CN116699257A - High-intensity radiation field testing device of low-level scanning field and testing method thereof - Google Patents
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Abstract
The invention relates to the technical field of electromagnetic environmental effects, and discloses a high-intensity radiation field testing device and a testing method of a low-level scanning field, wherein the high-intensity radiation field testing method of the low-level scanning field comprises the steps of taking the position and the trend of a cable into consideration as the coordinate parameters of the cable, and generating an equivalent coefficient based on a trained coefficient model; according to the invention, the position and the trend of the cable are taken into consideration as the coordinate parameters of the cable on the basis of the equivalence of the existing irradiation method and DIC method, and the equivalent coefficients are generated in the trained coefficient model, so that the injection current required to be injected in the current test is obtained, the error between the calculated injection current and the actual injection current required to be applied is reduced, and the accuracy of the test result is improved.
Description
Technical Field
The invention relates to the field of electromagnetic environmental effects, in particular to a high-intensity radiation field testing device of a low-level scanning field and a testing method thereof.
Background
The energy of the high-intensity radiation field in the low frequency band of the airplane is directly coupled to the internal wiring harness of the airplane, so that the method for testing the scanning field in the high frequency band is not applicable; therefore, at present, a test method of directly injecting low-level scanning current is generally adopted to test the induced current of the cable in the aircraft, and the induced current of the cable in the aircraft is compared with a design threshold value of the cable to evaluate the safety shielding performance of the aircraft.
The specific HIRF environment is equivalent to the injection current on the aircraft body, which is called a direct current injection method (DCI method), simply, the relation between the field intensity of the irradiation method and the DCI injection current can be obtained by determining the transfer functions corresponding to the irradiation method and the DCI method, the applied injection current can be obtained based on the relation between the irradiation field intensity which is required to be simulated currently and the field intensity of the irradiation method and the DCI injection current, then the induction current of the cable in the aircraft model is measured and tested, and the safety shielding performance of the aircraft is evaluated.
However, in the DCI method, when the induced current of the internal cable is measured for the test aircraft, the position and trend of the cable tested in the test aircraft are different from those of the cable in the aircraft, for example, when the transfer function corresponding to the cable tested in the test aircraft is greater than the maximum transfer function of the cable in the aircraft under the electromagnetic field of the HIRF environment, the obtained injection current value is smaller than the injection current which should be actually applied based on the relationship between the field intensity of the irradiation method and the DCI injection current, so that the tested cable induced current value is smaller than the actual cable induced current value, and the protection design and the safety evaluation of the unqualified aircraft are easily classified to meet the requirements, thereby causing erroneous judgment.
Disclosure of Invention
The invention provides a high-intensity radiation field testing device of a low-level scanning field and a testing method thereof, which solve the technical problem that the error judgment of an aircraft safety testing result is easily caused because factors of cable positions and trend are not considered in an equivalent method between an irradiation method and a DCI method in the related art.
The invention provides a high-intensity radiation field test method of a low-level scanning field, which comprises the following steps:
step one, a first airplane model is established, and a plurality of cables are laid in the first airplane model;
step two, performing a test by an irradiation method, calibrating the field intensity of a first airplane model placement site, and obtaining a first transfer function of a cable in the first airplane model;
step three, performing a test by a DCI method, injecting current into the first airplane model, and obtaining a second transfer function of a cable in the first airplane model;
step four, calculating equivalent coefficients through field intensity, injection current, a first transfer function and a second transfer function;
fifthly, recording three-dimensional coordinates of the cable in a three-dimensional coordinate system to generate cable coordinate parameters;
establishing a coefficient model representing the relation between the equivalent coefficient and the coordinate parameter of the cable, and training the coefficient model through the coordinate parameter of the cable in the fifth step and the equivalent coefficient of the cable in the fourth step;
step seven, when a DCI method test is carried out on the second aircraft model, firstly inputting the coordinate parameters of the cable in the second aircraft model into the coefficient model trained in the step six, and generating corresponding equivalent coefficients; the maximum value of all the generated equivalent coefficients is used as the equivalent coefficient of the current test;
and step eight, multiplying the field intensity required by the current test by the equivalent coefficient of the current test to obtain the injection current required by the current test, and applying the injection current to perform the DIC test.
In a preferred embodiment, in step four: the calculation formula of the equivalent coefficient is as follows:wherein->Is the equivalent coefficient of the ith cable, +.>And->The first transfer function and the second transfer function of the ith cable, respectively.
