A high-intensity radiation field whole machine low-level scanning field extrapolation verification system and verification method

Abstract

The invention relates to the technical field of electromagnetic environmental effects, and discloses a high-intensity radiation field whole machine low-level scanning field extrapolation verification system and a verification method. The verification method comprises the following steps: building a whole machine HIRF high-level scanning field test system under the same test site requirements as the whole machine HIRF-LLSF test, the whole machine HIRF high-level scanning field test system comprises adopting an HPM system to simulate a narrowband high-level HIRF radiation source, keeping the distance between a transmitting antenna and a test object the same as that in the whole machine HIRF-LLSF test, and placing a receiving antenna or a field strength probe in the same position as that in the whole machine HIRF-LLSF test; the invention can solve the technical difficulties of whole machine HIRF high-level scanning field calibration and cabin coupling field precise synchronous measurement and the problem that the accuracy of extrapolation of whole machine HIRF-LLSF test results needs to be verified, and provides a test means for aircraft HIRF protection design and safety evaluation.

Description

Technical Field

[0001] The present invention relates to the field of electromagnetic environment effects, and more specifically, to a high-intensity radiation field whole machine low-level scanning field extrapolation verification system and verification method. Background Art

[0002] High-intensity radiated field (HIRF) refers to the electromagnetic environment that civil aircraft may encounter under current flight rules, which is generated by radiation from ship radar, airport surveillance radar, AM and FM radio stations, VHF TV transmitters, mobile communication base stations, etc. HIRF is caused by human activities, and its frequency range is as high as 10kHz to 40GHz, which affects the safety of aircraft. HIRF protection test verification is a rigid requirement for the airworthiness of civil aircraft.

[0003] With the continuous development of modern aviation technology, on the one hand, traditional mechanical control systems have been largely replaced by highly integrated electronic control systems, which has greatly increased the sensitivity of electronic and electrical systems; on the other hand, the widespread use of composite materials with low electromagnetic shielding performance and the increasingly complex and changeable electromagnetic environment have led to a more severe cabin electromagnetic environment, and the HIRF environment poses an increasingly severe threat to the flight safety of civil aircraft. The HIRF airworthiness verification of civil aircraft is based on the linear extrapolation of the low-level test results of the whole aircraft to the high-level environment, obtaining the HIRF coupling field strength of the cabin where the electronic and electrical system is located, and conducting airworthiness compliance review based on the radiation sensitivity of the electronic and electrical system. There has been no research at home and abroad on the consistency between the coupling field strength in the cabin under the high-level HIRF environment and the coupling field strength under the high-level environment from the linear extrapolation of the low-level test results of the whole aircraft to the high-level environment, to verify the accuracy of the linear extrapolation of the low-level scanning field (LLSF) test. Summary of the invention

[0004] The present invention provides a high-intensity radiation field whole machine low-level scanning field extrapolation verification system and verification method, which solve the technical problems raised in the above background technology.

[0005] The present invention provides a method for extrapolating and verifying a low-level scanning field of a whole machine in a high-intensity radiation field, comprising the following steps:

[0006] Step S1, building a whole machine HIRF high level scanning field test system according to the same test site requirements as the whole machine HIRF-LLSF test, the whole machine HIRF high level scanning field test system includes using an HPM system to simulate a narrowband high level HIRF radiation source, keeping the distance between the transmitting antenna and the test object the same as that of the whole machine HIRF-LLSF test, and placing the receiving antenna or field strength probe in the same position as that of the whole machine HIRF-LLSF test;

[0007] Step S2, when there is no test object, the whole machine HIRF high level scanning field calibration is performed, and the HPM transmission power is controlled so that the center position of the test area reaches the whole machine HIRF high level scanning field test field strength requirement;

[0008] Step S3, aiming the main beam of the transmitting antenna at the test area, irradiating the test area at the required irradiation angle under horizontal and vertical polarization respectively, the cabin of the test area is divided and specified by the tester according to the test task requirements;

[0009] Step S4, irradiating the cabin in the test area with the whole machine HIRF high-level scanning field calibration power, and collecting the internal coupling field signal of the cabin in the test area with the receiving antenna;

[0010] Step S5, comparing the cabin internal coupling field obtained from the whole machine HIRF high electric scanning field test with the whole machine HIRF-LLSF linear extrapolation value, and analyzing and evaluating the accuracy of the linear extrapolation of the whole machine HIRF-LLSF test.

