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CN113238288A - Rotor wing target feature extraction method based on difference spectral line - Google Patents

Rotor wing target feature extraction method based on difference spectral line Download PDF

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Publication number
CN113238288A
CN113238288A CN202110551309.XA CN202110551309A CN113238288A CN 113238288 A CN113238288 A CN 113238288A CN 202110551309 A CN202110551309 A CN 202110551309A CN 113238288 A CN113238288 A CN 113238288A
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blade
blades
modal
vortex electromagnetic
rotor
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CN113238288B (en
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谢跃雷
许强
邓涵方
肖潇
曾浩南
梁文斌
王胜
谢星丽
欧阳缮
廖桂生
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Guilin University of Electronic Technology
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    • G01—MEASURING; TESTING
    • G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS
    • G01V3/00—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation
    • G01V3/12—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation operating with electromagnetic waves

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Abstract

The invention discloses a rotor wing target characteristic extraction method based on difference spectral lines, which is characterized by comprising the following steps of: 1) constructing a rotor wing target blade and a vortex electromagnetic wave model; 2) processing the simulation data by using a spectral decomposition method to obtain a difference spectral line; 3) and (3) changing the number of the blades, the length of the blades, the width of the blades and the position angle of the blades, and repeating the step 2) to respectively obtain difference spectral lines influencing the OAM. The method can accurately acquire the blade characteristics of the rotor target, thereby improving the precision of detecting and identifying the rotor target.

Description

Rotor wing target feature extraction method based on difference spectral line
Technical Field
The invention relates to the field of electromagnetic vortex target detection, in particular to a rotor wing target characteristic extraction method based on a difference spectral line.
Background
Nowadays, in people's social life, many rotor crafts have not been enough, and the big outbreak of unmanned aerial vehicle industry is widely used in fields such as aerial photography, agriculture, military affairs, and unmanned aerial vehicle belongs to typical rotor target. The frequent appearance of rotor target brings convenience in the life of giving people, has also brought some potential safety hazards, like unmanned aerial vehicle "black flight" incident frequently in recent years, uses unmanned aerial vehicle to carry out malicious investigation and monitoring, direct attack crowd etc.. However, a rotor target has the characteristics of a "low, slow, small" target, and the rotor target can hover in the air at any time, which is not detectable at all for conventional radars.
In recent years, with the introduction of vortex electromagnetic waves carrying Orbital Angular Momentum (OAM), a new angle and a new method are provided for the field of target detection for people, theoretically, the vortex electromagnetic waves have infinite different topological charge numbers, namely modes of orbital angular momentum, for convenience of calculation, the modes generally take integers, the modes of different orbital angular momentum are orthogonal to each other, namely the vortex electromagnetic waves with different modal numbers can be linearly superposed, and the property shows that the vortex electromagnetic waves with different modal numbers can be physically separated.
Aiming at the rotor target, no matter the rotor target is in a flying state or a hovering state, the spiral blades of the rotor target are always in rotation, the number, the length, the width and the like of the blades of the rotor target can be different according to different types of the rotor targets, and the different characteristics can be used as detection and identification bases for the rotor target.
Disclosure of Invention
The invention aims to provide a rotor wing target feature extraction method based on difference spectral lines, aiming at the defects of the prior art. The method can accurately acquire the blade characteristics of the rotor target, thereby improving the precision of detecting and identifying the rotor target.
