CN112462169A - System and method for testing shielding effectiveness of whole airplane - Google Patents
System and method for testing shielding effectiveness of whole airplane Download PDFInfo
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- CN112462169A CN112462169A CN202011226790.7A CN202011226790A CN112462169A CN 112462169 A CN112462169 A CN 112462169A CN 202011226790 A CN202011226790 A CN 202011226790A CN 112462169 A CN112462169 A CN 112462169A
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- 238000010168 coupling process Methods 0.000 claims abstract description 16
- 238000005859 coupling reaction Methods 0.000 claims abstract description 16
- 230000000694 effects Effects 0.000 claims description 8
- 230000005855 radiation Effects 0.000 description 11
- 230000004044 response Effects 0.000 description 9
- 238000010998 test method Methods 0.000 description 6
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- 238000012937 correction Methods 0.000 description 2
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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
- G01R31/001—Measuring interference from external sources to, or emission from, the device under test, e.g. EMC, EMI, EMP or ESD testing
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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
- G01R31/005—Testing of electric installations on transport means
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Abstract
The application provides a system and a method for testing the overall shielding effectiveness of an airplane, wherein the method is applied to the system for testing the overall shielding effectiveness of the airplane as claimed in claim 1, and comprises the following steps: the synthetic plane wave antenna array 1 generates a plane wave environment covering the whole airplane according to preset transmitting power; testing the coupling signal on the cable 2 by using the current probe 3; the current probe 3 sends the coupling signal to the test equipment 4; the test equipment 4 calculates the shielding effectiveness value of the airplane according to the receiving power and the transmitting power of the coupling signal.
Description
Technical Field
The invention belongs to the field of electromagnetic compatibility testing and evaluation, and particularly relates to a system and a method for testing the whole shielding effectiveness of an airplane.
Background
In the current national military standard, the methods for testing the shielding effectiveness are as follows: GB/T12190-2006 method for measuring the shielding effectiveness of electromagnetic shielding chambers; GJB 3039-1997 test methods for the requirements and shielding effectiveness of shielding cabins of ships; GJB 5185-2003 method for measuring shielding effectiveness of small shields; GJB 5240-2004 military electronic equipment Universal Cabinet Shielding effectiveness requirements and test methods; GJB 5362-2005 missile Shell Shielding effectiveness measurement method; GJB 6190-; GJB 6785-2009 military electronic equipment shelter shielding effectiveness test method.
In the existing standard for guiding the shielding effectiveness test, the test of local shielding effectiveness is mainly used, the test method is carried out around a door, a window or a regular shielding material with regular shape, and the selection of test points is also distributed around the current test part. The shielding effectiveness test is carried out aiming at a certain part of a shielding body strictly, and errors caused by factors such as hole seam leakage outside the tested part and reflection caused by large equipment cabinet distribution in a cabin cannot be corrected. Meanwhile, the shielding effectiveness test method produces the following results: the local performance is used to replace the overall performance, and the shielding effectiveness data measured at different positions of the whole aircraft platform mostly have different differences. Considering the shielding effectiveness of the aircraft on the premise of the above problem becomes an open problem.
In addition, the inquiry of the condition of the currently published patent shows that the Chinese patent publication number: CN102955091B, published 2015, 10, 21, the name of the invention is a method for testing and evaluating the low-frequency shielding effectiveness of a shielding shelter under the condition of the whole shelter, the application belongs to the technical field of testing the shielding effectiveness of the shielding shelter, and discloses a method for testing and evaluating the low-frequency shielding effectiveness of the shielding shelter under the condition of the whole shelter. The method has the disadvantages that the situation that local shielding effectiveness is used to replace the whole shielding effectiveness cannot be avoided; secondly, the device is only suitable for the shielding effectiveness test of low frequency band; thirdly, the method is only suitable for the standard shielding square cabin; fourthly, the receiving antenna is used for testing the shelter in which the irregular cabinet is placed, and the influence caused by reflection cannot be avoided; the possibility of great difference of test results of different parts still cannot be avoided.