[0011] In a preferred embodiment, the HPM system is a complete HIRF high-level scanning field emission subsystem.

[0012] In a preferred embodiment, a narrowband high-level radiation field measurement subsystem is used to perform high-level radiation field calibration and precise synchronous measurement of the coupling field in the cabin.

[0013] In a preferred embodiment, the method for analyzing the accuracy of the extrapolation of the whole machine LLSF test data includes obtaining test data under different irradiation directions and polarization modes and comparing them with the extrapolated values ​​of the test data under the corresponding irradiation directions and polarization modes of the whole machine LLSF test.

[0014] A high-intensity radiation field whole machine low-level scanning field extrapolation verification system, comprising a control unit, a high-power radiation unit, a receiving unit, a signal transmission unit, and a signal processing unit;

[0015] A control unit, used for controlling the transmission of HPM signals and analyzing received signals;

[0016] A high-power radiation unit is a device for generating a high-power radio frequency signal output to irradiate the aircraft fuselage;

[0017] A receiving unit, including a receiving antenna and an attenuator, for receiving the field strength inside the test aircraft cabin;

[0018] A signal transmission unit, used for transmitting the received signal to the signal processing system;

[0019] The signal processing unit converts the received electrical signal into a digital signal.

[0020] In a preferred embodiment, the control unit includes a control system, which is composed of a computer and test automation control software. The control system controls the radiation source through a data line, and is used to read data from an oscilloscope and analyze the results.

[0021] In a preferred embodiment, the high-power radiation unit includes a narrowband HPM analog source, a coupler and a transmitting antenna;

[0022] Narrowband HPM analog source for generating high-power RF signals;

[0023] A coupler is connected to the reference trigger channel of the oscilloscope through a radio frequency cable. The coupler is used to extract the transmission signal of the transmitting antenna as a reference trigger signal. The reference trigger signal is transmitted to the oscilloscope through the radio frequency cable. The oscilloscope displays the transmission signal and the receiving signal at the same time. The reference trigger signal is used to synchronize the display so as to compare and analyze the difference between the transmission signal and the receiving signal.

[0024] Transmitting antenna, a transmitting device used to convert high-power radio frequency signals into space-radiated electromagnetic fields, and to form a transmitting link with a narrowband HPM simulation source HPM through a radio frequency cable;

[0025] The transmitting antenna height is the same as the height of the area of ​​interest in the center of the aircraft cabin.

[0026] In a preferred embodiment, the receiving unit includes a receiving antenna and an attenuator;

[0027] A receiving antenna is used to collect the coupling field strength in the aircraft cabin, and the receiving antenna is placed in the aircraft cabin;

[0028] Attenuator, which is placed in the aircraft cabin and connected to the receiving antenna, is used to prevent the receiving field strength from being too strong to damage the optical converter;

[0029] The signal transmission unit includes an optical remote end unit, an optical fiber link and an optical near end unit;

[0030] An optical remote terminal is placed in the aircraft cabin and is used to convert the received field strength electrical signal into an optical signal;

[0031] Fiber optic link, optical signal transmission over long distances, without interference and with low loss;

[0032] The optical near-end machine is placed in the control room and connected to the measuring probe of the oscilloscope. The optical near-end machine is used to convert the optical signal of the optical fiber link into an electrical signal and transmit it to the oscilloscope for processing;

[0033] The signal processing unit block includes an oscilloscope;

[0034] An oscilloscope is used to couple the transmitted signal and the received signal and compare and analyze the difference between the transmitted signal and the received signal.

