distances are from 1 meter
Radiative EMI is generated using simulator, i.e., electromagnetic interference receiver is according to electric thruster radiation-emitting parameter, to preamplifier
The input of frequency and field strength is provided, preamplifier externally emits electromagnetism according to frequency and field strength (after filter filtering) using antenna
Wave, that is, simulate the ability of radiation-emitting under electric thruster fired state, and practical electric thruster vacuum work electromagnetic radiation experiment is surveyed
Range is tried in 10~65dB μ V/m, whole star test according to margin requirement, injects the Radiative EMI amount of 2 times of maximum values
Grade, i.e. 130dB μ V/m (3V/m；Then, field intensity probe is being set up at electric propulsion 0.1m~3m, is ensureing field intensity probe monitoring
To interference strength meet electric propulsion electromagnetic radiation magnitude requirement, at this time using receiver record test result, monitoring satellite be
It is no disturbed, isotropism electric field probe covering 10kHz-40GHz ranges, resolution ratio 0.01v/m, measurement range 0.15-3000V/
M, 1V/m=log10 (10e6 × 20) dB μ V/m).
Interference field strength threshold value is set in frequency band of detection, when the radio field intensity that antenna detects in step (4) is higher than setting
Interference field strength threshold value when, judgement configuration electric propulsion system satellite Electro Magnetic Compatibility it is unqualified；Otherwise, it is determined that configuration electricity pushes away
Electro Magnetic Compatibility into the satellite of system is qualified.Currently preferred satellite electromagnetic compatibility judgment criterion is：
(5) satellite radiosensitivity test is carried out.The field strength of satellite key position is measured, judges electric propulsion system is configured
The Electro Magnetic Compatibility of satellite, the Electro Magnetic Compatibility of the complete satellite for being organized in pairs electric propulsion system are tested and are assessed.It is specific
Way is：
Field intensity probe is being moved at 0.3~1m of electric propulsion, is being placed near quick, star is quick neighbouring and other are sensitive
Near equipment, the disturbed situation of satellite band, threshold requirement as shown in Figure 4, explanation under test electric propulsion simulation working environment
It is as follows：When usual satellite RF frequency acceptance band is observing and controlling frequency acceptance band, interference field strength threshold value is set should not in the test frequency range
Less than 2V/m；When the satellite RF frequency acceptance band being related to that communicates is communication band, interference field strength is set in the test frequency range
Threshold value is not lower than 4V/m；Field intensity probe is located at quick position, and whole star power-up procedures maximum field strength threshold value is not lower than 4V/m.
Whole star Electro Magnetic Compatibility is assessed by adjusting antenna detecting location and tests indoor radiation-emitting characteristic, passes through acquisition
Analysis radio field intensity confirms the disturbed magnitude of satellite with the variation of frequency.
(5) Fig. 5 describes the realization flow of the whole star electromagnetic compatibility test based on electromagnetic radiation simulator.It is logical first
The electromagnetic radiation characteristic crossed under individual ground vacuum thruster fired state measures, and obtains the spoke under electric thruster fired state
Emission parameter is penetrated, the demand that solving electric propulsion system can only light a fire in vacuum environment is tried with existing satellite Electro Magnetic Compatibility
Contradiction between vacuum environment cannot be provided by testing environment, and the satellite for electric propulsion system is configured carries out the survey of whole star Electro Magnetic Compatibility
Examination and assessment provide approach；Secondly, electric propulsion radiation-emitting simulator is built according to the data of test, carries out whole star normal pressure shape
Electromagnetic compatibility test under state.225MHz~31GHz range tests, which are realized, by a variety of antenna combinations obtains electric thruster
The simulation of the radiation-emitting magnitude of operated under vacuum, and realize Electro Magnetic Compatibility assessment under whole star environment and more according to this condition
Point measurement of electromagnetic environment, forms the satellite electromagnetic compatibility judgment criterion lighted a fire under electromagnetic radiation environment for electric propulsion, to defend
Star provides test interpretation foundation with electric thruster electromagnetic compatibility；Then, the present invention provides assessment electric propulsion to satellite other
The anti-interference threshold value of subsystem compatibility test, present invention provide that threshold value under may determine that the satellite other equipment course of work
Will not be worked by electric propulsion is influenced.
