A flight control system multi-level high-intensity radiation field testing method and system

Abstract

The embodiment of the present application is about a multi-level high-intensity radiation field test method and system for a flight control system. The test method includes: according to the aircraft structure diagram and the radiation test level, the flight control system components are divided into a first test component, a second test component and a third test component; calibrating the equipment in the electromagnetic reverberation chamber so that the field strength of the electromagnetic reverberation chamber reaches the preset calibration field strength; arranging the first test component, the second test component and the third test component in the test area of ​​the electromagnetic reverberation chamber; performing a high-intensity radiation field test on the first test component; covering the first test component with a shielding net, and performing a high-intensity radiation field test on the second test component; covering the first test component and the second test component with a shielding net, and performing a high-intensity radiation field test on the third test component. The test method provided in the present application can realize the testing of multiple radiation test levels on the flight control system components in the electromagnetic reverberation chamber.

Description

Technical Field

[0001] The present application relates to the technical field of flight control system testing, and in particular to a flight control system multi-level high-intensity radiation field testing method and system. Background Art

[0002] The flight control system of an aircraft is often composed of multiple components. Based on the different levels of electromagnetic shielding protection for the multiple components of the flight control system, the multiple components of the flight control system are distributed in the shielded area, semi-exposed area and exposed area of ​​the aircraft. This requires that when conducting airworthiness certification tests on the flight control system, it is necessary to conduct verification of different radiation test levels on multiple components distributed in different areas. Among them, the components in the exposed area need to undergo the highest radiation test level, the components in the semi-exposed area need to undergo a relatively low radiation test level, and the components in the shielded area need to undergo the lowest radiation test level.

[0003] In the prior art, electromagnetic reverberation chambers are generally used to conduct high-intensity radiation field tests on components to be tested. Although electromagnetic reverberation chambers can provide a high-intensity radiation field test environment, when conducting higher-level radiation tests, components with lower radiation test level requirements often show faults, which will affect the testing of components with higher radiation test level requirements, making it impossible to conduct multiple radiation test level tests on multiple components of the flight control system in an electromagnetic reverberation chamber.

[0004] Therefore, it is necessary to provide a new technical solution to improve one or more problems existing in the above solutions.

[0005] It should be noted that the information disclosed in the above background technology section is only used to enhance the understanding of the background of the present application, and therefore may include information that does not constitute the prior art known to ordinary technicians in the field. Summary of the invention

[0006] The purpose of the embodiments of the present application is to provide a multi-level high-intensity radiation field testing method and system for a flight control system, so as to implement multiple radiation test level testing of flight control system components in an electromagnetic reverberation chamber.

[0007] According to a first aspect of an embodiment of the present application, a method for testing a multi-level high-intensity radiation field of a flight control system is provided, comprising:

[0008] According to the aircraft structure diagram and radiation test level, the flight control system components are divided into the first test component, the second test component and the third test component;

[0009] Calibrate the equipment in the electromagnetic reverberation chamber so that the field strength of the electromagnetic reverberation chamber reaches a preset calibration field strength;

[0010] Arranging the first test assembly, the second test assembly and the third test assembly in a test area of ​​the electromagnetic reverberation chamber;

[0011] performing a high-intensity radiation field test on the first test assembly;

[0012] Covering the first test assembly with a shielding net, and performing a high-intensity radiation field test on the second test assembly;

[0013] Covering the first test assembly and the second test assembly with a shielding net, and performing a high-intensity radiation field test on the third test assembly;

[0014] The radiation test level of the third test component is higher than the radiation test level of the second test component, and the radiation test level of the second test component is higher than the radiation test level of the first test component.

[0015] In an exemplary embodiment of the present application, the device in the calibration electromagnetic reverberation chamber includes:

[0016] Selecting a plurality of measuring points within the test area;

[0017] Measuring the field strength at a plurality of the measuring points to obtain a plurality of measured field strengths;

[0018] Calculate an average field strength based on the multiple measured field strengths to obtain an actual field strength in the test area;

[0019] According to the preset calibration field strength and the actual field strength, the equipment in the electromagnetic reverberation chamber is adjusted until the actual field strength reaches the preset calibration field strength.

[0020] In an exemplary embodiment of the present application, the device for calibrating the electromagnetic reverberation chamber further includes:

[0021] The field strength standard deviation is calculated based on the average field strength and the plurality of measured field strengths, and the calculation formula of the field strength standard deviation is:

[0022] (1)

[0023] in, For the The measured field strength at each measuring point is is the average field strength, is the number of measurement points, is the standard deviation;

[0024] The equipment in the electromagnetic reverberation chamber is adjusted according to the field strength standard deviation until the field strength standard deviation reaches a preset standard deviation threshold.

[0025] In an exemplary embodiment of the present application, the test area includes a shielding area, a semi-exposed area, and an exposed area;

[0026] Arranging the first test assembly, the second test assembly, and the third test assembly in a test area of ​​the electromagnetic reverberation chamber includes:

[0027] Arrange the first test component in the shielding area, arrange the second test component in the semi-exposed area, and arrange the third test component in the exposed area;

[0028] A connecting cable is arranged in the test area, and the first test component, the second test component and the third test component are connected to each other through the connecting cable.