Disclosure of Invention
The invention fills the blank that the concept of integral shielding effectiveness is not available at present. The method solves the defect that the shielding efficiency of the whole machine is replaced by the local shielding efficiency in the existing testing method, and eliminates the influence on the testing result under the condition that the irregular shielding cabin and the irregular cabinet are distributed in the cabin. The method for testing and evaluating the shielding effectiveness of the whole airplane mainly adopts an alternative method.
In a first aspect, the present application provides an aircraft complete shielding effectiveness testing system, which includes a synthetic plane wave antenna array 1, a cable 2, a current probe 3, and a testing device 4, wherein:
the synthetic plane wave antenna array 1 is an antenna array covering the plane wave environment of the whole airplane; the cable 2 is a receiving device of the test system, and the cable 2 is arranged in a cabin of the airplane; the other end of the current probe 3 is connected with the cable 2, and the other end of the current probe 3 is connected with the test equipment 4.
Specifically, the transmission power of the synthesized plane wave antenna array 1 is greater than a preset power value.
Specifically, the length of the cable 2 needs to be set according to the wavelength corresponding to the test frequency.
In a second aspect, the present application provides an aircraft complete shielding effectiveness testing method, which is applied to the aircraft complete shielding effectiveness testing system according to claim 1, and the method includes:
the synthetic plane wave antenna array 1 generates a plane wave environment covering the whole airplane according to preset transmitting power;
testing the coupling signal on the cable 2 by using the current probe 3;
the current probe 3 sends the coupling signal to the test equipment 4;
the test equipment 4 calculates the shielding effectiveness value of the airplane according to the receiving power and the transmitting power of the coupling signal.
Specifically, the preset transmitting power is set according to the requirement of the working frequency band of the airplane.
Specifically, the method further comprises:
and if the shielding effect value is smaller than the preset shielding effect value, judging that the equipment in the aircraft cabin cannot normally work under the preset external electromagnetic environment.
Specifically, the method further comprises:
and if the shielding effect value is greater than or equal to a preset shielding effect value, judging that the equipment in the aircraft cabin can normally work under a preset external electromagnetic environment.
Specifically, the testing of the coupled signal on the cable 2 by the current probe 3 specifically includes:
and testing the coupling signals on the cable 2 by using the current probe 3 corresponding to the working frequency band on different working frequency bands.
In summary, the invention provides a method for testing and evaluating shielding effectiveness of a complete machine of an airplane. Firstly, the blank that no concept of the whole shielding effectiveness exists at present is filled, and the checking requirement of the whole shielding effectiveness of the airplane is met; secondly, a method for testing the shielding effectiveness of local departments, windows and gaps in the existing standard is distinguished from the shielding effectiveness of the whole machine, and the fact that the shielding effectiveness of the local shielding effectiveness instead of the shielding effectiveness of the whole machine is a miszone is clear; thirdly, a shielding effectiveness testing and assessment reference method of the irregular shielding body is provided, and the defect that a testing method is single due to the fact that the shielding body with a regular shape is mainly used as an assessment object in a relevant standard is overcome; finally, a new idea of an alternative method for testing shielding effectiveness is provided, which provides a new choice based on the traditional transmitting antenna/receiving antenna test system.
Drawings
Fig. 1 is a schematic system architecture diagram of an aircraft complete shielding effectiveness testing system provided in the present application;
wherein: 1-synthetic plane wave antenna array, 2-cable, 3-current probe, 4-test equipment.
Detailed Description
The invention discloses a method for testing and evaluating the shielding effectiveness of a complete machine of an airplane. The invention belongs to the field of electromagnetic compatibility testing, and discloses an application method with strong pertinence based on the particularity of an airplane platform. The invention provides a concept of the shielding effectiveness of the whole machine, and distinguishes the difference between the local shielding effectiveness test and the whole machine shielding effectiveness test in the existing standard; unifying the evaluation method of the shielding effectiveness test results of different test parts of the same platform; meanwhile, a shielding effectiveness substitution test and evaluation method is provided for the conditions that a large number of irregular metal bodies exist in the engine room, the space is narrow and the like.
Example one
The invention relates to a method for testing and evaluating the shielding effectiveness of an airplane complete machine, which comprises the following steps of firstly, generating corresponding plane wave testing environments by frequency division aiming at the defects that the shielding effectiveness of each local position of an airplane platform has larger difference and cannot replace the shielding effectiveness of the complete machine, and covering the whole airplane platform; secondly, aiming at the current situation that a large number of metal cabinets need to be arranged in the aircraft cabin, the influence of the reflection of the cabinets and the superposition of electromagnetic waves on the test result is eliminated by using a cable coupling substitution method.