The technical scheme for realizing the purpose of the invention is as follows:
a rotor wing target characteristic extraction method based on difference spectral lines is different from the prior art and comprises the following steps:
1) constructing a rotor target blade and vortex electromagnetic wave model: adopting feko electromagnetic simulation software to construct a simulation model of a rotor target blade and vortex electromagnetic waves, generating vortex electromagnetic waves by forming a circular array by 8 dipole antennas which are arranged at equal intervals, sequentially applying signal excitation sources with the same amplitude and gradually increased phase to the array elements with the frequency of the array elements being 10GHz and the radius of the array being 30mm, namely the length of one wavelength, generating vortex electromagnetic waves with different modal numbers, a sampling circumference with the radius of 30mm is arranged at the position 300mm above the circular array, the radius of the sampling circumference is 30mm consistent with the radius of the circular array, the number of sampling points is 360 points, a rotor wing target spiral blade model is arranged between the circular array and the sampling circumference, namely 150mm above the circular array, and the number of blades, the length of the blades, the width of the blades and the position angle parameters of the blades of the rotor wing target spiral blade model are adjustable;
2) obtaining a difference spectral line: changing the phase of an excitation source, generating vortex electromagnetic waves with different modal numbers, emitting the vortex electromagnetic waves with different modal numbers, and carrying out spectral decomposition method processing on simulated data by adopting MATLAB to obtain a difference spectral line, wherein the method specifically comprises the following steps: rotor target spiral blades are not added between the circular array and the sampling circumference, namely, vortex electromagnetic waves directly reach the sampling circumference, and the circular array antenna respectively transmits the vortex electromagnetic waves with the modal numbers of 0, 1, 2 and 3 to obtain a group of simulation data as a comparison group; and then, a rotor target spiral blade is added between the circular array and the sampling circumference, the circular array antenna respectively emits vortex electromagnetic waves with the modal numbers of 0, 1, 2 and 3, and the vortex electromagnetic waves reach the sampling circumference after being influenced by the blades to obtain a group of simulation data as an experimental group. Because the modal numbers are mutually orthogonal, a modal spectrogram of the vortex electromagnetic wave is drawn through a spectral decomposition method, and a modal difference spectral line graph, which is called a difference spectral line for short, is obtained by subtracting the modal spectrum of the control group from the modal spectrum of the experimental group;
3) obtaining a difference spectral line influencing OAM: changing the number of blades, the length of the blades, the width of the blades and the position angle of the blades, repeating the step 2) to obtain a plurality of groups of simulation data as experimental group data, respectively obtaining difference spectral lines influencing OAM, and obtaining the difference spectral lines by the difference spectral lines: the number, the length and the width of the blades have great influence on high-mode vortex electromagnetic waves and small influence on low modes; the number of the blades takes the main mode as a central axis, the number of the blades is taken as a stepping number to influence the secondary mode, the influence of the blades on OAM is irrelevant to the position angle, the speed of electromagnetic waves is far greater than the rotation speed of a propeller, and the propeller can be regarded as a static state with different position angles for the electromagnetic waves, so that the influence of the rotating blades on OAM is equivalent to the influence of the static blades on OAM, the change of a secondary mode spectrum is analyzed, whether a rotor target exists can be judged, the parameter characteristics of the rotor target blades are obtained, and the accuracy is improved for the detection and the identification of the rotor target.
Compared with the prior radar detection rotor target, the technical scheme has the following characteristics:
the invention constructs a model of a rotor target blade and vortex electromagnetic waves, the rotor target can cause influence on the mode number of the vortex electromagnetic waves by taking the blade number as a period, the influence is irrelevant to the position angle of the rotor target blade, and whether the rotor target is in a flying state or a hovering state, the spiral blade is always in a rotating state, so whether the rotor target exists in a range can be effectively judged by observing the change of a vortex electromagnetic wave mode spectrum, if the rotor target exists, the blade characteristic of the rotor target can be extracted, and the type identification of the rotor target is realized.
The method can accurately acquire the blade characteristics of the rotor target, thereby improving the precision of detecting and identifying the rotor target.
