CN107907738B - Distortion analysis method of space remote measuring signal - Google Patents
Distortion analysis method of space remote measuring signal Download PDFInfo
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Abstract
The invention relates to a distortion analysis method of a space telemetering signal, which comprises the following steps: s1, acquiring a standard filtering signal and a test filtering signal; s2, performing cross-correlation analysis on the standard filtering signal and the test filtering signal; and S3, outputting an analysis result by an output device, and directly adopting the standard frequency spectrum data and converting the test signal into the frequency spectrum data so as to ensure that the test frequency spectrum data and the standard frequency spectrum data can be successfully compared and analyzed, thereby simplifying the preprocessing process of the test filtering signal and the standard filtering signal. Therefore, the time delay of the distortion analysis of the test signal sent by the spacecraft is reduced, and the real-time performance of the analysis of the test signal of the spacecraft is better ensured.
Description
Technical Field
The invention relates to a distortion analysis method of a telemetering signal, in particular to a distortion analysis method for an aerospace telemetering signal.
Background
In the process of testing the spacecraft, a radio frequency link needs to be established between the spacecraft and ground testing equipment, remote control instructions, remote measurement data, image voice data and the like are transmitted between the spacecraft and the ground through the radio frequency link, and in order to timely find out the states such as radio frequency signal abnormality sent by the spacecraft or the ground equipment, radio frequency signal instability between the spacecraft and the ground caused by interference factors such as multipath effect and the like in the testing state of the wireless state of the spacecraft, the frequency spectrum of the radio frequency link needs to be monitored and analyzed. In the current spacecraft integrated test, adopt the frequency spectrograph to receive radio frequency signal usually to show the spectrum that obtains after handling, the tester monitors the demonstration page of frequency spectrograph and carries out spectrum real-time analysis, and the result of this kind of manual analysis inevitably can receive the influence of individual subjective factor, and takes place the condition of lou judgement easily in long-time monitoring process. When the signal spectrum distortion duration is short and the distortion degree is small, the signal spectrum distortion duration is difficult to find, and the method is only suitable for the time when the signal spectrum distortion is obvious and stable.
In addition, in the test of the spacecraft, with the increase of a measurement and control link of the spacecraft, more and more radio frequency signals need to be monitored simultaneously, only one path of monitoring can be selected by the current manual analysis method, or the monitoring is frequently switched, the workload is large, and the real-time analysis of multiple paths of signals cannot be realized.
For example, an invention patent with publication number CN103869334B entitled "automatic identification and processing method of GNSS space signal distortion" discloses a solution. Firstly establishing a signal distortion model base, secondly analyzing and processing satellite navigation signals acquired by a data acquisition card, then establishing a signal analysis comparison model base, and finally establishing a distortion signal model base. According to the scheme, the satellite signals are analyzed and processed, and the distortion types and the like of the satellite signals are determined through multiple times of comparison, so that the processing process in the whole process is very complex, the display of the analysis result is delayed, and the real-time monitoring and analysis of the signals of the spacecraft are not facilitated.
Disclosure of Invention
The invention aims to provide a distortion analysis method of a space telemetering signal, which solves the problem of signal distortion analysis delay.
In order to achieve the above object, the present invention provides a distortion analysis method for an aerospace telemetry signal, comprising:
s1, acquiring a standard filtering signal and a test filtering signal;
s2, performing cross-correlation analysis on the standard filtering signal and the test filtering signal;
s3, outputting an analysis result by an output device,
wherein the step of performing a cross-correlation analysis on the standard filtered signal and the test filtered signal comprises:
s21, performing FFT calculation on the standard filtering signal to obtain first result data;
s22, carrying out FFT calculation on the test filtering signal to obtain second result data, and carrying out conjugate calculation on the second result data to obtain third result data;
s23, carrying out complex multiplication on the first result data and the third result data to obtain fourth result data;
s24, performing frequency domain weighting calculation on the fourth result data to obtain fifth result data;
and S25, analyzing the fifth result data.
According to an aspect of the invention, the step of analyzing the fifth result data comprises:
s251, performing IFFT calculation on the fifth result data to obtain sixth result data, and performing modulus extraction on the sixth result data to obtain seventh result data;
and S252, acquiring the maximum value in the seventh result data and comparing the maximum value with a set threshold value.
According to one aspect of the invention, the step of obtaining the standard filtered signal comprises:
s11, acquiring standard frequency spectrum data from a ground data source;
and S12, carrying out digital filtering on the standard frequency spectrum data to obtain the standard filtering signal.