In a preferred embodiment, in the fifth step, the three-dimensional coordinate system uses an injection point of the injected current as an origin, the aircraft axis direction is an X-axis direction, the aircraft spanwise direction is a Y-axis direction, and the aircraft height direction is a Z-axis direction;
the coordinate parameters of the ith cable are expressed asWherein->、/>And->Respectively representing the coordinates of the 1 st, 2 nd and n th points on the ith cable, wherein the distance between two adjacent points is equal,/and%>Wherein->、/>、/>Respectively representing three-dimensional coordinate values of the nth point.
In a preferred embodiment, after the step eight, collecting test data and collecting calculation test results, comparing the induced current of the cable in the tested second aircraft model with a design threshold value for performance evaluation, wherein if the induced current exceeds the design threshold value, the aircraft protection design is not in accordance with the safety standard, and otherwise, the aircraft protection design is in accordance with the safety standard.
In a preferred embodiment, the coefficient model is a neural network model, and the coefficient model includes a linear layer, a first hidden layer and a fully connected layer, wherein the linear layer inputs azimuth characteristics of cables generated by coordinate parameters of the cables, outputs intermediate characteristics of the corresponding cables to the first hidden layer, the first hidden layer further inputs an adjacency matrix representing a direct connection relationship between the cables, the first hidden layer outputs output characteristics corresponding to each cable to the fully connected layer, and the fully connected layer outputs equivalent coefficients.
In a preferred embodiment, the first hidden layer is calculated as follows:，，/>，/>wherein->Representing the output characteristics of the ith cable, +.>And->Representing the intermediate characteristics of the i and j-th cables, respectively,/->Weight parameter representing the first hidden layer, +.>Weight vector representing the first hidden layer, +.>Representing a collection of cables connected directly to the i-th cable;
the azimuth characteristics of the ith cable are expressed as:wherein->、/>、/>Three-dimensional coordinate values of 1 st point of i-th cable,/respectively>、/>、Three-dimensional coordinate values of the nth point of the ith cable are respectively represented.
In a preferred embodiment, the full-join layer outputs a point value class label representing the equivalence factor, the class label corresponding to the discretized point value of the value range of the equivalence factor.
In a preferred embodiment, in step two, the induced current response function of the ith cable in the irradiation method is:wherein->For the induced current of the ith cable, +.>For the field strength of the HIRF ambient electromagnetic field outside the first aircraft model,/for the first aircraft model>For the first transfer function of the ith cable inside the first aircraft model under the HIRF ambient electromagnetic field +.>For the number of cables>Is constant.
In a preferred embodiment, in step three, the induced current response function of the i-th cable in the DCI method is:wherein->For the injection of current from the ith cable to the first aircraft model surface,for the second transfer function of the ith cable in the DCI method,>is the induced current of the ith cable in the DCI method.
A high-intensity radiation field testing apparatus for a low-level scan field for implementing the high-intensity radiation field testing method for a low-level scan field described above, comprising:
the coordinate data acquisition module is used for recording the three-dimensional coordinates of the cable in the three-dimensional coordinate system to generate cable coordinate parameters;
the training module is used for training the coefficient model;
the equivalent coefficient selection module is used for inputting coordinate parameters of cables in the second aircraft model into the trained coefficient model when the DCI method test is carried out on the second aircraft model, generating corresponding equivalent coefficients, and taking the maximum value in all the generated equivalent coefficients as the equivalent coefficient of the current test;
and the injection current calculation module is used for multiplying the field intensity required by the current test by the equivalent coefficient of the current test to obtain the injection current required by the current test.
The invention has the beneficial effects that: according to the invention, the position and the trend of the cable are taken into consideration as the coordinate parameters of the cable on the basis of the equivalence of the existing irradiation method and DIC method, and the equivalent coefficients are generated in the trained coefficient model, so that the injection current required to be injected in the current test is obtained, the error between the calculated injection current and the actual injection current required to be applied is reduced, and the accuracy of the test result is improved.
Drawings
FIG. 1 is a flow chart of the test method of the present invention.
FIG. 2 is a block diagram of the test apparatus of the present invention.
In the figure: 101. the coordinate data acquisition module; 102. a training module; 103. an equivalent coefficient selection module; 104. and an injection current calculation module.
Detailed Description
The subject matter described herein will now be discussed with reference to example embodiments. It is to be understood that these embodiments are merely discussed so that those skilled in the art may better understand and implement the subject matter described herein and that changes may be made in the function and arrangement of the elements discussed without departing from the scope of the disclosure herein. Various examples may omit, replace, or add various procedures or components as desired. In addition, features described with respect to some examples may be combined in other examples as well.