[0029] In an exemplary embodiment of the present application, the arranging the first test assembly, the second test assembly and the third test assembly in the test area of ​​the electromagnetic reverberation chamber further includes:

[0030] Calibrate the layout distances among the first test component, the second test component and the third test component.

[0031] In an exemplary embodiment of the present application, the high-intensity radiation field test includes:

[0032] Generate a radio frequency signal using a signal generator;

[0033] amplifying the radio frequency signal to a preset value through a power amplifier;

[0034] The test data of the flight control system components are collected, and the performance of the flight control system components is analyzed based on the test data to obtain analysis results.

[0035] In an exemplary embodiment of the present application, when a high-intensity radiation field test is performed on the first test component, the radio frequency signal is amplified to a first preset value by the power amplifier;

[0036] When performing a high-intensity radiation field test on the second test component, amplifying the radio frequency signal to a second preset value through the power amplifier;

[0037] When performing a high-intensity radiation field test on the third test component, amplifying the radio frequency signal to a third preset value through the power amplifier;

[0038] The first preset value is smaller than the second preset value, and the second preset value is smaller than the third preset value.

[0039] In an exemplary embodiment of the present application, before collecting the test data of the flight control system components, the method further includes:

[0040] Monitor the field strength of the test area by using a field strength monitoring device to obtain a field strength monitoring result;

[0041] The signal generator and the power amplifier are adjusted according to the preset test field strength and the field strength monitoring result.

[0042] In an exemplary embodiment of the present application, the shielding effectiveness of the shielding net satisfies formula (2):

[0043] (2)

[0044] in, is the frequency of the electromagnetic wave, is the thickness of the shielding mesh, is the relative magnetic permeability of the shielding net, is the relative conductivity of the shielding mesh, is the offset constant, It is the shielding effectiveness of the shielding net.

[0045] According to a second aspect of an embodiment of the present application, a flight control system multi-level high-intensity radiation field test system is provided, the test system is applied to the flight control system multi-level high-intensity radiation field test method, and the test system includes:

[0046] Electromagnetic reverberation chamber, used to provide a test area;

[0047] A signal generator, used for generating a radio frequency signal;

[0048] A power amplifier, used to amplify the radio frequency signal to a preset value;

[0049] Shielding net, used to cover the flight control system components;

[0050] A field strength monitoring device, used to monitor the field strength in the test area;

[0051] A data acquisition system, used to collect test data of the flight control system components;

[0052] The data analysis system is used to analyze the performance of the flight control system components based on the test data to obtain analysis results.

[0053] The technical solution provided by this application may have the following beneficial effects:

[0054] In an embodiment of the present application, on the one hand, according to the aircraft structure diagram and the radiation test level, the flight control system components are divided into a first test component, a second test component and a third test component, so that during the test process, the first test component, the second test component and the third test component can be tested in batches to meet the different radiation test level requirements of the flight control system components; on the other hand, in this embodiment, the first test component, the second test component and the third test component are sequentially subjected to high-intensity radiation field tests in the order of the radiation test level from low to high, and when testing the second test component with relatively high radiation test level requirements, a shielding net is used to cover the first test component to avoid the first test component from displaying a fault, thereby ensuring that the testing of the second test component is not affected; when testing the third test component with the highest radiation test level requirements, a shielding net is used to cover the first test component and the second test component to avoid the first test component and the second test component from displaying a fault, thereby ensuring that the testing of the third test component is not affected, thereby realizing the testing of multiple radiation test levels of flight control system components in an electromagnetic reverberation chamber.

[0055] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0056] The drawings herein are incorporated into the specification and constitute a part of the specification, illustrate embodiments consistent with the present application, and together with the specification are used to explain the principles of the present application. Obviously, the drawings described below are only some embodiments of the present application, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0057] Figure 1 A flow chart showing a method for testing a multi-level high-intensity radiation field of a flight control system in an exemplary embodiment of the present application;

[0058] Figure 2 A test scene diagram showing a test area in an exemplary embodiment of the present application;

[0059] Figure 3 A test scene diagram showing a first test component in which a shielding area is covered with a shielding net in an exemplary embodiment of the present application;

[0060] Figure 4 A test scene diagram showing a first test component in a shielded area covered with a shielding net and a second test component in a semi-exposed area in an exemplary embodiment of the present application. DETAILED DESCRIPTION

[0061] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be implemented in a variety of forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this application will be more comprehensive and complete and fully convey the concepts of the example embodiments to those skilled in the art. The described features may be combined in any suitable manner in one or more embodiments.

[0062] In addition, the drawings are only schematic illustrations of the present application and are not necessarily drawn to scale. The same reference numerals in the drawings represent the same or similar parts, and their repeated descriptions will be omitted. Some of the block diagrams shown in the drawings are functional entities and do not necessarily correspond to physically or logically independent entities.