According to one aspect of the invention, the step of obtaining the test filtered signal comprises:
s13, collecting a test signal sent by the spacecraft;
s14, obtaining test frequency spectrum data of the test signal;
and S15, carrying out digital filtering on the test frequency spectrum data to obtain the test filtering signal.
According to one aspect of the invention, the test spectrum data is acquired as a sequence of numbers.
According to an aspect of the present invention, the step of outputting the analysis result by the output means further comprises:
and S31, displaying the maximum value in the seventh result data through the output device.
According to an aspect of the present invention, the output means displays a prompt message when the maximum value in the seventh result data is less than a set threshold value.
According to an aspect of the present invention, the acquired test spectrum data is stored, and the maximum value among the acquired seventh result data is stored.
According to an aspect of the invention, the maximum value in the seventh result data is displayed in a curve manner.
According to one aspect of the invention, the test signal is converted into test spectral data by a spectrometer having a spectral data output interface.
According to one scheme of the invention, the standard frequency spectrum data is directly adopted, and the test signal is converted into the frequency spectrum data, so that the smooth comparison and analysis between the test frequency spectrum data and the standard frequency spectrum data are ensured, and the pre-processing process of the test filtering signal and the standard filtering signal is simplified. Therefore, the time delay of the distortion analysis of the test signal sent by the spacecraft is reduced, and the real-time performance of the analysis of the test signal of the spacecraft is better ensured. Meanwhile, the digital filtering is carried out on the test frequency spectrum data and the standard frequency spectrum data, so that redundant and unnecessary interference in the test frequency spectrum data and the standard frequency spectrum data can be removed, and the beneficial effect of accelerating the efficiency of the cross-correlation analysis of the subsequent test filtering signal and the standard filtering signal is achieved. The requirement of real-time analysis on the spacecraft test signals is further met.
According to one scheme of the invention, the fourth result data is further filtered by carrying out frequency domain weighting on the fourth result data, clutter influence in the fourth result data is inhibited, meanwhile, the fourth result data is large in dynamic range, wide in frequency band and high in sensitivity, and the accuracy of the result in the subsequent analysis process is further effectively improved. Particularly for the spacecraft, the interference of irrelevant signals is effectively avoided by improving the accuracy of the subsequent analysis process, and the spacecraft state information can be timely and accurately acquired and accurately controlled.
According to one scheme of the invention, the error in the IFFT calculation of the fifth result data is reduced by carrying out frequency domain weighting on the fourth result data, so that the error of the sixth result data is small, and the accuracy of obtaining the seventh result data is further effectively improved. By the method, in the process of testing the test signal sent by the spacecraft, the accuracy of the data result obtained in the analysis process is improved, so that the method is beneficial to acquiring the operation state information of the spacecraft in real time and accurately controlling the spacecraft. Meanwhile, the accuracy of the analysis result is improved, the influence of other irrelevant signals on the analysis result is avoided, and the misjudgment of the analysis method on the real-time state of the spacecraft is avoided. By taking the modulus of the seventh result data and obtaining the maximum value and comparing the maximum value with the threshold value, each value in the seventh result data does not need to be compared with the threshold value, the complexity of the analysis process of the invention is effectively reduced, the analysis process is simplified, the precision and the reliability of the analysis method of the invention are ensured, and the real-time analysis capability of the clear analysis method is further improved.
According to one scheme of the invention, the seventh result data can be displayed intuitively by using the curve mode for display, so that a user can observe the displayed curve intuitively, and the identification degree is improved. In the real-time mode, the output device displays the presentation information when the maximum value in the seventh result data is smaller than the set threshold value. By the method, the distortion signal generated by the user can be timely found when the user observes the displayed curve, the missing judgment of the distortion signal is avoided, and the user can be further ensured to timely obtain the state information of the spacecraft.
According to one scheme of the invention, the analysis method of the invention is used for replacing manual work to complete the analysis of the test signal, and automatically reminds a user when the test signal is distorted, thereby improving the automation degree of the test. By the analysis method, the test signals sent by the spacecraft are subjected to quantitative visual display, and the influence of subjective factors of a user on the judgment result of the test signals is avoided by comparing the test signals with the set threshold value. By means of sending prompt information to remind the user, the condition of missed judgment caused by factors such as fatigue and the like under the condition that the user monitors for a long time is avoided. By the analysis method, the multi-channel signal spectrum distortion can be analyzed in real time, the workload of manual analysis is reduced, various state information of the working state of the spacecraft can be further obtained by a user in real time, and the normal operation of the spacecraft is ensured.