As shown in fig. 1, a method for testing a high-intensity radiation field of a low-level scan field includes the following steps:
step one, a first airplane model is established, and a plurality of cables are laid in the first airplane model;
the cables run at different positions and orientations within the interior of the first aircraft model.
Step two, performing a test by an irradiation method, and calibrating the field intensity of a first airplane model placement site to enable the first airplane model to be in a uniform electromagnetic field; the field strength of the electromagnetic field isThe method comprises the steps of carrying out a first treatment on the surface of the Acquiring a first transfer function of a cable inside a first aircraft model;
step three, performing a test by a DCI method (direct current injection method), and injecting current into the first aircraft model, wherein the injection current is as followsAcquiring a second transfer function of the cable inside the first aircraft model;
step four, passing field intensityInjection current->The first transfer function and the second transfer function calculate equivalent coefficients, each cable in the first aircraft model has a first transfer function and a second transfer function, and therefore each cable calculates an equivalent coefficient, and the calculation formula of the equivalent coefficient is as follows: />Wherein->Is the equivalent coefficient of the ith cable, +.>And->First transfer function sum of i-th cableA second transfer function;
recording three-dimensional coordinates of the cable in a three-dimensional coordinate system to generate cable coordinate parameters, wherein the three-dimensional coordinate system takes an injection point of injection current as an origin, and the axial direction of the airplane is the X-axis direction;
the coordinate parameters of the ith cable are expressed asWherein->、/>And->Respectively representing the coordinates of the 1 st, 2 nd and n th points on the ith cable, wherein the distance between two adjacent points is equal,/and%>Wherein->、/>、/>Respectively representing three-dimensional coordinate values of the nth point. The default value of n is 500 and may be scaled up based on the total number of cables and the total length.
Establishing a coefficient model representing the relation between the equivalent coefficient and the coordinate parameter of the cable, and training the coefficient model through the coordinate parameter of the cable in the fifth step and the equivalent coefficient of the cable in the fourth step;
step seven, when a DCI method test is carried out on the second aircraft model, firstly inputting the coordinate parameters of the cable in the second aircraft model into the coefficient model trained in the step six, and generating corresponding equivalent coefficients; the maximum value of all the generated equivalent coefficients is used as the equivalent coefficient of the current test;
and step eight, multiplying the field intensity required by the current test by the equivalent coefficient of the current test to obtain the injection current required by the current test, and applying the injection current to perform the DIC test.
Thereafter, the method further includes the step of collecting test data (cable induced current, etc.) and calculating test results, which are similar to those of the conventional DIC method test.
For example, the induced currents of all the cables are collected, the induced currents are compared with a design threshold value to perform performance evaluation, if the induced currents exceed the design threshold value, the aircraft protection design is not in accordance with the safety standard, and otherwise, the aircraft protection design is in accordance with the safety standard.
In one embodiment of the invention, the second aircraft model differs from the first aircraft model only in the internal cable arrangement. This allows more accurate results to be obtained when applying the coefficient model.
In one embodiment of the present invention, the coefficient model is a general mathematical model or a neural network model, and as an implementation mode in which the coefficient model is a neural network model, the coefficient model includes a linear layer, a first hidden layer and a fully connected layer, wherein the linear layer inputs azimuth characteristics of cables generated by coordinate parameters of the cables, outputs intermediate characteristics of the corresponding cables to the first hidden layer, the first hidden layer further inputs an adjacency matrix representing a direct connection relationship between the cables, the first hidden layer outputs output characteristics corresponding to each cable to the fully connected layer, and the fully connected layer outputs equivalent coefficients;
the element of the ith row and jth column of the adjacency matrix represents the direct connection relationship of the ith and jth cables, if the element value is 1, the ith and jth cables are directly connected, otherwise the ith and jth cables are not directly connected.
The i and j cables may more specifically mean that the two cables are connected to the same controller or sensor, or that the two cables are connected in parallel.
The calculation formula of the first hidden layer is as follows:，，/>，/>wherein->Representing the output characteristics of the ith cable, +.>And->Representing the intermediate characteristics of the i and j-th cables, respectively,/->Weight parameter representing the first hidden layer, +.>Weight vector representing the first hidden layer, +.>Representing a collection of cables connected directly to the i-th cable;
in one embodiment of the invention, the azimuth characteristics of the ith cable are expressed as:wherein->、/>、/>Three-dimensional coordinate values of 1 st point of i-th cable,/respectively>、/>、/>Three-dimensional coordinate values of the nth point of the ith cable are respectively represented.