[0063] In this example implementation, a multi-level high-intensity radiation field test method for a flight control system is first provided. Figure 1 As shown in , the method may include the following steps:

[0064] Step S101: According to the aircraft structure diagram and the radiation test level, the flight control system components are divided into a first test component, a second test component, and a third test component.

[0065] Step S102: Calibrate the equipment in the electromagnetic reverberation chamber so that the field strength of the electromagnetic reverberation chamber reaches a preset calibration field strength.

[0066] Step S103: Arrange the first test assembly, the second test assembly and the third test assembly in the test area of ​​the electromagnetic reverberation chamber.

[0067] Step S104: performing a high-intensity radiation field test on the first test component.

[0068] Step S105: Cover the first test component with a shielding net and perform a high-intensity radiation field test on the second test component.

[0069] Step S106: Cover the first test assembly and the second test assembly with a shielding net, and perform a high-intensity radiation field test on the third test assembly.

[0070] Among them, the radiation test level of the third test component is higher than the radiation test level of the second test component, and the radiation test level of the second test component is higher than the radiation test level of the first test component.

[0071] In an embodiment of the present application, on the one hand, according to the aircraft structure diagram and the radiation test level, the flight control system components are divided into a first test component, a second test component and a third test component, so that during the test process, the first test component, the second test component and the third test component can be tested in batches to meet the different radiation test level requirements of the flight control system components; on the other hand, in this embodiment, the first test component, the second test component and the third test component are sequentially subjected to high-intensity radiation field tests in the order of the radiation test level from low to high, and when testing the second test component with relatively high radiation test level requirements, a shielding net is used to cover the first test component to avoid the first test component from displaying a fault, thereby ensuring that the testing of the second test component is not affected; when testing the third test component with the highest radiation test level requirements, a shielding net is used to cover the first test component and the second test component to avoid the first test component and the second test component from displaying a fault, thereby ensuring that the testing of the third test component is not affected, thereby realizing the testing of multiple radiation test levels of flight control system components in an electromagnetic reverberation chamber.

[0072] Next, we will refer to Figures 1 to 4 As shown in , each step of the above method in this example implementation is described in more detail.

[0073] In one embodiment, the calibration of the equipment in the electromagnetic reverberation chamber in step S102 may include the following steps:

[0074] Select multiple measurement points within the test area;

[0075] Measuring the field strength at a plurality of measuring points to obtain a plurality of measured field strengths;

[0076] Calculate the average field strength based on multiple measured field strengths to obtain the actual field strength in the test area;

[0077] According to the preset calibration field strength and the actual field strength, adjust the equipment in the electromagnetic reverberation room until the actual field strength reaches the preset calibration field strength.

[0078] The above average field strength is obtained by averaging multiple measured field strengths. The obtained average field strength can more accurately reflect the actual field strength level in the test area. The preset calibration field strength and the actual field strength can be combined to adjust the equipment in the electromagnetic reverberation room, which is more conducive to ensuring that the actual field strength level in the test area is close to the preset calibration field strength and improving the calibration accuracy.

[0079] It should be noted that, in the step of selecting a plurality of measurement points in the test area, the selected plurality of measurement points should be evenly distributed in the test area of ​​the electromagnetic reverberation chamber to fully reflect the field intensity distribution in the test area.

[0080] Specifically, in one embodiment, at least 8 measurement points may be selected in the test area, and these 8 measurement points should be distributed at the 8 vertices of a cube. In another embodiment, at least 9 measurement points may be selected in the test area, and these 9 measurement points should be distributed at the 8 vertices and the center of a cube.

[0081] Specifically, in the step of measuring the field strength at multiple measurement points, an electric field probe may be used for measurement, and a suitable electric field probe may be selected based on the field strength test accuracy requirements. For example, in this application, a wide-band field strength probe such as the Narda NBM series or the ARFL7000 series may be used, which have good isotropic properties and high sensitivity and can accurately measure the electric field strength at different frequencies.

[0082] Specifically, in the step of adjusting the equipment in the electromagnetic reverberation chamber according to the preset calibration field strength and the actual field strength, the position and tilt angle of the reflector in the electromagnetic reverberation chamber can be selectively adjusted. By adjusting the reflector, the reflection path of the electromagnetic wave can be changed, thereby adjusting the field strength distribution in the test area to adjust the actual field strength in the test area.

[0083] It should be noted that in actual operation, technicians can gradually adjust the position and tilt angle of the reflector according to the results of multiple field strength measurements, and through repeated testing and repeated adjustment operations, they can adjust the actual field strength in the test area to the preset calibration field strength.

[0084] Furthermore, the equipment in the electromagnetic reverberation chamber is calibrated, and further includes:

[0085] The standard deviation of the field strength is calculated based on the average field strength and multiple measured field strengths. The calculation formula for the standard deviation of the field strength is:

[0086] (1)

[0087] in, For the The measured field strength at each measuring point is is the average field strength, is the number of measurement points, is the standard deviation;

[0088] The equipment in the electromagnetic reverberation chamber is adjusted according to the field strength standard deviation until the field strength standard deviation reaches a preset standard deviation threshold.