Drawings
FIG. 1 schematically shows a flow diagram of a cross-correlation analysis method of signal distortion according to an embodiment of the invention;
FIG. 2 schematically shows a flow diagram of a cross-correlation analysis method of signal distortion according to an embodiment of the invention;
fig. 3 schematically shows a cross-correlation analysis flowchart of a cross-correlation analysis method of signal distortion according to another embodiment of the present invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present invention.
The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.
As shown in fig. 1, according to one embodiment of the present invention, the distortion analysis method of the aerospace telemetry signal according to the present invention comprises:
s1, acquiring a standard filtering signal and a test filtering signal;
s2, performing cross-correlation analysis on the standard filtering signal and the test filtering signal;
and S3, outputting an analysis result by an output device.
As shown in fig. 2, according to an embodiment of the present invention, the standard filtered signal is obtained by the following steps:
s11, standard frequency spectrum data are obtained from a ground data source, and the standard frequency spectrum data are digital sequences.
The ground data source stores standard frequency spectrum data, and the standard frequency spectrum data in the ground data source can be conveniently obtained by reading.
And S12, carrying out digital filtering on the standard frequency spectrum data to obtain a standard filtering signal.
As shown in fig. 2, according to an embodiment of the present invention, the test filtered signal is obtained by the following steps:
s13, collecting a test signal sent by the spacecraft;
in this embodiment, a test signal transmitted by the spacecraft is received over a radio frequency link established between the ground and the spacecraft.
S14, obtaining test frequency spectrum data of the test signal, wherein the test frequency spectrum data is a digital sequence;
in this embodiment, a received test signal is input to a spectrometer, and the test signal is converted into test spectrum data by the action of the spectrometer. In this embodiment, the test signal is converted into test spectrum data by a spectrometer having a spectrum data output interface. Meanwhile, the test spectrum data of the test signal converted by the frequency spectrograph is a digital sequence.
And S15, carrying out digital filtering on the test frequency spectrum data to obtain the test filtering signal.
Through the steps, the standard frequency spectrum data are directly adopted, and the test signal is converted into the frequency spectrum data, so that the smooth comparison and analysis between the test frequency spectrum data and the standard frequency spectrum data are ensured, and the preprocessing process of the test filtering signal and the standard filtering signal is simplified. Therefore, the time delay of the distortion analysis of the test signal sent by the spacecraft is reduced, and the real-time performance of the analysis of the test signal of the spacecraft is better ensured. Meanwhile, the digital filtering of the test spectrum data and the standard spectrum data can ensure that redundant and unnecessary interference is removed, the beneficial effect of accelerating the efficiency of the cross-correlation analysis of the subsequent test filtering signal and the standard filtering signal is achieved, and the requirement of real-time analysis of the spacecraft test signal is further met.
As shown in fig. 3, according to one embodiment of the invention, a cross-correlation analysis is performed on the standard filtered signal and the test filtered signal. In this embodiment, the step of performing cross-correlation analysis on the standard filtered signal and the test filtered signal further includes:
s21, receiving the standard filtering signal generated in the previous step, and performing FFT (fast Fourier transform algorithm) calculation on the standard filtering signal to obtain first result data, wherein X is used for obtaining the first result data1(ω) represents;
s22, receiving the test filtering signal generated in the previous step, performing FFT calculation on the test filtering signal to obtain second result data, and calculating by X2And (omega) represents. Meanwhile, conjugate calculation is carried out through the obtained second result data to obtain third result data so as to obtain
Represents;
and S23, simultaneously receiving the transmitted first result data and the third result data. In this step, the received first result data and the third result data need to be complex multiplied to obtain the fourth result data, which is denoted by G12(ω) represents;
in this step, the fourth result data satisfies the following formula:
wherein: x1(omega) representsFirst result data;
representing third result data; g12(ω) represents the fourth result data.
And S24, carrying out frequency domain PHAT weighting calculation on the fourth result data to obtain fifth result data. In the embodiment, the fourth result data is further filtered by weighting the fourth result data in the frequency domain, so that clutter influence in the fourth result data is suppressed, the fourth result data is large in dynamic range, wide in frequency band and high in sensitivity, and the accuracy of a result in a subsequent analysis process is further effectively improved. Particularly for the spacecraft, the interference of irrelevant signals is effectively avoided by improving the accuracy of the subsequent analysis process, and the spacecraft state information can be timely and accurately acquired and accurately controlled.
