CN114167148A - System for simulating X-ray irradiation satellite to generate electromagnetic field - Google Patents
System for simulating X-ray irradiation satellite to generate electromagnetic field Download PDFInfo
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- CN114167148A CN114167148A CN202111469452.0A CN202111469452A CN114167148A CN 114167148 A CN114167148 A CN 114167148A CN 202111469452 A CN202111469452 A CN 202111469452A CN 114167148 A CN114167148 A CN 114167148A
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- 230000005672 electromagnetic field Effects 0.000 title claims abstract description 25
- 230000005540 biological transmission Effects 0.000 claims abstract description 21
- 230000008878 coupling Effects 0.000 claims abstract description 7
- 238000010168 coupling process Methods 0.000 claims abstract description 7
- 238000005859 coupling reaction Methods 0.000 claims abstract description 7
- 238000002347 injection Methods 0.000 claims description 33
- 239000007924 injection Substances 0.000 claims description 33
- 230000009471 action Effects 0.000 claims description 2
- 230000001678 irradiating effect Effects 0.000 claims 2
- 238000012360 testing method Methods 0.000 abstract description 7
- 238000004891 communication Methods 0.000 abstract description 6
- 230000005284 excitation Effects 0.000 abstract description 3
- 230000002787 reinforcement Effects 0.000 abstract description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- 239000003990 capacitor Substances 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 230000005856 abnormality Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 230000009528 severe injury Effects 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
- G01R29/08—Measuring electromagnetic field characteristics
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- G—PHYSICS
- 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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- General Physics & Mathematics (AREA)
- Electromagnetism (AREA)
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Abstract
The invention discloses a system for simulating an electromagnetic field generated by an X-ray irradiation satellite, which comprises a large-current pulse source, a conical transmission line and a satellite solar sailboard, wherein the large-current pulse source is connected with the conical transmission line; the conical transmission line injects a pulse current signal output by the high-current pulse source into the satellite solar sailboard in a capacitive coupling mode. The invention aims to provide a system for simulating an electromagnetic field generated by an X-ray irradiation satellite, which simulates the electromagnetic field generated by the X-ray irradiation satellite in an electromagnetic excitation mode and provides a new test means for the reinforcement of anti-electromagnetic pulses of a power supply system, a communication system, an antenna orientation system and the like in the satellite.
Description
Technical Field
The invention relates to the technical field of satellite system electromagnetic pulse effect, in particular to a system for simulating an electromagnetic field generated by an X-ray irradiation satellite.
Background
The system electromagnetic pulse mainly occurs in the instantaneous nuclear radiation environment and the space environment, at the moment, X rays act on a satellite, electron emission is generated on the outer surface and the inner part, strong electromagnetic pulse is excited, and serious interference and damage are caused to electronic devices.
When the energy of X-rays is low, photons are difficult to penetrate through the aircraft shell, and at the moment, the photons mainly act with the outer wall of the system to emit electrons outwards and excite an electromagnetic field; when the energy of X-ray is higher, photons can enter the system through the transmission shell layer, and act with the inner surface of the system to emit electrons inwards and excite the electromagnetic field.
Since the current source for the system electromagnetic pulses can be generated anywhere within the system, the electronics and equipment are directly exposed to severe damage, and the system electromagnetic pulses can generate up to 10 on the satellite5Electric field intensity of V/m and 104The surface current of a/m is likely to cause abnormality in a power supply, a communication system, an antenna orientation system, and the like in a satellite.
In order to reinforce the power supply system, the communication system, the antenna orientation system and the like in the satellite against electromagnetic pulses, the electromagnetic field generated by the X-ray irradiation satellite needs to be simulated, and in the prior art, no good means is provided for simulating the process of generating the electromagnetic field by the X-ray irradiation satellite.