[0089] By introducing the field strength standard deviation, the uniformity of the field strength in the test area can be evaluated. This embodiment does not limit the specific value of the above-mentioned preset standard deviation threshold. It should be noted that the smaller the preset standard deviation threshold set in this embodiment, the more uniform the field strength distribution in the test area is, which is conducive to improving the reliability of the test results. Therefore, the above-mentioned step of adjusting the equipment in the electromagnetic reverberation room according to the field strength standard deviation until the field strength standard deviation reaches the preset standard deviation threshold can ensure that the field strength distribution in the test area is more uniform, thereby ensuring that the test results are more reliable.

[0090] Specifically, in the step of adjusting the equipment in the electromagnetic reverberation chamber according to the field strength standard deviation, the position and tilt angle of the reflector in the electromagnetic reverberation chamber can be selectively adjusted, and the position of the stirrer and the transmitting antenna in the electromagnetic reverberation chamber can also be selectively adjusted to improve the uniformity of the field strength in the test area.

[0091] In one embodiment, the test area includes a shielded area, a semi-exposed area, and an exposed area;

[0092] Arranging the first test assembly, the second test assembly and the third test assembly in a test area of ​​the electromagnetic reverberation chamber includes:

[0093] Arranging the first test component in the shielding area, arranging the second test component in the semi-exposed area, and arranging the third test component in the exposed area;

[0094] A connecting cable is arranged in the test area, and the first test component, the second test component and the third test component are connected to each other through the connecting cable.

[0095] The positions of the above-mentioned shielded areas, semi-exposed areas and exposed areas in the test area must be arranged according to the aircraft structure diagram to ensure that the relative positions of the shielded areas, semi-exposed areas and exposed areas in the test area are consistent with the relative positions of the shielded areas, semi-exposed areas and exposed areas of the aircraft, so that the high-intensity radiation field test of the flight control system components in the test area is more in line with the actual situation.

[0096] By arranging the first test component in the shielded area, the second test component in the semi-exposed area, and the third test component in the exposed area, the arrangement of the first test component, the second test component, and the third test component in the test area complies with the following situation mentioned in the background technology: based on the different levels of electromagnetic shielding protection for multiple components of the flight control system, the multiple components of the flight control system are respectively distributed in the shielded area, semi-exposed area, and exposed area of ​​the aircraft.

[0097] The connecting cables are arranged in the test area, and the first test component, the second test component and the third test component are connected to each other through the connecting cables to simulate the actual electrical connection relationship between the flight control system components on the aircraft.

[0098] It should be noted that the aircraft structure diagram mentioned in this embodiment shows the installation positions of the flight control system components on the aircraft structure, including but not limited to: the installation positions of the first test assembly, the second test assembly and the third test assembly on the aircraft structure, the spacing between the first test assembly, the second test assembly and the third test assembly, and the layout of the connecting cables on the aircraft structure. It should also be noted that the first test assembly, the second test assembly and the third test assembly also include multiple devices respectively. According to the aircraft structure diagram, the installation positions of these devices on the aircraft structure and the spacing between these devices can also be confirmed.

[0099] It should be noted that the reference Figure 2 As shown in , the first test assembly in the shielded area, the third test assembly in the exposed area, and the second test assemblies in the two semi-exposed areas are respectively connected to the connecting cables. The shielded area is provided with inertial navigation, flap sensor, flight control module, flap control electronics, pedal sensor, atmospheric data module, landing gear control unit, flight control computer-1, flight control computer-2, flight control computer-3, servo electronics-1, servo electronics-2, servo electronics-3, servo electronics-4, power module-1, power module-2, power module-3, power module-4, AC generator impedance network and multiple impedance networks and other devices. The exposed area is provided with landing gear control unit, spoiler, spoiler, left outer aileron, right outer aileron, atmospheric data module, integrated standby instrument, right inner aileron, motor control electronics, left inner aileron, spoiler control module, lower rudder, right outer elevator, upper rudder, left outer elevator, right inner elevator, middle rudder, left inner elevator and other devices. One semi-exposed area is equipped with deceleration control lever, throttle control instrument, trim control panel, interface display unit, angle of attack sensor, actuation brake pedal, inertial navigation, atmospheric data module, bracket switch, inertial navigation assembly, radio altimeter, maintenance switch, spoiler and other devices; the other semi-exposed area is equipped with angle sensor, radio altimeter, right side bar, left side bar, remote switch, interface display unit, global landing unit, atmospheric data module, angle of attack sensor, auxiliary actuation brake pedal, window heating module, dimming control panel, atmospheric temperature sensor and other devices. It should be noted that the types of devices arranged in the shielded area, exposed area and two semi-exposed areas listed above are only for illustrative purposes, and do not limit the arrangement of devices of corresponding radiation test levels in the shielded area, exposed area and semi-exposed area.