A kind of whole star Electro Magnetic Compatibility verification system based on electric propulsion radiation-emitting simulator of the present invention, solves electricity
The demand that propulsion system can only light a fire in vacuum environment cannot provide vacuum with existing satellite electromagnetic compatibility test environment
Contradiction between environment, the satellite for electric propulsion system is configured carries out the test of whole star Electro Magnetic Compatibility and assessment provides way
Diameter, system include：Acquisition module builds module, test and evaluation module, judgment module；
Acquisition module obtains the radiation-emitting parameter under electric thruster fired state；
It builds module and electric propulsion radiation-emitting simulator is built according to the radiation-emitting parameter of step (1), make electric propulsion spoke
Penetrate launching simulator have configuration electric propulsion system satellite operation full frequency band in simulation electric thruster fired state under radiate
The ability of transmitting；The present invention provides the radiation-emittings that 225MHz~31GHz range tests obtain electric thruster operated under vacuum
Magnitude realizes that the Electro Magnetic Compatibility under whole star environment is assessed in 10~70dB μ V/m ranges, and according to this condition.
Test and evaluation module are in whole star Electro Magnetic Compatibility laboratory to the electromagnetic compatibility of the satellite of configuration electric propulsion system
Property is tested and is assessed
Judgment module judges electric propulsion system is configured by the disturbed situation of the satellite of configuration electric propulsion system in detection process
The Electro Magnetic Compatibility of the satellite of system, the Electro Magnetic Compatibility of the complete satellite for being organized in pairs electric propulsion system are tested and are assessed.This
Invention provides satellite electromagnetic compatibility judgment criterion, and test interpretation foundation is provided for satellite and electric thruster electromagnetic compatibility.
The present invention provides assessment electric propulsion to the anti-interference threshold value of other subsystem compatibility tests of satellite, in the present invention
It may determine that the satellite other equipment course of work will not be influenced by electric propulsion work under defined threshold value.
The present invention has carried out whole star and has tested (Radiated emission in the front and rear Electromagnetic Launching of electric propulsion work
test:RE102), itself radiation interference strength range to satellite of electric thruster normal work, test frequency range covering are tested
1GHz~31GHz frequency ranges, by above-mentioned three phases test confirmed electric propulsion working electromagnet radiation interference magnitude 10~
60dB μ V/m ranges, the electromagnetic radiation effect of the electric propulsion course of work do not interfere with whole star communication payload L frequency ranges, C frequency ranges,
The normal work of Ku frequency ranges and Ka frequency ranges.
Claims (10)
1. a kind of whole star Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator, it is characterised in that step is such as
Under：
(1) the radiation-emitting parameter under electric thruster fired state is obtained；
(2) electric propulsion radiation-emitting simulator is built according to the radiation-emitting parameter of step (1), simulates electric propulsion radiation-emitting
Device has the ability of the radiation-emitting under simulation electric thruster fired state in the satellite operation full frequency band of configuration electric propulsion system；
(3) Electro Magnetic Compatibility that the satellite of electric propulsion system is configured is tested and is assessed in whole star Electro Magnetic Compatibility laboratory
(4) by the disturbed situation for the satellite that electric propulsion system is configured in detection process, judge the satellite of electric propulsion system is configured
Electro Magnetic Compatibility, the Electro Magnetic Compatibility of the complete satellite for being organized in pairs electric propulsion system tested and assessed.
2. a kind of whole star Electro Magnetic Compatibility authentication based on electric propulsion radiation-emitting simulator according to claim 1
Method, it is characterised in that：Step (1) obtains the radiation-emitting parameter under electric thruster fired state, and step is as follows：
(1) electric thruster is placed in wave transparent cabin, to being vacuumized in wave transparent cabin,
(2) electric thruster is lighted a fire under vacuum conditions,
(3) thruster electromagnetic property test is implemented in shielded anechoic chamber, ensures external environment to result of the test interference effect in this way
Reduce, a reception antenna is placed in wave transparent out of my cabin, is directed at the back side of electric thruster, another reception antenna is placed in wave transparent cabin
Outside, it is directed toward perpendicular to the side of electric thruster；
(4) the radiation-emitting parameter of electric thruster received respectively using measuring instrument two reception antennas of measurement, test are obtained
Radiation-emitting magnitude.
3. a kind of whole star Electro Magnetic Compatibility authentication based on electric propulsion radiation-emitting simulator according to claim 1
Method, it is characterised in that：Step (2) builds electric propulsion radiation-emitting simulator according to the radiation-emitting parameter of step (1), pushes away electricity
Have in the satellite operation full frequency band of configuration electric propulsion system under simulation electric thruster fired state into radiation-emitting simulator
The ability of radiation-emitting, step are as follows：
(1) electromagnetic interference receiver detects and controls the electric thruster radiation-emitting parameter of equipment acquisition according to ground, to putting in advance
Device provides the input of frequency and field strength；
(2) preamplifier externally emits electromagnetic wave according to frequency and field strength using antenna, that is, simulates spoke under electric thruster fired state
Penetrate the ability of transmitting.
