CN109670234B - Deployment method of airborne electromagnetic environment test probe - Google Patents
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Abstract
The invention belongs to the field of airborne electromagnetic environment monitoring, and provides a deployment method of an airborne electromagnetic environment test probe, which is used for making a basis for the diagnosis and analysis of subsequent electromagnetic environment data and comprises the following steps: step 1, modeling an airplane body, airborne equipment and an internal cable to obtain electromagnetic environment parameters of different positions on the airplane under the action of an onboard radiation source; step 2, comprehensively predicting the electromagnetic environment of key parts in the machine, screening electromagnetic vulnerable points, and deploying test probes for the electromagnetic vulnerable points; and 3, calibrating the test probe, and verifying the reliability of the test probe in an airborne environment considering various temperature stresses.
Description
Technical Field
The invention belongs to the field of airborne electromagnetic environment monitoring, and relates to a method for deploying an airborne electromagnetic environment test probe in a machine.
Background
The deployment of the airborne electromagnetic environment test probe is characterized in that after modeling is carried out on an airplane body, airborne equipment and an internal cable, electromagnetic vulnerable points are evaluated and screened, positions, frequency bands and probe types needing to be monitored are determined to be selected, and various electromagnetic environment test probes are installed in the airplane. Under general conditions, the installation of airborne electronic and electrical equipment is more concentrated, and if the test probe installation position is selected improperly, the test probe can be influenced by the electromagnetic environment, so that the test precision is reduced, and the index cannot be met. The establishment of related deployment strategies requires comprehensive consideration of various factors such as installation position, space, probe shape, material, data transmission media and the like, and has great technical difficulty.
With the increasing emphasis of all parties on electromagnetic environment problems, aircraft electromagnetic environment testing and analyzing technologies are also subject to rapid development, and research units in China also carry out deeper research, but most of the research is laboratory testing or object testing in a simple scene, and specific research and actual operation are not carried out on real-time measurement of electromagnetic environment under a flight condition, which means that an electromagnetic environment testing probe is not installed in an aircraft, and research on a deployment method of an airborne electromagnetic environment testing probe is not reported in China, and lacks of technical accumulation and engineering experience in related fields.
Disclosure of Invention
The purpose of the invention is as follows: the deployment method of the airborne electromagnetic environment test probe is provided, and the basis is made for the diagnosis and analysis of subsequent electromagnetic environment data.
The technical scheme of the invention is as follows:
a deployment method of an airborne electromagnetic environment test probe comprises the following steps:
step 1, modeling an airplane body, airborne equipment and an internal cable to obtain electromagnetic environment parameters of different positions on the airplane under the action of an onboard radiation source;
step 2, comprehensively predicting the electromagnetic environment of key parts in the machine, screening electromagnetic vulnerable points, and deploying test probes for the electromagnetic vulnerable points;
and 3, calibrating the test probe, and verifying the reliability of the test probe in an airborne environment considering various temperature stresses.
The modeling of the step 1 is divided into: fuselage modeling, airborne equipment modeling and aircraft internal cable modeling;
(1) Aircraft fuselage modeling
Carrying out fuselage modeling aiming at the selected airplane type, converting an airplane geometric model into an electromagnetic model, and dividing the electromagnetic model into model building import, model correction, material information import and grid division;
(2) Airborne equipment modeling
Performing electromagnetic characteristic modeling aiming at selected onboard typical equipment and systems, wherein the electromagnetic characteristic modeling comprises frequency equipment emission modeling, disturbance equipment emission modeling, sensitive equipment cabinet modeling and sensitive equipment board level equipment modeling;
(3) Aircraft interior cable modeling
And performing electromagnetic characteristic modeling on the selected cable in the airplane, and decomposing the electromagnetic characteristic modeling into cable topology layout definition, cable bundle type definition, cable electromagnetic attribute definition and electromagnetic characteristic parameter extraction.
(1) In the modeling of the airplane fuselage:
CAD software is adopted for model establishment and importing, and the model establishment and importing comprise basic appearance modeling of the airplane, key position characteristic modeling, model format conversion and importing; model modification is to remove redundant details irrelevant to the calculation result and reserve electromagnetic correlation characteristics influencing the calculation result, including geometric model cleaning, removal of model irrelevant details and modification of a model overlapping region; the material information import refers to the assignment of dielectric constant, conductivity and magnetic conductivity according to actual materials of the machine body, and the establishment of correct boundary conditions of the model; the grid division is to carry out numerical value dispersion and interpolation according to the point size, the physical size and the material attribute of the current model.