[0100] Further, the first test assembly, the second test assembly and the third test assembly are arranged in a test area of ​​the electromagnetic reverberation chamber, and further comprising:

[0101] Calibrate the layout distances among the first test component, the second test component, and the third test component.

[0102] Optionally, according to the actual layout positions of the flight control system components on the aircraft structure diagram, the layout distances between the first test component, the second test component and the third test component are calibrated to ensure that the first test component, the second test component and the third test component meet the actual layout conditions of the flight control system components.

[0103] Optionally, by evaluating the electromagnetic coupling effect between the first test component, the second test component and the third test component, the layout distance between the first test component, the second test component and the third test component is fine-tuned to calibrate the layout distance between the first test component, the second test component and the third test component. In this way, abnormal electromagnetic coupling caused by improper layout of flight control system components or connection cable layout that does not conform to actual conditions can be reduced, thereby avoiding the test results being affected by abnormal electromagnetic coupling.

[0104] Specifically, multiple field strength probes can be arranged in the electromagnetic reverberation chamber, and the field strength at different positions can be continuously measured using the multiple field strength probes to obtain the field strength change at different positions. The electromagnetic coupling effect between the first test component, the second test component, and the third test component can be evaluated by analyzing the field strength change to determine whether there is abnormal electromagnetic coupling.

[0105] Furthermore, when calibrating the layout distances between the first test component, the second test component and the third test component, a laser rangefinder can be used for distance measurement to ensure that the measured layout distances between the first test component and the second test component, the layout distances between the second test component and the third test component, and the layout distances between the first test component and the third test component are accurate enough, thereby avoiding the calibration effect being affected by the measurement accuracy.

[0106] In one embodiment, the high intensity radiation field test includes:

[0107] Generate a radio frequency signal using a signal generator;

[0108] Amplifying the radio frequency signal to a preset value through a power amplifier;

[0109] Collect test data of flight control system components, analyze the performance of flight control system components based on the test data, and obtain analysis results.

[0110] The above-mentioned signal generator and power amplifier cooperate to form a certain intensity of field strength in the test area, thereby radiating the flight control system components; and by collecting test data of the flight control system components affected by radiation, the performance of the flight control system components under radiation can be analyzed and the analysis results can be obtained.

[0111] It should be noted that the steps included in the above-mentioned high-intensity radiation field test are applicable to respectively conducting high-intensity radiation field tests on the first test component, the second test component and the third test component. It is only necessary to control the specific operating parameters of the signal generator and the power amplifier to control the field intensity formed in the test area, thereby meeting the different radiation test level requirements of the first test component, the second test component and the third test component.

[0112] Optionally, in the step of generating a radio frequency signal using a signal generator, the radio frequency signal can be controlled within the range of 100 MHz-18 GHz, which covers the electromagnetic interference frequency band that most civilian and military electronic equipment may encounter, so as to ensure that the test results of the high-intensity radiation field test are true and reliable. In this embodiment, a signal generator with high stability, low phase noise and precise frequency control capability can be selected, such as Keysight N5173B or Rohde & Schwarz SMB100A series.

[0113] In the step of amplifying the radio frequency signal to a preset value through a power amplifier, a broadband power amplifier can be selected to ensure that a high-intensity radiation field that meets the test standard can be formed in the electromagnetic reverberation chamber.

[0114] In the above-mentioned high-intensity radiation field test, precise control of the output power of the signal generator and the gain of the power amplifier is conducive to forming a stable and uniform field strength distribution in the test area.

[0115] It should be noted that in the step of collecting test data of flight control system components and analyzing the performance of flight control system components based on the test data to obtain analysis results, the test data includes but is not limited to: the command processing time and response time of the flight control computer, the output signal accuracy and noise level of sensors (such as accelerometers and gyroscopes). Performance includes but is not limited to: command processing accuracy and delay time, sensor reading stability and error changes. The analysis results can be obtained through the above test data and performance.

[0116] It should also be noted that based on the entire test process of the above-mentioned high-intensity radiation field test, a test report can be generated for the relevant staff to review. The test report includes but is not limited to the test conditions, test process and test results. Among them, the test conditions include the frequency range of the signal generator, the real-time field strength and environmental parameters (temperature, humidity) of the test area, etc.; the test process includes equipment configuration, specific test steps and data collection methods, etc.; the test results include test data, performance and analysis results, etc.

[0117] Furthermore, before collecting the test data of the flight control system components, it also includes:

[0118] Monitor the field strength in the test area through field strength monitoring equipment to obtain field strength monitoring results;

[0119] The signal generator and power amplifier are adjusted according to the preset test field strength and the field strength monitoring results to ensure that the field strength in the test area is stably maintained at the preset test field strength.

[0120] The above-mentioned field strength monitoring device may be a field strength probe, and specifically, the field strength of the test area may be monitored by cooperating with a plurality of field strength probes arranged in the test area.