[0035] The beneficial effects of the present invention are:

[0036] 1. The present invention can solve the technical difficulties of calibrating the whole aircraft HIRF high-level scanning field and accurately synchronizing the cabin coupling field, and the problem of the accuracy of extrapolating the test results of the whole aircraft HIRF-LLSF test to be verified, and provide a test method for the protection design and safety assessment of aircraft HIRF;

[0037] 2. The present invention adopts the existing mature high-power microwave technology to construct a narrow-band high-level radiation source, thereby solving the problem of high-level HIRF narrow-band scanning field test verification of the whole machine at a low cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 It is the first flow chart of the verification method of the present invention.

[0039] Figure 2 It is a system calibration arrangement diagram of the verification system of the present invention.

[0040] Figure 3 It is a system test layout diagram of the verification system of the present invention.

[0041] In the figure: 101, narrowband HPM simulation source; 102, coupler; 103, transmitting antenna; 201, receiving antenna; 202, attenuator; 203, optical remote end; 204, optical fiber link; 205, optical near end; 301, oscilloscope; 302, control system; 303, data line; 401, aircraft cabin; 501, RF cable. DETAILED DESCRIPTION

[0042] The subject matter described herein will now be discussed with reference to example embodiments. It should be understood that the discussion of these embodiments is only to enable those skilled in the art to better understand and implement the subject matter described herein, and the functions and arrangements of the elements discussed may be changed without departing from the scope of protection of the contents of this specification. Each example may omit, replace or add various processes or components as needed. In addition, the features described relative to some examples may also be combined in other examples.

[0043] like Figure 1 As shown, a method for extrapolating and verifying a low-level scanning field of a whole machine in a high-intensity radiation field comprises the following steps:

[0044] Step S1, building a whole-machine HIRF high-level scanning field test system according to the same test site requirements as the whole-machine HIRF-LLSF test, the whole-machine HIRF high-level scanning field test system includes using an HPM system to simulate a narrow-band high-level HIRF radiation source, keeping the test distance between the transmitting antenna and the aircraft the same as that of the whole-machine HIRF-LLSF test, and placing the receiving antenna or field strength probe in the same position as that of the whole-machine HIRF-LLSF test;

[0045] Step S2, when there is no test object, the whole machine HIRF high level scanning field calibration is performed, and the HPM transmission power is controlled so that the center position of the test area reaches the whole machine HIRF high level scanning field test field strength requirement;

[0046] Step S3, aiming the main beam of the transmitting antenna at the test area, irradiating the test area at the required irradiation angle under horizontal and vertical polarization respectively, the cabin of the test area is divided and specified by the tester according to the test task requirements;

[0047] It should be noted that the test area where the main lobe of the transmitting antenna is aimed refers to the specific area where the main lobe of the transmitting antenna (i.e. the direction of the strongest radiation) points during the test. This test area is usually the place where the tester wants to focus on research or monitoring, usually the area where important equipment on the aircraft is located;

[0048] It should be further explained that the transmitting antenna also includes all the illumination angles and polarizations. During the test, the transmitting antenna not only points to the test area, but also illuminates the area at different angles and in different polarizations. The purpose of this design is to simulate various radiation conditions that may be encountered in actual operation, ensuring that the test can fully cover different scenarios;

[0049] The transmitting antenna includes all the illumination angles. The illumination angle refers to the direction of the transmitting antenna relative to the object being measured. It can be horizontal, vertical, or any angle in between.

[0050] In HIRF testing, it is usually necessary to consider multiple different irradiation angles to evaluate the impact of radiation from different directions on the aircraft, such as:

[0051] Horizontal irradiation: The transmitting antenna irradiates the aircraft in the horizontal direction, simulating the aircraft being irradiated by HIRF in the horizontal direction;

[0052] Vertical irradiation: The transmitting antenna irradiates the aircraft in the vertical direction, simulating the aircraft being irradiated by HIRF from the vertical direction;

[0053] Oblique upward irradiation: The transmitting antenna irradiates the aircraft obliquely upward at a certain angle to simulate the radiation exposure of the aircraft in a specific flight attitude;

[0054] Oblique downward irradiation: The transmitting antenna irradiates the aircraft obliquely downward at a certain angle to simulate the radiation exposure of the aircraft in a specific flight attitude;

[0055] The transmitting antenna contains all polarization modes. Polarization refers to the direction in which the electric field vector of the electromagnetic wave changes over time.