(2) In modeling of the airborne equipment:
performing digital modeling by using frequency equipment emission modeling according to product information of on-board radiation equipment, wherein the digital modeling comprises radiation unit modeling, radiation power input and boundary condition determination; the disturbance equipment emission modeling comprises conducted emission and radiation emission, and comprises high-power electric equipment, switch rapid on-off equipment and high-speed data transmission and processing equipment; the sensitive equipment cabinet modeling is used for modeling the cabinet, and the sensitive equipment board-level equipment modeling is used for modeling the board-level equipment.
(3) In the modeling of the cable inside the airplane:
the cable topology layout definition defines cable nodes, wiring layout and trapping modes according to wiring paths of various equipment power lines and signal interconnection lines on the aircraft; the cable bundle type definition is to determine a specific cable pattern according to the number of the wire cores, the distance of the wire cores and the shielding mode; the cable electromagnetic attribute definition defines external electromagnetic attributes related to a cable model; the cable modeling is to extract electromagnetic characteristic parameters calculated by cable modeling.
The different positions on the machine include: different cabins, sensitive equipment parts, gaps, cables.
The test probe comprises: voltage probe, current probe, electric field probe, magnetic field probe, broadband antenna, integral electric field probe.
The step 2 comprises the following steps:
the current probe is additionally arranged on a cable, the monitoring equipment is connected with the cable for conducting and transmitting, the frequency sweep measurement is carried out in the frequency range of 10k-500MHz, and the electromagnetic emission transmitted to the outside by the equipment through the connected cable is obtained; the voltage probe is additionally arranged at the position of a power supply network of the equipment and is used for collecting ripple signals of the power supply system, recording the voltage fluctuation condition of the power supply system caused by the switching of the equipment and collecting spike signals generated by the equipment, and the instantaneous bandwidth is not lower than 500MHz; the electric field and magnetic field probe is additionally arranged at the key ports of the transmitting equipment and the sensitive equipment to realize the test of the near field electric field and the magnetic field, the electric field probe covers the frequency range of 10k-10GHz, and the magnetic field probe covers the frequency range of 25Hz-3 GHz; the broadband antenna is additionally arranged at the far end of the equipment, covers the frequency range of 10k-40GHz, performs frequency sweep test on electromagnetic emission in a local equipment concentrated area in the cabin through the deployment of the antenna group, and obtains external radiation emission data of the equipment in the area through a shell, a cable and the like; the integral electric field probe is additionally arranged in a central area in the engine room, monitors the comprehensive field intensity in the area, integrates all frequency signals of 10k-40GHz to obtain the comprehensive electric field value, selects an average value, a maximum value and a minimum value, and judges the incoming wave direction through the recording of X, Y and Z directions.
The step 3 comprises the following steps:
firstly, classifying probes according to the temperature and the electric stress of a working scene;
secondly, classifying the probes according to an electric field, a magnetic field, current conducted interference and voltage conducted interference;
thirdly, developing a probe calibration environment capable of simulating the loading of airborne stress according to different working scenes;
fourthly, determining a temperature range, a calibration frequency range and an intensity range to be calibrated, and calibrating the calibration system;
fifthly, calibrating the probe special for the airborne electromagnetic environment test within the set working temperature, calibration frequency and intensity range.
The invention has the advantages that:
the invention provides a deployment method of an airborne electromagnetic environment test probe, which has the following advantages:
a) Based on the steps of simulation prediction, assembly and calibration, the precision of the test probe after assembly is not reduced, and the reliability is high;
b) The normal work of electronic and electric equipment of the carrier is not influenced, and the original electromagnetic distribution of the carrier is not influenced;
c) The universality is strong, and the device is suitable for electromagnetic environment testing of civil aircraft of military aircraft.
Drawings
FIG. 1 is a schematic illustration of modeling a fuselage section;
FIG. 2 is a schematic diagram of electromagnetic emissions from an airborne device;
FIG. 3 is a probe calibration flow chart.