In order to solve the technical problem, the test section of the present invention includes the following two aspects:
1. a plane wave environment is generated that covers the entire aircraft platform. The situation that local shielding effectiveness replaces whole machine shielding effectiveness is avoided, and a proper platform is provided for whole machine testing. The synthetic plane wave method is used to generate virtual plane wave and belongs to the field of synthetic aperture method to generate plane wave. The principle of the radiation device is that radiation is respectively carried out on each radiation position in the caliber through a radiation unit, and the fields in the space are sequentially subjected to vector superposition. For a linear system, the common response of the parts of the system is equal to the sum of the individual responses of the parts. One is a field generated by the aperture array in space, the fields generated by the radiation units of the apertures are vector superposed in space, and the synthesized plane wave is a plane wave formed by superposing the fields radiated by the single radiation unit at different positions in space;
2. the method of cable coupling/current probe testing is used instead of antenna for reception. Theoretically, the shielding effectiveness of the whole airplane should be a fixed and uniform data. Even if the shielding performance varies from location to location due to differences in manufacturing processes and materials used, the presence of the external electromagnetic environment should have a consistent, comprehensive impact on the overall space within the cabin and on the equipment/personnel within the cabin. Therefore, the traditional shielding effectiveness testing method cannot provide a scientific conclusion which can reproduce theoretical analysis. And the coupling signal test is carried out by using the cable penetrating through the whole test space, so that on one hand, the measurement error caused by the size that the test antenna cannot be accommodated in the test space in the cabin can be avoided, on the other hand, the influence of the local electromagnetic environment difference formed by the superposition of electromagnetic waves caused by the reflection of the cabinet on the test result can be reduced as much as possible, and finally, the condition that the shielding effectiveness test result of each local test position has more difference is also avoided.
Specifically, the test principle is shown in fig. 1. The composite plane wave antenna array 1 is an antenna array. In actual measurement, a probe can be used to respectively emit fields e θ and γ at the positions of each unit of the array, the response of the antenna to be tested to the probe when the probe emits at each position is recorded, and then the responses at each position are weighted w θ and γ to be vector-superposed to obtain the response of the tested part under the irradiation of the quasi-plane wave. The cable 2 is used as a receiving device instead of an antenna, because its test path traverses the whole test space, and the electromagnetic waves of each local space are coupled to the cable and enter the test equipment 4 through the current probe 3. Because the cable coupling efficiency is low, the transmission power of the synthesized plane wave antenna array 1 is required to be large enough, and meanwhile, the cable length is required to be tested accurately according to the wavelength change corresponding to the test frequency.
When the shielding effectiveness of the whole airplane is evaluated, the requirements of the work function of the airplane and the sensitivities of different devices are mainly considered. Considering that the test result is affected by the difference of the arrangement positions of the cables 2, the positions of the test cables need to be arranged reasonably. Therefore, the scheme provided by the invention takes the key equipment cabinet as a key assessment part, the trend of the cable is mainly arranged through the key assessment part, one to three test positions are selected for multiple tests according to needs, and finally the most severe test result is taken as the evaluation standard of the shielding effectiveness of the whole machine.
Example two
The invention is described in further detail below with reference to the following detailed description and accompanying drawings:
the composite plane wave antenna array 1 of fig. 1 is a method of providing a test environment in which the shielding effectiveness test can reduce most of the work for calculation and correction. From W1 θ, γ to Wn θ, γ, the antenna array used to synthesize the plane wave is selected differently according to the different test frequency bands. The working principle is that radiation is respectively carried out at each radiation position in the caliber by one radiation unit, and the fields in the space are sequentially subjected to vector superposition. One is the field generated by the aperture array in the space, the vector superposition of the fields generated by the radiation units in the space, and the synthesized plane wave is the field radiated by the single radiation unit at different positions and is superposed in the space to form the plane wave. During actual measurement, a probe can be used for respectively emitting fields e theta and gamma at the positions of each unit of the array, the response of the antenna to be tested to the probe when the probe emits at each position is recorded, and then the weighted w theta and gamma vector superposition is carried out on the response of each position to obtain the response of the tested part under the irradiation of the quasi-plane wave.