[0121] Specifically, when the high-intensity radiation field test is performed on the first test assembly, the second test assembly, and the third test assembly, it should be noted that:

[0122] When performing a high-intensity radiation field test on the first test component, amplifying the radio frequency signal to a first preset value through the power amplifier;

[0123] When performing a high-intensity radiation field test on the second test component, amplifying the radio frequency signal to a second preset value through the power amplifier;

[0124] When performing a high-intensity radiation field test on the third test component, amplifying the radio frequency signal to a third preset value through the power amplifier;

[0125] The first preset value is smaller than the second preset value, and the second preset value is smaller than the third preset value.

[0126] By limiting the sizes of the first preset value, the second preset value and the third preset value as described above, it is ensured that when the high-intensity radiation field test is performed on the first test component, the second test component and the third test component in sequence, the intensity of the high-intensity radiation field formed in the electromagnetic reverberation chamber increases in sequence.

[0127] In one embodiment, covering the first test component with a shielding net in step S105 may include the following steps:

[0128] Covering the first test component with a shielding net, with the edge of the shielding net in contact with the ground of the electromagnetic reverberation chamber, to ensure that the shielding net completely covers the first test component;

[0129] The edge of the shielding net is folded to form a folded portion at the edge of the shielding net, and the folded portion and the edge of the shielding net can be fixed by using a conductive stitching line.

[0130] The above steps can prevent electromagnetic waves from entering or escaping through the tiny gaps at the edge of the shielding net, thereby improving the shielding effect of the shielding net on the first test component.

[0131] Furthermore, after the shielding net is covered on the first test component, the shielding net and the first test component can be fixed with conductive tape to prevent the shielding net from shifting relative to the first test component.

[0132] It should be noted that, in this embodiment, the operation steps of covering the second test component with the shielding net are the same as the above-mentioned steps of covering the first test component with the shielding net, and will not be repeated here.

[0133] In one embodiment, in combination with the specific steps of the above high-intensity radiation field test, how to perform a high-intensity radiation field test on the first test component located in the shielding area may include the following steps:

[0134] Generate a radio frequency signal using a signal generator;

[0135] amplifying the radio frequency signal to a first preset value through a power amplifier;

[0136] Monitor the field strength in the test area through field strength monitoring equipment to obtain field strength monitoring results;

[0137] Adjusting the signal generator and the power amplifier according to the first preset test field strength and the field strength monitoring result to ensure that the field strength in the test area is stably maintained at the first preset test field strength;

[0138] The test data of the first test component is collected, and the performance of the first test component is analyzed based on the test data to obtain an analysis result of the first test component.

[0139] In one embodiment, in combination with the specific steps of the above high-intensity radiation field test, refer to Figure 3 As shown in FIG. 1 , it is described how to perform a high-intensity radiation field test on a second test assembly located in a semi-exposed area, which may include the following steps:

[0140] A first test component covering a shielding area with a shielding net;

[0141] Generate a radio frequency signal using a signal generator;

[0142] amplifying the radio frequency signal to a second preset value through a power amplifier;

[0143] Monitor the field strength in the test area through field strength monitoring equipment to obtain field strength monitoring results;

[0144] Adjusting the signal generator and the power amplifier according to the second preset test field strength and the field strength monitoring result to ensure that the field strength in the test area is stably maintained at the second preset test field strength;

[0145] The test data of the second test component is collected, and the performance of the second test component is analyzed based on the test data to obtain the analysis result of the second test component.

[0146] In one embodiment, in combination with the specific steps of the above high-intensity radiation field test, refer to Figure 4 As shown in FIG. 1 , it is described how to perform a high-intensity radiation field test on a third test assembly located in an exposure area, which may include the following steps:

[0147] Using a shielding net to cover the first test component in the shielding area and the second test component in the semi-exposed area;

[0148] Generate a radio frequency signal using a signal generator;

[0149] amplifying the radio frequency signal to a third preset value through a power amplifier;

[0150] Monitor the field strength in the test area through field strength monitoring equipment to obtain field strength monitoring results;

[0151] adjusting the signal generator and the power amplifier according to the third preset test field strength and the field strength monitoring result to ensure that the field strength in the test area is stably maintained at the third preset test field strength;

[0152] Test data of the third test component is collected, and performance of the third test component is analyzed based on the test data to obtain an analysis result of the third test component.

[0153] Specifically, the shielding effectiveness of the shielding net in this embodiment satisfies formula (2):

[0154] (2)

[0155] in, is the frequency of the electromagnetic wave, is the thickness of the shielding mesh, is the relative magnetic permeability of the shielding net, is the relative conductivity of the shielding mesh, is the offset constant, It is the shielding effectiveness of the shielding net.

[0156] The offset constant in the above formula (2) reflects the additional shielding effect of the shielding net in practical applications. The offset constant takes into account the influence of multiple reflections, absorption and other practical factors on the shielding effectiveness.