Disclosure of Invention
The invention aims to provide a system for simulating an electromagnetic field generated by an X-ray irradiation satellite, which simulates the electromagnetic field generated by the X-ray irradiation satellite in an electromagnetic excitation mode and provides a new test means for the reinforcement of anti-electromagnetic pulses of a power supply system, a communication system, an antenna orientation system and the like in the satellite.
The invention is realized by the following technical scheme:
a system for simulating an electromagnetic field generated by an X-ray irradiation satellite comprises a large-current pulse source, a conical transmission line and a satellite solar sailboard; the conical transmission line injects a pulse current signal output by the high-current pulse source into the satellite solar sailboard in a capacitive coupling mode.
Preferably, the tapered transmission line comprises an injection flat plate, an electrode flat plate and a plurality of connecting cables; one end of any one of the connection cables is connected with the injection flat plate, and the other end of the connection cable is connected with the electrode flat plate.
Preferably, one side of the connecting cable connected to the injection flat plate corresponds to the position of the main cable inlet of the satellite solar sailboard.
Preferably, the connection cables are provided in 4 pieces.
Preferably, the coupling injection capacitance value of the injection plate is set to 200 pF.
Preferably, the impedance of the tapered transmission line is set to 170 Ω.
Preferably, the high-current pulse generator further comprises a pulse forming network, and the current signal output by the high-current pulse source is shaped by the pulse forming network and then transmitted to the conical transmission line.
Preferably, when the voltage of the high-current pulse source is greater than or equal to 10kV, the resistance and the capacitance in the pulse forming network are set to 30 Ω and 100pF, respectively.
Preferably, when the voltage of the high current pulse source is less than 10kV, the resistance and capacitance in the pulse forming network are set to 1000 Ω and 100pF, respectively.
Preferably, the device further comprises a receiver for receiving the star injection current; the star body injection current is generated by the satellite solar sailboard under the action of the pulse current signal.
Compared with the prior art, the invention has the following advantages and beneficial effects:
the system simulates the electromagnetic field generated by the X-ray irradiation satellite in an electromagnetic excitation mode, and provides a new test means for reinforcing the electromagnetic pulse resistance of a power supply system, a communication system, an antenna orientation system and the like in the satellite.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principles of the invention. In the drawings:
FIG. 1 is a schematic diagram of the system of the present invention;
FIG. 2 is a schematic structural diagram of a tapered transmission line according to the present invention;
reference numbers and corresponding part names in the drawings:
1. a high current pulse source; 2. a satellite solar array; 3. injecting the flat plate; 4. an electrode plate; 5. connecting a cable; 6. a pulse forming network; 7. a receiver.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Example 1
The embodiment provides a system for simulating an electromagnetic field generated by an X-ray irradiation satellite, in the system, a satellite star body is assumed to be a good conductor, a ground plane is an ideal ground plane, and in the specific implementation, a copper net or a copper plate can be laid on the ground plane. Specifically, the system is shown in fig. 1 and comprises a high-current pulse source 1, a conical transmission line and a satellite solar sailboard 2;
the pulse current waveform output by the large-current pulse source 1 is injected into the satellite solar sailboard 2 in a capacitive coupling mode through a tapered transmission line (the tapered transmission line is used for realizing impedance matching between the large-current injection source and an injection capacitor).
Specifically, the tapered transmission line in the present embodiment is shown in fig. 2, and includes an injection plate 3, an electrode plate 4, and 4 connection cables 5; one end of each of the 4 connecting cables 5 is connected with the injection flat plate 3, and the other end of each of the connecting cables is connected with the electrode flat plate 4. Wherein, in order to guarantee the injection efficiency of the pulse current signal, namely: the pulse current signals are injected into the satellite solar sailboards 2 to the maximum extent, and the connecting cable 5 is connected to one side of the injection flat plate 3 and corresponds to the inlet position of the main cable of the satellite solar sailboards 2. The correspondence referred to in this embodiment means: in the implementation, the connection cable 5 connected to the injection flat plate 3 side is located right below the main cable inlet of the satellite solar sailboard 2.