Drawings
FIG. 1 is a schematic view of an embodiment of a rotor target blade and a vortex electromagnetic wave model;
fig. 2 is a difference spectrum diagram after the OAM is affected by the blade numbers of 2, 3, and 4 in the embodiment, in which fig. 2 (a) shows the effect of different blade numbers on the vortex electromagnetic waves with the mode numbers of 0 and 1, and fig. 2 (b) shows the effect of different blade numbers on the vortex electromagnetic waves with the mode numbers of 2 and 3;
fig. 3 is a difference spectrum diagram after the blade lengths of 30mm, 70mm and 120mm respectively affect OAM in the embodiment, wherein fig. 3 (a) shows the results of different blade lengths affecting vortex electromagnetic waves with the mode numbers of 0 and 1, and fig. 3 (b) shows the results of different blade lengths affecting vortex electromagnetic waves with the mode numbers of 2 and 3;
fig. 4 is a difference spectrum diagram after the blade widths of 10mm and 20mm respectively affect OAM in the embodiment, wherein fig. 4 (a) shows the results of different blade widths affecting vortex electromagnetic waves with mode numbers of 0 and 1, and fig. 4 (b) shows the results of different blade widths affecting vortex electromagnetic waves with mode numbers of 2 and 3;
fig. 5 is a difference spectrum diagram of the blade position angles of 0 °, 20 ° and 80 ° in the embodiment after the influence is generated on the vortex electromagnetic wave with the mode numbers of 0 and 1.
Detailed Description
The invention will be further illustrated, but not limited, by the following description, with reference to the accompanying drawings and examples.
Example (b):
a rotor wing target feature extraction method based on difference spectral lines comprises the following steps:
1) constructing a rotor target blade and vortex electromagnetic wave model: adopting feko electromagnetic simulation software to construct a simulation model of a rotor wing target blade and vortex electromagnetic waves, as shown in fig. 1, the vortex electromagnetic wave generates a circular array composed of 8 dipole antennas arranged at equal intervals, each dipole array element antenna has a frequency of 10GHz and an array radius of 30mm, that is, a wavelength length, signal excitation sources with the same amplitude and gradually increased phases are sequentially applied to the array elements, the frequency of the array elements is 10GHz, vortex electromagnetic waves with different modal numbers are generated, a sampling circumference with the radius of 30mm is arranged at the position 300mm above the circular array, the radius of the sampling circumference is 30mm consistent with the radius of the circular array, the number of sampling points is 360 points, a rotor wing target spiral blade model is arranged between the circular array and the sampling circumference, namely 150mm above the circular array, and the number of blades, the length of the blades, the width of the blades and the position angle parameters of the blades of the rotor wing target spiral blade model are adjustable;
2) obtaining a difference spectral line: changing the phase of an excitation source, generating vortex electromagnetic waves with different modal numbers, emitting the vortex electromagnetic waves with different modal numbers, and carrying out spectral decomposition method processing on simulated data by adopting MATLAB to obtain a difference spectral line, wherein the method specifically comprises the following steps: rotor target spiral blades are not added between the circular array and the sampling circumference, namely, vortex electromagnetic waves directly reach the sampling circumference, and the circular array antenna respectively transmits the vortex electromagnetic waves with the modal numbers of 0, 1, 2 and 3 to obtain a group of simulation data as a comparison group; and then, a rotor target spiral blade is added between the circular array and the sampling circumference, the circular array antenna respectively emits vortex electromagnetic waves with the modal numbers of 0, 1, 2 and 3, and the vortex electromagnetic waves reach the sampling circumference after being influenced by the blades to obtain a group of simulation data as an experimental group. All the modal numbers are mutually orthogonal, a modal spectrogram of the vortex electromagnetic wave is drawn through a spectral decomposition method, and a modal difference spectrogram is obtained by subtracting the modal spectrum of the control group from the modal spectrum of the experimental group;