The cable 2 and the current probe 3 in fig. 1 are used as a receiving device for replacing an antenna and are main components used in a shielding effectiveness replacing method. The working principle of the cable is to transmit signals to a receiving device through a current probe by coupling electromagnetic waves in space. The length of the test cable can be controlled according to different test frequency bands, so that the test cable can generate strong response to the frequency band signals. Meanwhile, the cable can span the whole test part, the comprehensive change of the electromagnetic environment of the whole machine can be reflected through the test data, and the local electromagnetic environment difference formed by the superposition of electromagnetic waves due to the reflection of metal cabinets distributed in the cabin is avoided. The current probe also needs to be selected and replaced according to the change of the test frequency band and the matching with the test cable.
Considering different positions in the cabin and different sensitivities of related equipment for completing work functions, the key equipment cabinets in each cabin are taken as key assessment positions according to requirements, the trend of the cables is arranged to mainly pass through the areas, one to three test positions are selected for multiple tests, and finally the most severe test result is taken as an evaluation standard of the shielding effectiveness of the whole machine, so that the requirements of the sensitive equipment on the work environment are ensured.
The test equipment 4 in fig. 1 is a data receiving and processing component in the aircraft complete machine shielding effectiveness test system. Generally, a frequency spectrum receiver or a receiver is used, corresponding conversion and correction are completed through test software after test data are collected, and a final result is given and used as shielding effectiveness data of the whole airplane.
Claims (8)
1. The aircraft complete machine shielding effectiveness testing system is characterized by comprising a synthetic plane wave antenna array (1), a cable (2), a current probe (3) and testing equipment (4), wherein:
the synthetic plane wave antenna array (1) is an antenna array covering the plane wave environment of the whole airplane; the cable (2) is a receiving device of the test system, and the cable (2) is arranged in a cabin of the airplane; the other end of the current probe (3) is connected with the cable (2), and the other end of the current probe (3) is connected with the test equipment (4).
2. The system according to claim 1, characterized in that the transmit power of the synthetic plane wave antenna array (1) is larger than a preset power value.
3. A system according to claim 1, characterized in that the length of the cable (2) is set according to the wavelength corresponding to the test frequency.
4. The aircraft complete shielding effectiveness testing method is applied to the aircraft complete shielding effectiveness testing system of claim 1, and comprises the following steps:
the synthetic plane wave antenna array (1) generates a plane wave environment covering the whole airplane according to preset transmitting power;
testing the coupling signal on the cable (2) by using a current probe (3);
the current probe (3) sends the coupling signal to the test equipment (4);
the test equipment (4) calculates the shielding effectiveness value of the airplane according to the receiving power and the transmitting power of the coupling signal.
5. The method of claim 4, wherein the predetermined transmit power is set according to aircraft operating band requirements.
6. The method of claim 4, further comprising:
and if the shielding effect value is smaller than the preset shielding effect value, judging that the equipment in the aircraft cabin cannot normally work under the preset external electromagnetic environment.
7. The method of claim 4, further comprising:
and if the shielding effect value is greater than or equal to a preset shielding effect value, judging that the equipment in the aircraft cabin can normally work under a preset external electromagnetic environment.
8. The method according to claim 4, wherein the testing of the coupled signal at the cable (2) with the current probe (3) comprises:
and testing the coupling signals on the cable (2) by using the current probe (3) corresponding to the working frequency band on different working frequency bands.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202011226790.7A CN112462169A (en) | 2020-11-05 | 2020-11-05 | System and method for testing shielding effectiveness of whole airplane |
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| CN202011226790.7A CN112462169A (en) | 2020-11-05 | 2020-11-05 | System and method for testing shielding effectiveness of whole airplane |
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Cited By (2)
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| CN116390468A (en) * | 2023-05-15 | 2023-07-04 | 北京航天天美科技有限公司 | Optimization method for electromagnetic shielding performance of military shelter |
| CN117347734A (en) * | 2023-10-08 | 2024-01-05 | 东南大学 | Method for selecting position of special-shaped shielding shell shielding effectiveness test antenna |
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