The linear layer performs linear transformation on the cable azimuth characteristics through the first weight matrix.
The coefficient model of the embodiment considers the influence of connection and position relation between cables on the transfer function of the cables, and can output equivalent coefficients more accurately.
In one embodiment of the invention, the full connection layer directly outputs a value representing the equivalent coefficient.
In one embodiment of the invention, the full-connection layer outputs a point value classification tag representing the equivalent coefficient, the classification tag corresponding to the point value after discretization of the value range of the equivalent coefficient.
The following describes the coefficient of efficiency:
the induction current response function of the ith cable in the irradiation method is as follows:（1）
wherein the method comprises the steps ofFor the ith cable the field strength is +.>Lower induced current, ">For the field strength of the HIRF ambient electromagnetic field outside the first aircraft model,/for the first aircraft model>For a field strength of +.>A transfer function of an ith cable inside the lower first aircraft model; in formula (1)>Constant and unchanged;
assuming that the injection current to the first aircraft model surface with reference to the ith cable in the DCI method is，/>The i-th cable in DCI method is injected with current of +.>Transfer function below->The ith root in the DCI method is injected with current +.>The induced current of the cable is lower, and the induced current response function of the ith cable in the DCI method is as follows:
（2）
if the two test methods are equivalent, then
According to the formulas (1) and (2), the following formulas are obtained:（3）
since the injection current needs to be calculated according to the field strength of the equivalent irradiation method when the second aircraft model DCI method test is required, formula (3) is rewritten as:（4）
wherein, the liquid crystal display device comprises a liquid crystal display device,is the equivalent coefficient of the ith cable, +.>Injecting current to the surface of a first aircraft model in the DIC method;the field intensity of an HIRF environment electromagnetic field outside the first airplane model in the irradiation method; />The transfer function of the ith cable is sensed in the irradiation method; />The i-th cable in DCI method is injected with current of +.>A transfer function below;
in order to ensure that the injection current at the surface of the second aircraft model in the DIC method can reflect the weak point of the device when it encounters the HIRF environment, the maximum equivalent coefficient of the cable inside the second aircraft model needs to be selected to calculate the injection current to be equivalent to the irradiation method for the test.
As shown in fig. 2, there is provided a low-level field high-intensity radiation field testing apparatus for implementing the low-level field high-intensity radiation field testing method, comprising:
the coordinate data acquisition module 101 is used for recording three-dimensional coordinates of the cable in a three-dimensional coordinate system to generate cable coordinate parameters;
the training module 102 is used for training the coefficient model;
the equivalent coefficient selection module 103 is configured to input coordinate parameters of a cable inside the second aircraft model into the trained coefficient model when performing a DCI method test on the second aircraft model, generate corresponding equivalent coefficients, and use the maximum value of all the generated equivalent coefficients as the equivalent coefficient of the current test;
the injection current calculation module 104 is configured to multiply the field intensity of the simulation required by the current test by the equivalent coefficient of the current test to obtain the injection current required to be injected by the current test.
The embodiment has been described above with reference to the embodiment, but the embodiment is not limited to the above-described specific implementation, which is only illustrative and not restrictive, and many forms can be made by those of ordinary skill in the art, given the benefit of this disclosure, are within the scope of this embodiment.
Claims (9)
1. The high-intensity radiation field testing method for the low-level scanning field is characterized by comprising the following steps of:
step one, a first airplane model is established, and a plurality of cables are laid in the first airplane model;
step two, performing a test by an irradiation method, calibrating the field intensity of a first airplane model placement site, and obtaining a first transfer function of a cable in the first airplane model;
step three, performing a test by a DCI method, injecting current into the first airplane model, and obtaining a second transfer function of a cable in the first airplane model;
step four, calculating equivalent coefficients through field intensity, injection current, a first transfer function and a second transfer function;
fifthly, recording three-dimensional coordinates of the cable in a three-dimensional coordinate system to generate cable coordinate parameters;
establishing a coefficient model representing the relation between the equivalent coefficient and the coordinate parameter of the cable, and training the coefficient model through the coordinate parameter of the cable in the fifth step and the equivalent coefficient of the cable in the fourth step;
step seven, when a DCI method test is carried out on the second aircraft model, firstly inputting the coordinate parameters of the cable in the second aircraft model into the coefficient model trained in the step six, and generating corresponding equivalent coefficients; the maximum value of all the generated equivalent coefficients is used as the equivalent coefficient of the current test;
and step eight, multiplying the field intensity required by the current test by the equivalent coefficient of the current test to obtain the injection current required by the current test, and applying the injection current to perform the DIC test.