4. a kind of whole star Electro Magnetic Compatibility authentication based on electric propulsion radiation-emitting simulator according to claim 1
Method, it is characterised in that：Step (3) is in whole star Electro Magnetic Compatibility laboratory to the Electro Magnetic Compatibility of the satellite of configuration electric propulsion system
It is tested and is assessed, step is as follows：
(1) satellite that electric propulsion system is configured is placed in whole star Electro Magnetic Compatibility laboratory, Satellite Simulation is in-orbit in normal
Working condition；
(2) radiation-emitting parameter ranges of the electric propulsion radiation-emitting simulator according to electric thruster are used in satellite horizontal direction,
Inject the Radiative EMI magnitude of 2 times of radiation-emitting parameter maximum values；
(3) field strength is set up at a distance into certain distance in the satellite of whole star Electro Magnetic Compatibility experiment indoor distances configuration electric propulsion system
Probe, measures and confirms the field strength applied in setting frequency range；
(4) whole star Electro Magnetic Compatibility is detected by antenna and tests indoor radiation-emitting characteristic, pass through collection analysis electromagnetic wave field
The disturbed magnitude of satellite is confirmed with the variation of frequency by force.
5. a kind of whole star Electro Magnetic Compatibility authentication based on electric propulsion radiation-emitting simulator according to claim 1
Method, it is characterised in that：Step (4) judges configuration electricity by the disturbed situation of the satellite of configuration electric propulsion system in detection process
The Electro Magnetic Compatibility of the satellite of propulsion system, the Electro Magnetic Compatibility of the complete satellite for being organized in pairs electric propulsion system are tested and are commented
Estimate, step is as follows：
Interference field strength threshold value is set in frequency band of detection, when the radio field intensity of step (3) antenna detection is higher than the interference set
During field strength threshold value, the Electro Magnetic Compatibility of the satellite of judgement configuration electric propulsion system is unqualified；Otherwise, it is determined that configuration electric propulsion system
Satellite Electro Magnetic Compatibility it is qualified.
6. a kind of whole star Electro Magnetic Compatibility authentication based on electric propulsion radiation-emitting simulator according to claim 1
Method, it is characterised in that：Electric propulsion radiation-emitting simulator externally export electromagnetic wave frequency and field strength with electric propulsion light a fire shape
Radiation-emitting parameter under state is consistent, and the field strength parameter of frequency is obtained by the radiation emission test result of electric propulsion, and
It need to be tested under vacuum firing environment.
7. a kind of whole star Electro Magnetic Compatibility authentication based on electric propulsion radiation-emitting simulator according to claim 1
Method, it is characterised in that：When the test of satellite radiosensitivity is carried out, field intensity probe is being set up at a distance apart from electric propulsion 1m,
When satellite RF frequency acceptance band is observing and controlling frequency acceptance band, interference field strength threshold value is set to be not lower than 2V/m in the test frequency range；
When the satellite RF frequency acceptance band being related to that communicates is communication band, set interference field strength threshold value should not be low in the test frequency range
In 4V/m；Field intensity probe is located at quick position, and whole star power-up procedures maximum field strength threshold value is not lower than 3V/m.
8. a kind of whole star Electro Magnetic Compatibility authentication based on electric propulsion radiation-emitting simulator according to claim 1
Method, it is characterised in that：Measurand is that the satellite of electric propulsion system is configured, including：Electric thruster and its power supply, air supply system；
Electric thruster is located at outside the deck board of satellite；Whole star Electro Magnetic Compatibility laboratory, is non-closed environment, has shielding external electromagnetic and does
The ability disturbed, the electromagnetic compatibility test of satellite is normal temperature and pressure conditions.
9. a kind of whole star Electro Magnetic Compatibility authentication based on electric propulsion radiation-emitting simulator according to claim 1
Method, it is characterised in that：Electric propulsion radiation-emitting simulator, including：Electromagnetic interference receiver, multiple preamplifiers, mutiple antennas；Also
Including wave filter；
Ground detection and control device obtain the radiation-emitting parameter of point thruster；
Electromagnetic interference receiver according to ground detect and control equipment acquisition radiation-emitting parameter, to preamplifier provide frequency and
The input of field strength, preamplifier externally emit electromagnetic wave according to frequency and field strength using antenna.