3) obtaining a difference spectral line influencing OAM: changing the number of blades, the length of the blades, the width of the blades and the position angle of the blades, and repeating the step 2) to obtain a plurality of groups of simulation data as experimental group data, specifically:
3-1) changing the number of blades, setting the length of the blades to be 120mm, obtaining a difference spectral line of the blade number on the OAM, wherein as shown in FIG. 2, the abscissa corresponding to the difference spectral line being less than 0 in the graph is the number of modes for emitting vortex electromagnetic waves, namely the main mode, the main mode is reduced in ratio and the secondary mode is increased in ratio due to the influence of the blades, when the blade number is 2, the secondary mode is larger in ratio change and takes the main mode as a central axis, and 2 as a stepping secondary mode, for example, when the main mode is 0, the secondary mode is larger in ratio change and is-4, -2, 4; when the number of the blades is 3, the ratio of the secondary mode is changed greatly by taking the main mode as a central axis and taking 3 as a stepped secondary mode, and compared with fig. 2 (a) and fig. 2 (b), the ratio of the difference spectral lines when the main mode is 3 is reduced most, namely, the influence of the blades on the high-mode vortex electromagnetic waves is larger than that of the low-mode vortex electromagnetic waves;
3-2) setting the number of blades to be 3, changing the lengths of the blades to be 30mm, 70mm and 120mm respectively, and obtaining difference spectral lines of the lengths of the blades on OAM (operation administration and maintenance) influences, as shown in FIG. 3, as can be seen from FIG. 3 (a) and FIG. 3 (b), as the lengths of the blades increase, the ratio of the primary mode decreases more, the influence is larger, and the ratio of the secondary mode with larger change is the secondary mode with the primary mode as the central axis and 3 as the step;
3-3) the number of the blades is 3, the widths of the blades are changed to be 10mm and 20mm respectively, and the lengths of the blades are changed to be 120mm, so as to obtain a difference spectral line of the blade widths on the OAM influence, as shown in fig. 4, as can be seen from fig. 4 (a) and 4 (b), the larger the influence caused by the increase of the blade widths, the larger the change of the ratio of the secondary modes is, the primary mode is taken as the central axis, and the 3 is taken as the stepped secondary mode;
3-3) changing the position angle of the blade to be 0 degree, 20 degrees and 80 degrees respectively, the number of the blades is 3, the length is 120mm, obtaining a difference spectral line of the influence of the position angle of the blade on OAM, as shown in fig. 5, overlapping three lines, showing that the influence of the blade on OAM is irrelevant to the position angle, as the speed of electromagnetic wave is far greater than the rotation speed of the propeller, the propeller can be regarded as a static state of different position angles for the electromagnetic wave, so that the influence of the rotating blade on OAM can be presumed to be equivalent to the influence of the static blade on OAM, the influence of the rotating blade on OAM is equivalent to the influence of the static blade on OAM, analyzing the change of the sub-modal spectrum, judging whether a rotor target exists, obtaining the parameter characteristics of the rotor target blade, and improving the accuracy for the detection and identification of the rotor target.

Claims (1)