It should be noted that the size and shape of the upper injection plate and the lower injection plate are not particularly limited, and they are designed according to the parameters of the satellite solar array 2, such as size/satellite ground height, etc., as long as the coupling injection capacitance value is set to 200 pF.
Further, in order to ensure the quality of the pulse current waveform and realize impedance matching between the large-current injection source and the injection capacitor, the impedance of the tapered transmission line in the embodiment is set to 170 Ω.
Further, in order to prevent the injection flat plate 3 from breaking down with the solar panel when the pulse current signal is injected into the satellite solar panel 2, the injection flat plate 3 in this embodiment is made of a stainless steel material with high conductivity and low magnetic conductivity, and the edge of the injection flat plate 3 is rounded.
Example 2
When the system is used in a specific simulation mode, various testing devices are connected in the system besides the satellite star, and in order to reduce the influence of the testing devices on the satellite star testing result, a current-limiting resistor needs to be connected in series between the large-current pulse source 1 and the injection flat plate. Therefore, the present embodiment is modified from embodiment 1 as follows:
a pulse forming network 6 is added between the high-current pulse source 1 and the conical transmission line to achieve the effects of limiting the output current and sharpening the leading edge of the current waveform. Specifically, when the voltage of the large-current pulse source 1 is greater than or equal to 10kV, the resistance and the capacitance in the pulse forming network 6 are set to 30 Ω and 100pF, respectively; when the voltage of the high current pulse source 1 is less than 10kV, the resistance and capacitance in the pulse forming network 6 are set to 1000 Ω and 100pF, respectively.
Further, the current output by the pulse forming network 6 is single-point output, and a plurality of main cable inlets are distributed on the satellite solar sailboard 2, so that the size of the electrode flat plate 4 can be set to be small, and the area of the injection flat plate 3 can be set to be large to ensure the injection efficiency of the pulse current signal, so that the pulse current signal on the electrode flat plate 4 is distributed and injected into the satellite solar sailboard 2.
Further, in order to obtain the electromagnetic wave signal obtained through simulation and facilitate subsequent improvement of a power supply system, a communication system and an antenna orientation system in the aircraft according to the electromagnetic wave signal, the satellite solar array antenna system further comprises a receiver 7, wherein the receiver 7 in the embodiment is set as an oscilloscope, and the oscilloscope is connected with a sensor in the satellite solar array panel 2 through a signal test cable and is used for receiving and displaying the star injection current generated by the satellite solar array panel 2 under the pulse current signal.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are merely exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (10)
1. A system for simulating an electromagnetic field generated by an X-ray irradiation satellite is characterized by comprising a large-current pulse source (1), a conical transmission line and a satellite solar sailboard (2); the conical transmission line injects a pulse current signal output by the high-current pulse source (1) into the satellite solar sailboard (2) in a capacitive coupling mode.
2. The system for simulating the generation of electromagnetic fields by X-ray irradiation of satellites according to claim 1, wherein the tapered transmission line comprises an injection plate (3), an electrode plate (4) and a plurality of connecting cables (5); one end of any one connecting cable (5) is connected with the injection flat plate (3), and the other end of the connecting cable is connected with the electrode flat plate (4).
3. The system for simulating the generation of electromagnetic fields by X-ray irradiation satellites as claimed in claim 2, wherein the connecting cable (5) is connected to the injection flat plate (3) at a side corresponding to the position of the main cable entrance of the satellite solar sailboard (2).
4. A system for simulating electromagnetic fields generated by X-ray irradiation of satellites as claimed in claim 2 wherein, said connecting cables (5) are provided in 4 pieces.
5. A system for simulating the generation of electromagnetic fields for irradiating satellites with X-rays according to claim 2, characterized in that the coupling injection capacitance value of the injection plate (3) is set to 200 pF.