[0157] It is understood that the shielding effectiveness of the shielding net is related to the frequency of the electromagnetic wave, the thickness of the shielding net, the relative magnetic permeability of the shielding net and the relative electrical conductivity of the shielding net. Increasing the thickness will improve the shielding effectiveness, reflecting the fact that high-frequency electromagnetic waves are more easily shielded by the shielding net. Increasing the shielding efficiency will also increase the weight and cost of the shielding net. Relative conductivity of the shielding net The ratio reflects the shielding net's material's ability to absorb and reflect electromagnetic waves. The smaller the ratio, the higher the shielding effectiveness of the shielding net.

[0158] Optionally, the shielding effectiveness of the shielding net in this embodiment is not less than 20dB.

[0159] Optionally, the shielding net in this embodiment is made of a metal material. For example, the material of the shielding net can be copper, specifically copper with a purity of not less than 99.9%. Since copper has excellent electrical conductivity and thermal conductivity and is relatively low in cost, the use of high-purity copper as the material for making the shielding net can not only ensure the electrical conductivity of the shielding net, but also enhance the anti-oxidation ability of the shielding net, which is conducive to extending the service life of the shielding net.

[0160] It should be noted that, since conductive materials have good reflection and absorption effects on high-frequency electromagnetic waves, the conductivity of the shielding net will affect the shielding effect of the shielding net against electromagnetic interference. A shielding net with good conductivity can reduce the probability of high-frequency electromagnetic waves passing through the shielding net. It should also be noted that the shielding net can form a structure similar to a Faraday cage through its conductive properties, thereby protecting the equipment covered by the shielding net from interference from external electromagnetic fields. In this embodiment, the shielding net fully covers the flight control system components that need to be covered, and selects copper with good conductive properties as the manufacturing material of the shielding net, which can provide a good shielding effect for the covered flight control system components.

[0161] Optionally, the mesh density of the shielding net in this embodiment is not less than 120 meshes, and 120 meshes means that there are 120 meshes per inch of the shielding net.

[0162] Furthermore, in this exemplary embodiment, a flight control system multi-level high-intensity radiation field test system is also provided, and the test system is applied to the above-mentioned flight control system multi-level high-intensity radiation field test method, and the test system includes:

[0163] Electromagnetic reverberation chamber, used to provide a test area;

[0164] A signal generator, used for generating a radio frequency signal;

[0165] A power amplifier, used to amplify the radio frequency signal to a preset value;

[0166] Shielding net, used to cover the flight control system components;

[0167] Field strength monitoring equipment, used to monitor the field strength in the test area;

[0168] Data acquisition system, used to collect test data of flight control system components;

[0169] The data analysis system is used to analyze the performance of flight control system components based on test data and obtain analysis results.

[0170] The multi-level high-intensity radiation field test system of the flight control system can provide a stable test environment for high-intensity radiation field testing of flight control system components.

[0171] In one embodiment, the electromagnetic reverberation chamber is equipped with a stirrer and multiple antennas to ensure a uniform field strength distribution in the test area. It is understandable that the size of the electromagnetic reverberation chamber can be selected according to the size of the flight control system component being tested and the specific test requirements.

[0172] In one embodiment, the signal generator is used to generate a radio frequency signal in the frequency band of 100 MHz-18 GHz. The signal generator may be a high-performance signal generator such as Keysight N5173B or Rohde & Schwarz SMB100A. These types of signal generators have the characteristics of wide bandwidth, low phase noise and high output power, and can meet the frequency coverage requirements of the test.

[0173] In one embodiment, the power amplifier is used to amplify the radio frequency signal to a preset value. The power amplifier may be a broadband power amplifier to ensure that a high-intensity radiation field that meets the test standard can be formed in the electromagnetic reverberation chamber.

[0174] In one embodiment, the shielding net is used to cover flight control system components, and specifically can be used to cover flight control system components with lower radiation test level requirements, so as to electromagnetically shield the covered flight control system components and prevent them from affecting multi-level high-intensity radiation field testing of the flight control system components.

[0175] In one embodiment, the field strength monitoring device is used to monitor the field strength in the test area. The field strength monitoring device can specifically use broadband field strength probes such as Narda NBM series or AR FL7000 series, which have high sensitivity to ensure accurate monitoring.

[0176] In one embodiment, the data acquisition system is used to collect test data of flight control system components in a high-intensity radiation field test.

[0177] In one embodiment, the data analysis system is used to analyze the performance of the flight control system components based on the test data to obtain analysis results, thereby evaluating the response and performance of the flight control system components. The data analysis system may recommend the use of professional data analysis software, such as MATLAB, which has powerful data processing and visualization functions.

[0178] In one embodiment, in order to improve the overall performance and reliability of the multi-level high-intensity radiation field test system of the flight control system, it is recommended to integrate automatic control and monitoring functions into the system. For example, the signal generator, power amplifier and data acquisition system can be coordinated through a central controller to execute a preset test sequence.