[0056] In the test, it is usually necessary to consider horizontal polarization and vertical polarization, and sometimes other polarization modes such as circular polarization or elliptical polarization are also considered. The purpose of this design is to simulate the impact of radiation sources with different polarizations on the aircraft, for example:

[0057] Horizontal polarization: The electric field vector of the electromagnetic wave generated by the transmitting antenna vibrates in the horizontal direction;

[0058] Vertical polarization: The electric field vector of the electromagnetic wave generated by the transmitting antenna vibrates in the vertical direction;

[0059] Right-hand circular polarization: The electric field vector of the electromagnetic wave generated by the transmitting antenna rotates in a clockwise direction;

[0060] Left-hand circular polarization: The electric field vector of the electromagnetic wave generated by the transmitting antenna rotates in a counterclockwise direction;

[0061] Elliptical polarization: The electric field vector of the electromagnetic wave generated by the transmitting antenna vibrates along an elliptical trajectory;

[0062] Examples of combined illumination angles and polarizations:

[0063] Horizontal irradiation + horizontal polarization: The transmitting antenna irradiates the aircraft in the horizontal direction, and the electric field vector of the electromagnetic wave is also in the horizontal direction;

[0064] Vertical irradiation + vertical polarization: The transmitting antenna irradiates the aircraft in the vertical direction, and the electric field vector of the electromagnetic wave is also in the vertical direction;

[0065] Oblique upward illumination + right-hand circular polarization: The transmitting antenna illuminates the aircraft obliquely upward at a certain angle, and the electric field vector of the electromagnetic wave rotates in a clockwise direction;

[0066] Oblique downward illumination + left-hand circular polarization: The transmitting antenna illuminates the aircraft obliquely downward at a certain angle, and the electric field vector of the electromagnetic wave rotates in a counterclockwise direction;

[0067] Through the combination of these different irradiation angles and polarization modes, the response of the aircraft under different radiation conditions can be more comprehensively evaluated, thus ensuring the effectiveness and comprehensiveness of the HIRF test.

[0068] Step S4, irradiating the cabin in the test area with the whole machine HIRF high-level scanning field calibration power, and collecting the internal coupling field signal of the cabin in the test area with the receiving antenna;

[0069] Step S5, comparing the cabin internal coupling field obtained by the whole machine HIRF high electric scanning field test with the whole machine HIRF-LLSF linear extrapolation value, and analyzing and evaluating the accuracy of the whole machine HIRF-LLSF test linear extrapolation;

[0070] Each time an aircraft’s high-intensity radiation field effect safety assessment is conducted, the aircraft must be pulled out of storage or maintenance locations for detailed testing and evaluation. This process is not only time-consuming and labor-intensive, but also requires professional technicians and advanced testing equipment to complete.

[0071] In one embodiment of the present invention, in order to solve the above problem, a method for extrapolating and verifying a low-level scanning field of a whole machine in a high-intensity radiation field is provided, comprising the following steps:

[0072] Step S201, collecting historical test data, the historical test data including structural parameters of the aircraft and field strength measurement data, the structural parameters of the aircraft including materials, shape, size, position coordinates and component connection relationship, the field strength measurement data including the frequency of the radiation source, the power of the radiation source, the polarization direction of the radiation source, the incident angle of the radiation source, the aircraft attitude and environmental parameters;

[0073] It should be noted that the materials include aluminum alloy, carbon fiber composite materials, etc., the shapes include cuboid, cylinder, etc., the dimensions include the length, width and height of the components, the component connection relationship includes the connection mode and position relationship between the components of the test aircraft, the polarization direction of the radiation source includes horizontal and vertical, the incident angle of the radiation source indicates the angle at which the radiation reaches the surface of the test aircraft, the aircraft attitude includes the aircraft's pitch angle, roll angle, and yaw angle, the position coordinates include the aircraft's geographical coordinates or the position relative to the radiation source, and the environmental parameters include atmospheric conditions, humidity, and temperature;

[0074] It should be further noted that historical test data can be obtained from previous HIRF test reports, electromagnetic simulation software output, and laboratory tests.