1.一种基于差值谱线的旋翼目标特征提取方法，其特征在于，包括如下步骤：1. a rotor target feature extraction method based on difference spectrum line, is characterized in that, comprises the steps: 1）构建旋翼目标叶片与涡旋电磁波模型：采用feko电磁仿真软件构建旋翼目标叶片和涡旋电磁波的仿真模型，涡旋电磁波产生由8个等间距排列的偶极子天线组成圆形阵列、各偶极子阵元天线频率为10GHz、阵列半径为30mm即一个波长长度，依次对阵元施加幅度相同、相位递增的信号激励源，阵元频率为10GHz，产生不同模态数的涡旋电磁波，在圆形阵列正上方300mm处设置一个半径为30mm的采样圆周，采样圆周半径与圆形阵列半径一致均为30mm，采样点数为360个点，在圆阵与采样圆周之间即圆形阵列正上方150mm处设置旋翼目标螺旋叶片模型，旋翼目标螺旋叶片模型的叶片数、叶片长度、叶片宽度、叶片位置角度参数可调整；1) Build the rotor target blade and vortex electromagnetic wave model: The feko electromagnetic simulation software is used to build the simulation model of the rotor target blade and the vortex electromagnetic wave. The vortex electromagnetic wave generates a circular array composed of 8 equally spaced dipole antennas. The frequency of the dipole array element antenna is 10GHz, the array radius is 30mm, which is one wavelength length, and the signal excitation source with the same amplitude and increasing phase is applied to the elements in turn. A sampling circle with a radius of 30mm is set at 300mm directly above the circular array. The radius of the sampling circle is the same as that of the circular array, which is 30mm. The number of sampling points is 360 points. The rotor target helical blade model is set at 150mm, and the parameters of the blade number, blade length, blade width and blade position angle of the rotor target helical blade model can be adjusted; 2）得到差值谱线：改变激励源的相位，产生不同模态数的涡旋电磁波，发射不同模态数的涡旋电磁波，采用MATLAB对仿真的数据进行谱分解法处理，得到差值谱线，具体为：在圆形阵列与采样圆周之间先不添加旋翼目标螺旋叶片，即涡旋电磁波直接到达采样圆周，圆形阵列天线分别发射模态数为0、1、2、3的涡旋电磁波，得到一组仿真数据作为对照组；随后，在圆形阵列与采样圆周之间添加旋翼目标螺旋叶片，圆形阵列天线分别发射模态数为0、1、2、3的涡旋电磁波，涡旋电磁波经过叶片影响后，到达采样圆周，得到一组仿真数据作为实验组，由于各模态数之间相互正交，通过谱分解法绘制涡旋电磁波的模态谱图，将实验组的模态谱减去对照组的模态谱得到模态差值谱线图，简称差值谱线；2) Obtain the difference spectrum line: change the phase of the excitation source, generate vortex electromagnetic waves with different modal numbers, emit vortex electromagnetic waves with different modal numbers, and use MATLAB to process the simulated data by spectral decomposition method to obtain the difference spectrum Specifically, the target helical blade of the rotor is not added between the circular array and the sampling circle, that is, the vortex electromagnetic wave directly reaches the sampling circle, and the circular array antenna emits vortices with modal numbers 0, 1, 2, and 3 respectively. Then, a rotor target helical blade is added between the circular array and the sampling circle, and the circular array antenna emits vortex electromagnetic waves with modal numbers 0, 1, 2, and 3 respectively. , after the vortex electromagnetic wave is affected by the blade, it reaches the sampling circle, and a set of simulation data is obtained as the experimental group. Since the modal numbers are mutually orthogonal, the modal spectrum of the vortex electromagnetic wave is drawn by the spectral decomposition method. The modal spectrum of the control group is subtracted from the modal spectrum of the control group to obtain the modal difference spectrum, which is referred to as the difference spectrum; 3）得到对OAM影响的差值谱线：更改叶片数、叶片长度、叶片宽度、叶片位置角度，重复步骤2）得到多组仿真数据作为实验组数据，分别得到对OAM影响的差值谱线，由差值谱线得到：叶片数量、长度、宽度均对高模态的涡旋电磁波影响大、对低模态影响小；叶片数以主模态为中心轴、以叶片数为步进数对次模态造成影响，而叶片对OAM的影响与位置角度无关，电磁波的速度远大于螺旋桨转动速度，对于电磁波而言，螺旋桨可视为不同位置角度的静止状态，故转动的叶片对OAM的影响等效于静止的叶片对OAM的影响，分析次模态谱的变化，能判断是否存在旋翼目标，并获取旋翼目标叶片参数特征。3) Obtain the difference spectral line affecting OAM: change the number of leaves, leaf length, leaf width, and leaf position angle, repeat step 2) to obtain multiple sets of simulation data as experimental data, and obtain the difference spectral lines affecting OAM respectively. , obtained from the difference spectral line: the number, length, and width of the blades all have a great influence on the vortex electromagnetic wave in the high mode, and a small effect on the low mode; the number of blades takes the main mode as the central axis, and the number of blades as the number of steps It affects the secondary mode, and the influence of the blade on the OAM has nothing to do with the position angle. The speed of the electromagnetic wave is much greater than the rotation speed of the propeller. For the electromagnetic wave, the propeller can be regarded as a static state at different positions and angles. Therefore, the rotating blade has no effect on the OAM. The influence is equivalent to the influence of stationary blades on OAM. By analyzing the change of the sub-modal spectrum, it can judge whether there is a rotor target and obtain the parameter characteristics of the rotor target blade.
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