2. A method of high intensity radiation field testing of a low level scan field as defined in claim 1, wherein in step four: the calculation formula of the equivalent coefficient is as follows:wherein->Is the equivalent coefficient of the ith cable, +.>And->The first transfer function and the second transfer function of the ith cable, respectively.
3. The method for testing a high-intensity radiation field of a low-level scan field according to claim 2, wherein in the fifth step, the three-dimensional coordinate system uses an injection point of an injection current as an origin, an aircraft axis direction is an X-axis direction, an aircraft wingspan direction is a Y-axis direction, and an aircraft height direction is a Z-axis direction;
the coordinate parameters of the ith cable are expressed asWherein->、/>And->Respectively representing the coordinates of the 1 st, 2 nd and n th points on the ith cable, wherein the distance between two adjacent points is equal,/and%>Wherein->、/>、/>Respectively representing three-dimensional coordinate values of the nth point.
4. The method for testing a high-intensity radiation field of a low-level scan field according to claim 1, wherein the performance evaluation is performed by comparing the induced current of the cable in the second aircraft model to a design threshold, and the induced current exceeding the design threshold indicates that the protection design of the aircraft does not meet the safety standard, and otherwise indicates that the protection design of the aircraft meets the safety standard.
5. The method according to claim 4, wherein the coefficient model is a neural network model, the coefficient model includes a linear layer, a first hidden layer and a fully connected layer, wherein the linear layer inputs azimuth characteristics of the cables generated by coordinate parameters of the cables, outputs intermediate characteristics of the corresponding cables to the first hidden layer, the first hidden layer further inputs an adjacency matrix representing a direct connection relationship between the cables, the first hidden layer outputs output characteristics corresponding to each cable to the fully connected layer, and the fully connected layer outputs equivalent coefficients;
the element of the ith row and jth column of the adjacency matrix represents the direct connection relationship of the ith and jth cables, if the element value is 1, the ith and jth cables are directly connected, otherwise the ith and jth cables are not directly connected.
6. The method of claim 5, wherein the first hidden layer is calculated according to the following formula:，/>，，/>wherein->Representing the output characteristics of the ith cable, +.>And->Representing the intermediate characteristics of the i and j-th cables, respectively,/->Weight parameter representing the first hidden layer, +.>Weight vector representing the first hidden layer, +.>Representing a collection of cables connected directly to the i-th cable; the azimuth characteristics of the ith cable are expressed as:wherein->、/>、/>Three-dimensional coordinate values of 1 st point of i-th cable,/respectively>、/>、/>Three-dimensional coordinate values of the nth point of the ith cable are respectively represented.
7. The method of claim 6, wherein in the second step, the induced current response function of the i-th cable in the irradiation method is:wherein->For the induced current of the ith cable, +.>For the field strength of the HIRF ambient electromagnetic field outside the first aircraft model,for the first transfer function of the ith cable inside the first aircraft model under the HIRF ambient electromagnetic field +.>For the number of cables>Is constant.
8. The method of claim 7, wherein in the third step, the induced current response function of the i-th cable in the DCI method is:wherein->For the i-th cable to inject current into the first aircraft model surface, < >>For the second transfer function of the ith cable in the DCI method,>is the induced current of the ith cable in the DCI method.
9. A low-level-field high-intensity-radiation-field testing apparatus for performing the low-level-field high-intensity-radiation-field testing method according to any one of claims 1 to 8, the low-level-field high-intensity-radiation-field testing apparatus comprising:
the coordinate data acquisition module (101) is used for recording three-dimensional coordinates of the cable in a three-dimensional coordinate system to generate cable coordinate parameters;
a training module (102) for training the coefficient model;
the equivalent coefficient selection module (103) is used for inputting coordinate parameters of cables in the second aircraft model into the trained coefficient model when the DCI method test is carried out on the second aircraft model, generating corresponding equivalent coefficients, and taking the maximum value in all the generated equivalent coefficients as the equivalent coefficient of the current test;
and the injection current calculation module (104) is used for multiplying the field intensity of the simulation required by the current test by the equivalent coefficient of the current test to obtain the injection current required by the current test.
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| CN116879664A (en) * | 2023-09-06 | 2023-10-13 | 合肥航太电物理技术有限公司 | Low-level direct drive testing device and testing method for high-intensity radiation field |
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