[0075] Step S202, constructing a test aircraft graph structure according to historical test data;

[0076] Each node represents a component on the aircraft; the corresponding node feature represents the material, shape, size and position coordinates of the component;

[0077] The condition that there is an edge between two nodes indicates that the components corresponding to the two nodes are connected; the corresponding edge feature indicates the connection type and connection strength connecting the two nodes;

[0078] The global attributes include the overall attributes of the test aircraft, which include the total length, wingspan, height, total volume, weight and aircraft attitude of the test aircraft, where the aircraft attitude is represented by pitch angle, roll angle and yaw angle;

[0079] It should be noted that before constructing the test aircraft graph structure, the collected historical test data needs to be encoded, for example, material type: encoded using methods such as one-hot encoding or embedded encoding, geometric shape: encoded using the one-hot encoding method, position coordinates: can be kept as is or standardized, test the global properties of the aircraft graph structure, aircraft attitude: the pitch angle, roll angle, and yaw angle can be converted into radians for mathematical calculations, environmental parameters: such as atmospheric conditions, humidity, temperature, etc., can be kept as is or standardized.

[0080] Step S203, inputting the aircraft map structure data into the field strength prediction model, and the field strength prediction model outputs the coupling field strength corresponding to each node inside the antenna acquisition cabin;

[0081] The field strength prediction model includes a linear layer, a first hidden layer, a second hidden layer, and a fully connected layer, wherein the linear layer inputs an input feature matrix composed of all node features, outputs an intermediate feature matrix to the first hidden layer, the first hidden layer outputs a first updated intermediate feature matrix to the second hidden layer, the second hidden layer outputs a second updated intermediate feature matrix to the fully connected layer, and the fully connected layer outputs the coupled field strength inside the antenna collection cabin;

[0082] Linear Layer:

[0083] For each node There are corresponding node feature vectors , all node feature vectors in the aircraft graph structure data constitute the input feature matrix , the input feature matrix is ​​input into the linear layer, and the linear layer outputs the intermediate feature matrix ;

[0084] First hidden layer:

[0085] Input intermediate feature matrix , output the first updated intermediate feature matrix;

[0086] The calculation formula for the first hidden layer is:

[0087]

[0088]

[0089] in, represents the first updated intermediate feature matrix, represents the number of nodes, represents the attention weight coefficient vector of node v in the first hidden layer, represents the linear transformation parameters of the first hidden layer; Representation Node The set of neighbor nodes of represents vector concatenation, , are the first and second weight matrices respectively, Representation Node The node feature vector of Representation Node The set of neighbor nodes The feature matrix of all nodes in , Each row of corresponds to the feature vector of a neighbor node;

[0090] Second hidden layer:

[0091] Input a first updated intermediate feature matrix, and output a second updated intermediate feature matrix;

[0092] The calculation formula for the second hidden layer is:

[0093]

[0094] in, represents the second updated intermediate feature matrix, represents the weight matrix of the second hidden layer, represents the first updated intermediate feature matrix, represents the bias vector of the second hidden layer, represents the softmax function;

[0095] Fully connected layer:

[0096] Input the second updated intermediate characteristic matrix and output the coupling field strength inside the antenna acquisition cabin;

[0097] The calculation formula of the fully connected layer is:

[0098]

[0099] in, Indicates the coupling field strength corresponding to each node inside the antenna collection cabin, represents the second updated intermediate feature matrix, represents the weight matrix of the fully connected layer, represents the bias vector of the fully connected layer, represents the softmax function;

[0100] In one embodiment of the present invention, the coupling field strength corresponding to each node inside the antenna collection cabin represents the radiation source's ability to isolate and weaken radiation of different components on the test aircraft at different incident angles, which is used to evaluate whether different components of the test aircraft meet safety requirements.

[0101] It should be noted that the training data of the field strength prediction model uses the historical test data collected in step 101 as training data, and the label data of the training process is the internal coupling field strength of the cabin under different conditions. The parameters of the field strength prediction model are adjusted by the back propagation method to minimize the gap between the predicted value and the actual value.