[0179] This embodiment integrates a variety of high-performance test equipment to build a comprehensive, accurate and efficient flight control system multi-level high-intensity radiation field test system, which can not only simulate a complex high-intensity radiation field test environment, but also monitor the field strength distribution in real time, and efficiently collect and analyze test data. Through the flight control system multi-level high-intensity radiation field test system of this embodiment, the performance of flight control system components in various electromagnetic environments can be comprehensively evaluated, providing reliable data support for the electromagnetic compatibility design and optimization of the flight control system, thereby improving the overall reliability of the flight control system.

[0180] Those skilled in the art will readily appreciate other embodiments of the present application after considering the specification and practicing the invention disclosed herein. The present application is intended to cover any modification, use or adaptation of the present application, which follows the general principles of the present application and includes common knowledge or customary technical means in the art that are not disclosed in the present application.

Claims

1. A multi-level high-intensity radiation field testing method for a flight control system, characterized in that: include: According to the aircraft structure diagram and radiation test level, the flight control system components are divided into the first test component, the second test component and the third test component; Calibrate the equipment in the electromagnetic reverberation chamber so that the field strength of the electromagnetic reverberation chamber reaches a preset calibration field strength; Arranging the first test assembly, the second test assembly and the third test assembly in a test area of ​​the electromagnetic reverberation chamber; performing a high-intensity radiation field test on the first test assembly; Covering the first test assembly with a shielding net, and performing a high-intensity radiation field test on the second test assembly; Covering the first test assembly and the second test assembly with a shielding net, and performing a high-intensity radiation field test on the third test assembly; Wherein, the radiation test level of the third test component is higher than the radiation test level of the second test component, and the radiation test level of the second test component is higher than the radiation test level of the first test component; The test area includes a shielding area, a semi-exposed area and an exposed area; Arranging the first test assembly, the second test assembly, and the third test assembly in a test area of ​​the electromagnetic reverberation chamber includes: Arrange the first test component in the shielding area, arrange the second test component in the semi-exposed area, and arrange the third test component in the exposed area; Laying connecting cables in the test area, and connecting the first test component, the second test component, and the third test component to each other through the connecting cables; The shielding effectiveness of the shielding net satisfies formula (2): （2） in, is the frequency of the electromagnetic wave, is the thickness of the shielding mesh, is the relative magnetic permeability of the shielding net, is the relative conductivity of the shielding mesh, is the offset constant, It is the shielding effectiveness of the shielding net.

2. The flight control system multi-level high-intensity radiation field testing method according to claim 1 is characterized in that: The equipment in the calibration electromagnetic reverberation chamber includes: Selecting a plurality of measuring points within the test area; Measuring the field strength at a plurality of the measuring points to obtain a plurality of measured field strengths; Calculate an average field strength based on the multiple measured field strengths to obtain an actual field strength in the test area; According to the preset calibration field strength and the actual field strength, the equipment in the electromagnetic reverberation chamber is adjusted until the actual field strength reaches the preset calibration field strength.

3. The flight control system multi-level high-intensity radiation field testing method according to claim 2 is characterized in that: The equipment for calibrating the electromagnetic reverberation chamber also includes: The field strength standard deviation is calculated based on the average field strength and the plurality of measured field strengths, and the calculation formula of the field strength standard deviation is: （1） in, For the The measured field strength at each measuring point is is the average field strength, is the number of measurement points, is the standard deviation; The equipment in the electromagnetic reverberation chamber is adjusted according to the field strength standard deviation until the field strength standard deviation reaches a preset standard deviation threshold.

4. The flight control system multi-level high-intensity radiation field testing method according to claim 1, characterized in that: The step of arranging the first test assembly, the second test assembly and the third test assembly in a test area of ​​the electromagnetic reverberation chamber further includes: Calibrate the layout distances among the first test component, the second test component and the third test component.

5. The flight control system multi-level high-intensity radiation field testing method according to claim 1, characterized in that: The high-intensity radiation field test includes: Generate a radio frequency signal using a signal generator; amplifying the radio frequency signal to a preset value through a power amplifier; The test data of the flight control system components are collected, and the performance of the flight control system components is analyzed based on the test data to obtain analysis results.

6. The flight control system multi-level high-intensity radiation field testing method according to claim 5, characterized in that: When performing a high-intensity radiation field test on the first test component, amplifying the radio frequency signal to a first preset value through the power amplifier; When performing a high-intensity radiation field test on the second test component, amplifying the radio frequency signal to a second preset value through the power amplifier; When performing a high-intensity radiation field test on the third test component, amplifying the radio frequency signal to a third preset value through the power amplifier; The first preset value is smaller than the second preset value, and the second preset value is smaller than the third preset value.

7. The flight control system multi-level high-intensity radiation field testing method according to claim 5, characterized in that: Before collecting the test data of the flight control system components, the method further includes: Monitor the field strength of the test area by using a field strength monitoring device to obtain a field strength monitoring result; The signal generator and the power amplifier are adjusted according to the preset test field strength and the field strength monitoring result.

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