Detailed Description
In order to make the purpose and design method of the present invention clearer, the present invention will now be described in further detail:
a) Airborne electromagnetic environment simulation prediction
The airborne electromagnetic environment simulation comprises 3 parts, namely fuselage modeling, airborne equipment modeling and aircraft internal cable modeling.
1) Aircraft fuselage modeling
As shown in fig. 1, fuselage modeling is performed on a selected airplane model, an airplane geometric model is converted into an electromagnetic model, and the model modeling, the model modification, the material information import and the grid division are divided. The model establishment and import adopts CAD software, and needs to comprise basic appearance modeling of the airplane, key position characteristic modeling (cabin, gap and interface), model format conversion and import; the model modification is to remove redundant details irrelevant to the calculation result and reserve electromagnetic correlation characteristics influencing the calculation result, and the electromagnetic correlation characteristics comprise geometric model cleaning, model irrelevant detail removal and model overlapping region modification; the material information import refers to the assignment of dielectric constant, conductivity and magnetic conductivity according to actual materials of the machine body, and the establishment of correct boundary conditions of the model; the grid division is mainly to carry out numerical value dispersion and interpolation according to the point size, the physical size and the material attribute of the current model and establish correct basis function representation.
2) Airborne equipment modeling
As shown in fig. 2, electromagnetic feature modeling is performed on the selected onboard typical device and system, and the modeling includes frequency-using device emission modeling, disturbance device emission modeling, sensitive device cabinet modeling, and sensitive device board-level device modeling. Performing digital modeling by using frequency equipment emission modeling according to product information of main radiating equipment on the machine, wherein the digital modeling comprises the steps of modeling a radiating element, inputting radiation power and determining boundary conditions; disturbance equipment emission modeling mainly considers unintentional emission of non-frequency equipment on a machine, including conducted emission and radiation emission, and mainly considers high-power electric equipment, switch rapid on-off equipment and high-speed data transmission and processing equipment; the machine cabinet modeling of the sensitive equipment and the board-level equipment modeling of the sensitive equipment perform digital modeling on the whole equipment from different product levels, the machine cabinet modeling reflects the attenuation degree of electromagnetic radiation coupled to the inside of the machine cabinet, and the board-level equipment modeling represents the root of a typical sensitive problem.
3) Aircraft interior cable modeling
Electromagnetic characteristic modeling is carried out on the selected cable in the airplane, and the electromagnetic characteristic modeling is mainly decomposed into cable topology layout definition, cable bundle type definition, cable electromagnetic attribute definition and electromagnetic characteristic parameter extraction. The topological layout of the cable mainly defines the factors such as cable nodes, routing layout, trapping mode and the like according to the routing paths of various equipment power lines and signal interconnection lines on the machine; the cable bundle type is determined according to the number of the wire cores, the distance of the wire cores and the shielding mode, such as a twisted pair, a coaxial wire and a strip line; the cable electromagnetic property is to define external electromagnetic properties related to a cable model, such as port impedance characteristics, the type of transmission signals and whether inter-wire interference is considered; the cable modeling is considered in a mode that a mutual coupling interface exists between an airplane and a cable, and electromagnetic characteristic parameters calculated by the cable modeling are extracted continuously, such as transmission characteristics, radiation characteristics and transfer impedance.
According to the modeling in the step 3, the electromagnetic environment parameters of different positions (different cabins, sensitive equipment parts, gaps and cables) on the machine under the action condition of the radiation source on the machine are obtained, simulation is carried out by utilizing the electromagnetic field vector superposition principle, the electromagnetic environment of key parts in the machine is comprehensively predicted, comprehensive electromagnetic environment prediction data of specific positions on the machine are obtained, and electromagnetic vulnerable points are screened.