[0102] Step S204, compare the internal coupling field strength of the antenna acquisition cabin output by the field strength prediction model with the threshold value. If it is lower than the threshold value, the test aircraft is tested according to steps S1 to S5 to obtain the final test results. The test results include compliance with safety standards and non-compliance with safety standards. If it is higher than the threshold value, it means that the test aircraft does not meet the safety standards and no test is required.

[0103] It should be noted that the threshold value is determined according to the specific HIRF protection design requirements and relevant standards, and the determined threshold value is compared with the predicted coupling field strength inside the antenna collection cabin, and the result of each evaluation is recorded.

[0104] The present invention predicts the internal coupling field strength of the test aircraft under different HIRF conditions by training the field strength prediction model, which can reduce the need for actual testing, save time and cost, quickly evaluate the effects of different design schemes, and accelerate the iterative process of HIRF protection design. The model can simulate the coupling field strength under a variety of test conditions and provide a more comprehensive safety assessment basis. By implementing the above technical solution, the problem that the aircraft needs to be pulled out for test and assessment every time the safety of the high-intensity radiation field effect of the aircraft is assessed can be effectively solved, thereby improving the efficiency and reliability of HIRF protection design and safety assessment.

[0105] A high-intensity radiation field whole machine low-level scanning field extrapolation verification system, comprising a control unit, a high-power radiation unit, a receiving unit, a signal transmission unit, and a signal processing unit;

[0106] A control unit, used for controlling the transmission of HPM signals and analyzing received signals;

[0107] A high-power radiation unit is a device for generating a high-power radio frequency signal output to irradiate the aircraft fuselage;

[0108] A receiving unit, including a receiving antenna and an attenuator, for receiving the field strength inside the test aircraft cabin;

[0109] A signal transmission unit, used for transmitting the received signal to the signal processing system;

[0110] A signal processing unit converts the received electrical signal into a digital signal;

[0111] like Figure 2 and Figure 3As shown, in one embodiment of the present invention, the control unit includes a control system 302, which is mainly composed of a computer and test automation control software, and controls the radiation source through a data line 303, and is used to read the data of the oscilloscope 301 and analyze the results to complete the test;

[0112] The high power radiation unit includes a narrowband HPM simulation source 101, a coupler 102 and a transmitting antenna 103;

[0113] A narrowband HPM analog source 101, used to generate a high-power radio frequency signal;

[0114] The coupler 102 is connected to the reference trigger channel of the oscilloscope 301 through the radio frequency cable 501. The coupler 102 is used to extract the transmission signal of the transmission antenna 103 as the reference trigger signal. The reference trigger signal is transmitted to the oscilloscope 301 through the radio frequency cable 501. The oscilloscope 301 displays the transmission signal and the reception signal at the same time, and the reference trigger signal is used to synchronize the display, so as to compare and analyze the difference between the transmission signal and the reception signal.

[0115] Transmitting antenna 103, a transmitting device for converting high-power radio frequency signals into a space-radiated electromagnetic field, forming a transmitting link with the narrowband HPM simulation source 101 through a radio frequency cable;

[0116] The height of the transmitting antenna 103 is the same as the height of the central test area of ​​the aircraft cabin 401;

[0117] The receiving unit includes a receiving antenna 201 and an attenuator 202;

[0118] A receiving antenna 201 is used to collect coupling field strength in the aircraft cabin 401 , and the receiving antenna 201 is placed in the aircraft cabin 401 ;

[0119] Attenuator 202, the attenuator 202 is placed in the aircraft cabin 401, the attenuator 202 is connected to the receiving antenna 201, and the attenuator 202 is used to prevent the receiving field strength power from being too large to damage the optical converter;

[0120] The signal transmission unit includes an optical remote end 203, an optical fiber link 204 and an optical near end 205;

[0121] An optical remote terminal 203, which is placed in the aircraft cabin 401 and is used to convert the received field strength electrical signal into an optical signal;

[0122] Optical fiber link 204, optical signal transmission over long distances, without interference, and with low loss;

[0123] The optical near-end machine 205 is placed in the control room and connected to the measuring probe of the oscilloscope 301. The optical near-end machine 205 is used to convert the optical signal of the optical fiber link 204 into an electrical signal and transmit it to the oscilloscope for processing;

[0124] The signal processing unit block includes an oscilloscope 301;

[0125] The oscilloscope 301 is used to couple the transmission signal and the reception signal, and compare and analyze the difference between the transmission signal and the reception signal.