6. The system for simulating the generation of electromagnetic fields by X-ray irradiation of satellites as claimed in claim 1, wherein the impedance of the tapered transmission line is set to 170 Ω.
7. A system for simulating electromagnetic field generation by X-ray irradiation satellite according to any one of claims 1 to 6, further comprising a pulse forming network (6), wherein the current signal outputted by the high current pulse source (1) is shaped by the pulse forming network (6) and then transmitted to the tapered transmission line.
8. A system for simulating the generation of an electromagnetic field by an X-ray irradiated satellite according to claim 7, characterized in that when the voltage of the high current pulse source (1) is greater than or equal to 10kV, the resistance and capacitance in the pulse forming network (6) are set to 30 Ω and 100pF, respectively.
9. A system for simulating the generation of an electromagnetic field by an X-ray irradiated satellite according to claim 7, characterized in that when the voltage of the high current pulse source (1) is less than 10kV, the resistance and capacitance in the pulse forming network (6) are set to 1000 Ω and 100pF, respectively.
10. A system for simulating the generation of electromagnetic fields for irradiating satellites with X-rays according to claim 1, further comprising a receiver (7), wherein the receiver (7) is used for receiving the satellite injection current; the star body injection current is generated by the satellite solar sailboard (2) under the action of the pulse current signal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111469452.0A CN114167148A (en) | 2021-12-03 | 2021-12-03 | System for simulating X-ray irradiation satellite to generate electromagnetic field |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111469452.0A CN114167148A (en) | 2021-12-03 | 2021-12-03 | System for simulating X-ray irradiation satellite to generate electromagnetic field |
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| CN114167148A true CN114167148A (en) | 2022-03-11 |
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Citations (8)
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|---|---|---|---|---|
| CN102183696A (en) * | 2011-03-03 | 2011-09-14 | 中国航空无线电电子研究所 | Surface current injection technology substituted for electromagnetic compatibility radiation test |
| CN102426310A (en) * | 2011-10-09 | 2012-04-25 | 中国航空无线电电子研究所 | Novel full aircraft high-strength irradiation test method |
| CN105044494A (en) * | 2015-06-29 | 2015-11-11 | 中国航空无线电电子研究所 | Surface current injection measurement method used for electromagnetic compatibility test |
| CN106569074A (en) * | 2016-11-15 | 2017-04-19 | 中国人民解放军军械工程学院 | Coupling device-based conduction sensitivity test method and system |
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| CN113030591A (en) * | 2021-02-24 | 2021-06-25 | 中国人民解放军陆军工程大学 | Non-shielding multi-core cable coupling channel large-current injection equivalent test method |
-
2021
- 2021-12-03 CN CN202111469452.0A patent/CN114167148A/en active Pending
Patent Citations (8)
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|---|---|---|---|---|
| CN102183696A (en) * | 2011-03-03 | 2011-09-14 | 中国航空无线电电子研究所 | Surface current injection technology substituted for electromagnetic compatibility radiation test |
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| CN105044494A (en) * | 2015-06-29 | 2015-11-11 | 中国航空无线电电子研究所 | Surface current injection measurement method used for electromagnetic compatibility test |
| CN106569074A (en) * | 2016-11-15 | 2017-04-19 | 中国人民解放军军械工程学院 | Coupling device-based conduction sensitivity test method and system |
| CN107727942A (en) * | 2017-09-13 | 2018-02-23 | 北京空间飞行器总体设计部 | A kind of satellite electric propulsion system electromagnetic radiation characteristic simulator |
| CN112345836A (en) * | 2020-11-03 | 2021-02-09 | 中国人民解放军陆军工程大学 | Multi-core cable large-current injection equivalent strong field radiation effect test method and system |
| CN113030590A (en) * | 2021-02-24 | 2021-06-25 | 中国人民解放军陆军工程大学 | Large-current injection equivalent substitution irradiation test method for shielded wire coupling channel |
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Application publication date: 20220311 |