b) Test probe installation deployment
The current probe is additionally arranged on the cable, the monitoring equipment is connected with the cable for conducting emission, sweep frequency measurement is carried out within the frequency range of 10k-500MHz, and electromagnetic emission transmitted to the outside by the equipment through the connected cable can be obtained; the voltage probe is additionally arranged at the position of a power supply network of the equipment and is used for collecting ripple signals of the power supply system, recording the voltage fluctuation condition of the power supply system caused by the switching of the equipment and collecting spike signals generated by the equipment, and the instantaneous bandwidth is not lower than 500MHz; the electric field probe and the magnetic field probe are additionally arranged near the key ports of the transmitting equipment and the sensitive equipment to realize the test of the near field electric field and the magnetic field, the electric field probe covers the frequency range of 10k-10GHz, and the magnetic field probe covers the frequency range of 25Hz-3 GHz; the broadband antenna is additionally arranged at a far position of the equipment, covers a frequency range of 10k-40GHz, performs frequency sweep test on electromagnetic emission in a local equipment concentrated area in the cabin through antenna group deployment, and obtains external radiation emission data of the equipment in the area through a shell, a cable and the like; the integral electric field probe is additionally arranged in a central area in the engine room, monitors the comprehensive field intensity in a certain area, integrates all frequency signals of 10k-40GHz to obtain the comprehensive electric field value, can select the modes of average value, maximum value, minimum value and the like, and judges the incoming wave direction through the recording of X, Y and Z directions.
According to the working characteristics of each sensor and the screening results of electromagnetic vulnerable points, 6 types of test probes are deployed, in addition, the influence of the deployment of the sensor on the normal work of the built-in electronic and electrical equipment is also considered, when the test probes are deployed, the problems of installation position, space and weight are fully considered, and the influence on the normal layout and wiring of the built-in equipment is reduced as much as possible.
c) Test-dedicated probe calibration and reliability verification
The probe special for airborne electromagnetic environment test is calibrated to verify the reliability of the probe in an airborne environment, the traditional probe calibration environment is often in a room temperature environment, and a real-time monitoring system needs to consider various temperature stress conditions which may occur in the airborne environment.
The work flow of the probe calibration comprises the following steps: firstly, classifying probes according to the temperature and the electric stress of a working scene; secondly, classifying the probe according to an electric field, a magnetic field, current conducted interference (continuous/transient state) and voltage conducted interference (continuous/transient state); thirdly, developing a probe calibration environment capable of simulating and loading airborne stress (such as temperature and electric stress) according to different working scenes; fourthly, determining a temperature range, a calibration frequency range and an intensity range to be calibrated, and calibrating the calibration system; fifthly, calibrating the special probe for the airborne electromagnetic environment test within the set working temperature, frequency and intensity range. The workflow of the probe calibration is shown in figure 3.
Claims (8)
1. A deployment method of an airborne electromagnetic environment test probe is characterized by comprising the following steps:
step 1, modeling an airplane body, airborne equipment and an internal cable to obtain electromagnetic environment parameters of different positions on the airplane under the action of an onboard radiation source;
step 2, comprehensively predicting the electromagnetic environment of key parts in the machine, screening electromagnetic vulnerable points, and deploying a test probe for the electromagnetic vulnerable points; the step 2 comprises the following steps: the current probe is additionally arranged on a cable, the monitoring equipment is connected with the cable for conducting and transmitting, the frequency sweep measurement is carried out in the frequency range of 10k-500MHz, and the electromagnetic emission transmitted to the outside by the equipment through the connected cable is obtained; the voltage probe is additionally arranged at the position of a power supply network of the equipment and is used for collecting ripple signals of the power supply system, recording the voltage fluctuation condition of the power supply system caused by the switching of the equipment and collecting spike signals generated by the equipment, and the instantaneous bandwidth is not lower than 500MHz; the electric field and magnetic field probe is additionally arranged at the key ports of the transmitting equipment and the sensitive equipment to realize the test of the near field electric field and the magnetic field, the electric field probe covers the frequency range of 10k-10GHz, and the magnetic field probe covers the frequency range of 25Hz-3 GHz; the broadband antenna is additionally arranged at the far end of the equipment, covers the frequency range of 10k-40GHz, performs frequency sweep test on electromagnetic emission in a local equipment concentrated area in the cabin through the deployment of the antenna group, and obtains radiation emission data of the equipment in the area through the shell and the cable; the integral electric field probe is additionally arranged in a central area in the engine room, the comprehensive field intensity in the area is monitored, all frequency signals of 10k-40GHz are integrated to obtain the comprehensive electric field value, the average value, the maximum value and the minimum value are selected, and the incoming wave direction is judged through the recording of X, Y and Z directions;
and 3, calibrating the test probe, and verifying the reliability of the test probe in an airborne environment considering various temperature stresses.