[0126] The specific operation steps of the above verification system are as follows:

[0127] See attached Figure 2 , field strength calibration steps:

[0128] 1) Select one of the antenna illumination angles to test and start calibration from the starting test frequency point;

[0129] 2) Setting the polarization direction (horizontal or vertical) of the transmitting antenna 103;

[0130] 3) Inject appropriate forward power into the test area at the test frequency point;

[0131] 4) Using a measuring receiver to measure the field strength level of the receiving antenna 201;

[0132] 5) Adjust the output power of the irradiation source. When the field strength level received from the receiving antenna 201 reaches the requirement and is output stably, record and store the forward power value at this time;

[0133] 6) Step to the next frequency point;

[0134] 7) Repeat the calibration process from 3) to 6) until the end frequency of the test;

[0135] 8) Repeat the calibration process from 2) to 7) until the calibration of both polarization directions is completed;

[0136] 9) The current test is ended, and the transmitting antenna 103 moves to the next transmitting position;

[0137] 10) Repeat steps 1) to 9) until all positions are calibrated.

[0138] See attached Figure 3 , Field strength test steps:

[0139] 1) Select one of the antenna radiation angles to test and start the test from the starting test frequency point;

[0140] 2) Setting the polarization direction (horizontal or vertical) of the transmitting antenna 103;

[0141] 3) Inject the calibrated recorded forward power into the test area at the test frequency point;

[0142] 4) measuring the electromagnetic field strength in the aircraft cabin 401 using a measuring receiver;

[0143] 5) Step to the next scanning frequency point (usually logarithmically spaced);

[0144] 6) Repeat steps 3) to 5) to complete all frequency point tests;

[0145] 7) Repeat the test process from 2) to 6) until the test of two polarization directions is completed;

[0146] 8) The current test is ended, and the transmitting antenna 103 moves to the next transmitting position;

[0147] 9) Repeat steps 1) to 8) to complete the entire test.

[0148] The verification system of the present invention adopts the existing mature high-power microwave HPM technology, which solves the problem that the high-level irradiation test of the whole machine can only be replaced by a low-level scanning field due to the limitation of the test equipment, and the accuracy of the test results needs to be verified.

[0149] The above describes an embodiment of the present embodiment, but the present embodiment is not limited to the above-mentioned specific implementation methods. The above-mentioned specific implementation methods are merely illustrative and not restrictive. Under the guidance of the present embodiment, ordinary technicians in this field can also make many forms, all of which are within the protection of the present embodiment.

Claims

1. A method for extrapolating and verifying low-level scanning fields of a whole machine in a high-intensity radiation field, characterized in that: The following steps are involved: Step S1, building a whole machine HIRF high level scanning field test system according to the same test site requirements as the whole machine HIRF-LLSF test, the whole machine HIRF high level scanning field test system includes using an HPM system to simulate a narrowband high level HIRF radiation source, keeping the distance between the transmitting antenna and the test object the same as that of the whole machine HIRF-LLSF test, and placing the receiving antenna or field strength probe in the same position as that of the whole machine HIRF-LLSF test; Step S2, when there is no test object, the whole machine HIRF high level scanning field calibration is performed, and the HPM transmission power is controlled so that the center position of the test area reaches the whole machine HIRF high level scanning field test field strength requirement; Step S3, aiming the main beam of the transmitting antenna at the test area, irradiating the test area at the required irradiation angle under horizontal and vertical polarization respectively, the cabin of the test area is divided and specified by the tester according to the test task requirements; Step S4, irradiating the cabin in the test area with the whole machine HIRF high-level scanning field calibration power, and collecting the internal coupling field signal of the cabin in the test area with the receiving antenna; Step S5, comparing the cabin internal coupling field obtained from the whole machine HIRF high electric scanning field test with the whole machine HIRF-LLSF linear extrapolation value, and analyzing and evaluating the accuracy of the linear extrapolation of the whole machine HIRF-LLSF test.