10. a kind of whole star Electro Magnetic Compatibility verification system based on electric propulsion radiation-emitting simulator, it is characterised in that including：It obtains
Modulus block builds module, test and evaluation module, judgment module；
Acquisition module obtains the radiation-emitting parameter under electric thruster fired state；
It builds module and electric propulsion radiation-emitting simulator is built according to the radiation-emitting parameter of step (1), make electric propulsion radiation hair
Penetrate simulator have configuration electric propulsion system satellite operation full frequency band in simulation electric thruster fired state under radiation-emitting
Ability；
Test and evaluation module whole star Electro Magnetic Compatibility laboratory to be configured electric propulsion system satellite Electro Magnetic Compatibility into
Row test and assessment
Judgment module judges electric propulsion system is configured by the disturbed situation of the satellite of configuration electric propulsion system in detection process
The Electro Magnetic Compatibility of satellite, the Electro Magnetic Compatibility of the complete satellite for being organized in pairs electric propulsion system are tested and are assessed.
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| CN108287275A (en) * | 2017-12-28 | 2018-07-17 | 中国空间技术研究院 | A kind of electric thruster electromagnetic property test method and system based on wave transparent pair cabin and shielded anechoic chamber |
| CN108846230A (en) * | 2018-06-28 | 2018-11-20 | 天津航天机电设备研究所 | A kind of satellite is not intended to electromagnetic radiation impact evaluation method |
| CN109131939A (en) * | 2018-07-20 | 2019-01-04 | 中国空间技术研究院 | A kind of satellite equipment layout method and system based on electromagnetic radiation environment |
| CN109164325A (en) * | 2018-09-26 | 2019-01-08 | 上海微小卫星工程中心 | A kind of volume production satellite electromagnetic compatibility rapid detection method |
| CN111338230A (en) * | 2019-10-09 | 2020-06-26 | 中国舰船研究设计中心 | Method for determining forced power failure magnetic sensitivity threshold of speed boat |
| CN111965435A (en) * | 2020-08-18 | 2020-11-20 | 北京环境特性研究所 | High-speed plasma sheath spectrum modulation characteristic measuring device |
| CN112394245A (en) * | 2020-09-29 | 2021-02-23 | 北京空间飞行器总体设计部 | Method for analyzing electromagnetic compatibility of satellite system with large-size multi-wave-position SAR (synthetic Aperture Radar) antenna |
| CN112415280A (en) * | 2020-11-26 | 2021-02-26 | 上海卫星装备研究所 | Spacecraft radiation emission test system and method based on electric wave reverberation chamber |
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| CN109131939A (en) * | 2018-07-20 | 2019-01-04 | 中国空间技术研究院 | A kind of satellite equipment layout method and system based on electromagnetic radiation environment |
| CN109164325A (en) * | 2018-09-26 | 2019-01-08 | 上海微小卫星工程中心 | A kind of volume production satellite electromagnetic compatibility rapid detection method |
| CN111338230A (en) * | 2019-10-09 | 2020-06-26 | 中国舰船研究设计中心 | Method for determining forced power failure magnetic sensitivity threshold of speed boat |
| CN111338230B (en) * | 2019-10-09 | 2023-02-28 | 中国舰船研究设计中心 | Method for determining forced power failure magnetic sensitivity threshold of speed boat |
| CN111965435A (en) * | 2020-08-18 | 2020-11-20 | 北京环境特性研究所 | High-speed plasma sheath spectrum modulation characteristic measuring device |
| CN112394245A (en) * | 2020-09-29 | 2021-02-23 | 北京空间飞行器总体设计部 | Method for analyzing electromagnetic compatibility of satellite system with large-size multi-wave-position SAR (synthetic Aperture Radar) antenna |
| CN112394245B (en) * | 2020-09-29 | 2023-08-15 | 北京空间飞行器总体设计部 | Electromagnetic compatibility analysis method for satellite system with large-size multi-wave-level SAR antenna |
| CN112415280B (en) * | 2020-11-26 | 2022-08-12 | 上海卫星装备研究所 | Spacecraft radiation emission test system and method based on electric wave reverberation chamber |
| CN112415280A (en) * | 2020-11-26 | 2021-02-26 | 上海卫星装备研究所 | Spacecraft radiation emission test system and method based on electric wave reverberation chamber |
| CN113408106A (en) * | 2021-05-27 | 2021-09-17 | 北京国电高科科技有限公司 | Ender-sky constellation communication load EMC analysis model and EMC characteristic improvement method |
| CN114325173A (en) * | 2021-12-07 | 2022-04-12 | 中国空间技术研究院 | Universal testing device and method for spacecraft system-level electromagnetic radiation emission |
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