2. The deployment method of the airborne electromagnetic environment test probe according to claim 1, wherein the modeling of step 1 is divided into: modeling a fuselage, modeling airborne equipment and modeling cables in the aircraft;
(1) Aircraft fuselage modeling
Carrying out fuselage modeling aiming at the selected airplane type, converting an airplane geometric model into an electromagnetic model, and dividing the electromagnetic model into model building import, model correction, material information import and grid division;
(2) Airborne equipment modeling
Performing electromagnetic characteristic modeling aiming at selected onboard typical equipment and systems, wherein the electromagnetic characteristic modeling comprises frequency equipment emission modeling, disturbance equipment emission modeling, sensitive equipment cabinet modeling and sensitive equipment board level equipment modeling;
(3) Aircraft interior cable modeling
And performing electromagnetic characteristic modeling on the selected cable in the airplane, and decomposing the electromagnetic characteristic modeling into cable topology layout definition, cable bundle type definition, cable electromagnetic attribute definition and electromagnetic characteristic parameter extraction.
3. The deployment method of the airborne electromagnetic environment test probe according to claim 2, wherein (1) in aircraft fuselage modeling:
CAD software is adopted for model building and importing, and the model building and importing comprise basic appearance modeling of the airplane, key position feature modeling, model format conversion and importing; the model modification is to remove redundant details irrelevant to the calculation result and reserve electromagnetic correlation characteristics influencing the calculation result, and the electromagnetic correlation characteristics comprise geometric model cleaning, model irrelevant detail removal and model overlapping region modification; the material information import refers to the assignment of dielectric constant, conductivity and magnetic conductivity according to actual materials of the machine body, and the establishment of correct boundary conditions of the model; the grid division is to carry out numerical value dispersion and interpolation according to the point size, the physical size and the material attribute of the current model.
4. The deployment method of the airborne electromagnetic environment test probe according to claim 2, wherein in (2) modeling of the airborne equipment:
performing digital modeling by using frequency equipment emission modeling according to product information of on-board radiation equipment, wherein the digital modeling comprises radiation unit modeling, radiation power input and boundary condition determination; the disturbance equipment emission modeling comprises conducted emission and radiation emission, and comprises high-power electric equipment, switch rapid on-off equipment and high-speed data transmission and processing equipment; the sensitive equipment cabinet modeling is used for modeling the cabinet, and the sensitive equipment board-level equipment modeling is used for modeling the board-level equipment.
5. The deployment method of the airborne electromagnetic environment test probe according to claim 2, wherein (3) in the modeling of the cable inside the aircraft:
the cable topology layout definition defines cable nodes, wiring layout and trapping modes according to wiring paths of power lines and signal interconnection lines of various devices on the computer; the cable bundle type definition is to determine a specific cable pattern according to the number of the wire cores, the distance of the wire cores and the shielding mode; the cable electromagnetic attribute definition defines external electromagnetic attributes related to a cable model; the cable modeling is to extract electromagnetic characteristic parameters calculated by cable modeling.
6. The method of deploying an onboard electromagnetic environment test probe of claim 1, wherein the different locations on the aircraft include: different cabins, sensitive equipment parts, gaps and cables.
7. The method of deploying an onboard electromagnetic environment test probe of claim 1, wherein the test probe comprises: voltage probe, current probe, electric field probe, magnetic field probe, broadband antenna, integral electric field probe.
8. The deployment method of the airborne electromagnetic environment test probe according to claim 1, wherein the step 3 comprises:
firstly, classifying probes according to the temperature and the electric stress of a working scene;
secondly, classifying the probes according to an electric field, a magnetic field, current conducted interference and voltage conducted interference;
thirdly, developing a probe calibration environment capable of simulating the loading of airborne stress according to different working scenes;
fourthly, determining a temperature range, a calibration frequency range and a strength range to be calibrated, and calibrating the calibration system;
fifthly, calibrating the probe special for airborne electromagnetic environment test within the set working temperature, calibration frequency and intensity range.
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