2. According to claim 1, a high-intensity radiation field whole machine low-level scanning field extrapolation verification method is characterized in that: The HPM system is the HIRF high-level scanning field emission subsystem of the whole machine.

3. The method for extrapolating and verifying a low-level scanning field of a whole machine with a high-intensity radiation field according to claim 2 is characterized in that: A narrowband high-level radiation field measurement subsystem is used to perform high-level radiation field calibration and precise synchronous measurement of the coupling field in the cabin.

4. The method for extrapolating and verifying a low-level scanning field of a whole machine in a high-intensity radiation field according to claim 3 is characterized in that: The method for analyzing the accuracy of the extrapolation of the whole machine LLSF test data includes obtaining the test data under different irradiation directions and polarization modes and comparing them with the extrapolated values ​​of the test data under the corresponding irradiation directions and polarization modes of the whole machine LLSF test.

5. A high-intensity radiation field whole machine low-level scanning field extrapolation verification system, which is used to execute the steps in the high-intensity radiation field whole machine low-level scanning field extrapolation verification method as claimed in claim 1, characterized in that: It includes a control unit, a high-power radiation unit, a receiving unit, a signal transmission unit, and a signal processing unit; A control unit, used for controlling the transmission of HPM signals and analyzing received signals; A high-power radiation unit is a device for generating a high-power radio frequency signal output to irradiate the aircraft fuselage; A receiving unit, including a receiving antenna and an attenuator, for receiving the field strength inside the test aircraft cabin; A signal transmission unit, used for transmitting the received signal to the signal processing system; The signal processing unit converts the received electrical signal into a digital signal.

6. A high-intensity radiation field whole machine low-level scanning field extrapolation verification system according to claim 5, characterized in that: The control unit includes a control system, which is composed of a computer and test automation control software. The control system controls the radiation source through a data line and is used to read data from an oscilloscope and perform result analysis.

7. A high-intensity radiation field whole machine low-level scanning field extrapolation verification system according to claim 6, characterized in that: The high-power radiation unit includes a narrowband HPM analog source, a coupler and a transmitting antenna; Narrowband HPM analog source for generating high-power RF signals; A coupler is connected to the reference trigger channel of the oscilloscope through a radio frequency cable. The coupler is used to extract the transmission signal of the transmitting antenna as a reference trigger signal. The reference trigger signal is transmitted to the oscilloscope through the radio frequency cable. The oscilloscope displays the transmission signal and the receiving signal at the same time. The reference trigger signal is used to synchronize the display so as to compare and analyze the difference between the transmission signal and the receiving signal. Transmitting antenna, a transmitting device used to convert high-power RF signals into space-radiated electromagnetic fields, forming a transmission link with a narrowband HPM simulation source through an RF cable; The transmitting antenna height is the same as the height of the test area in the center of the aircraft cabin.

8. The high-intensity radiation field whole machine low-level scanning field extrapolation verification system according to claim 7 is characterized in that: The receiving unit includes a receiving antenna and an attenuator; A receiving antenna is used to collect the coupling field strength in the aircraft cabin, and the receiving antenna is placed in the aircraft cabin; Attenuator, which is placed in the aircraft cabin and connected to the receiving antenna, is used to prevent the receiving field strength from being too strong to damage the optical converter; The signal transmission unit includes an optical remote end unit, an optical fiber link and an optical near end unit; An optical remote terminal is placed in the aircraft cabin and is used to convert the received field strength electrical signal into an optical signal; Fiber optic link, optical signal transmission over long distances, without interference and with low loss; The optical near-end machine is placed in the control room and connected to the measuring probe of the oscilloscope. The optical near-end machine is used to convert the optical signal of the optical fiber link into an electrical signal and transmit it to the oscilloscope for processing; The signal processing unit block includes an oscilloscope; An oscilloscope is used to couple the transmitted signal and the received signal and compare and analyze the difference between the transmitted signal and the received signal.

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