In this step, a frequency domain PHAT weighting factor needs to be obtained in the process of performing frequency domain PHAT weighting calculation on the fourth result data, and the expression of the PHAT weighting factor is as follows:
wherein psi12(ω) represents a PHAT weighting factor; g12(ω) represents the fourth result data.
And S25, analyzing the fifth result data.
In this embodiment, the step of analyzing the fifth result data includes:
s251, performing IFFT calculation on the fifth result data to obtain sixth result data (R is used for the sixth result data)12(τ) and modulo the sixth result data to obtain seventh result data.
In this step, the sixth result data satisfies the following formula:
wherein R is12(τ) represents sixth result data; psi12(ω) represents a PHAT weighting factor; g12(ω) represents the fourth result data.
In the present embodiment, the deviation of the fifth result data obtained by performing frequency domain PHAT weighting on the fourth result data is small, and the accuracy of the sixth result data obtained by performing IFFT calculation on the fifth result data is high, so that the seventh result data can be obtained more accurately.
And S252, acquiring the maximum value in the seventh result data and comparing the maximum value with a set threshold value.
Through the steps, the error in the IFFT calculation of the fifth result data is reduced by carrying out frequency domain weighting on the fourth result data, so that the error of the sixth result data is small, and the accuracy of obtaining the seventh result data is further effectively improved. By the method, in the process of testing the test signal sent by the spacecraft, the accuracy of the result data obtained in the analysis process is improved, so that the method is beneficial to acquiring the operation state information of the spacecraft in real time and accurately controlling the spacecraft. Meanwhile, the accuracy of the analysis result is improved, the influence of other irrelevant signals on the analysis result is avoided, and the misjudgment of the analysis method on the real-time state of the spacecraft is avoided. By taking the modulus of the seventh result data and obtaining the maximum value and comparing the maximum value with the threshold value, each value in the seventh result data does not need to be compared with the threshold value, the complexity of the analysis process of the invention is effectively reduced, the analysis process is simplified, the precision and the reliability of the analysis method of the invention are ensured, and the real-time analysis capability of the clear analysis method is further improved.
As shown in fig. 2, the step of outputting the analysis result by the output device according to a real-time mode of the present invention further includes:
and S31, displaying the maximum value in the seventh result data through an output device. In the present real-time mode, the maximum value in the seventh result data is displayed in a graph mode. The seventh result data can be displayed intuitively by using the curve mode for displaying, the displayed curve is favorably observed intuitively by a user, and the identification degree is improved. In the real-time mode, the output device displays the presentation information when the maximum value in the seventh result data is smaller than the set threshold value. By the method, the distortion signal generated by the user can be timely found when the user observes the displayed curve, the missing judgment of the distortion signal is avoided, and the user can be further ensured to timely obtain the state information of the spacecraft.
By the mode, the analysis method provided by the invention is used for replacing manual work to complete the analysis of the test signal, and automatically reminding a user when the test signal is distorted, so that the test automation degree is improved. By the analysis method, the test signals sent by the spacecraft are subjected to quantitative visual display, and the influence of subjective factors of a user on the judgment result of the test signals is avoided by comparing the test signals with the set threshold value. By means of sending prompt information to remind the user, the condition of missed judgment caused by factors such as fatigue and the like under the condition that the user monitors for a long time is avoided. By the analysis method, the multi-channel signal spectrum distortion can be analyzed in real time, the workload of manual analysis is reduced, various state information of the working state of the spacecraft can be further obtained by a user in real time, and the normal operation of the spacecraft is ensured.
According to the real-time mode, the acquired test frequency spectrum data is stored in the ground storage device, so that the rapid reading in the subsequent analysis process is ensured, the whole analysis method only needs to convert the test signal in the frequency spectrograph once, and the analysis efficiency of the subsequent steps of the whole analysis method is improved. Meanwhile, the maximum value in the obtained seventh result data is stored, so that the distortion signal in the test signal can be analyzed by the user, the analysis efficiency of the test signal in the real-time analysis process is improved, other users can extract and analyze the distortion reason of the test signal, the influence among different users is avoided, and the real-time performance of the whole analysis method is further improved.
The foregoing is illustrative of specific embodiments of the present invention and reference should be made to the implementation of apparatus and structures not specifically described herein, which is understood to be a general purpose apparatus and method of operation known in the art.
The above description is only one embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A method of distortion analysis of an aerospace telemetry signal, comprising:
s1, acquiring a standard filtering signal and a test filtering signal;
s2, performing cross-correlation analysis on the standard filtering signal and the test filtering signal;
s3, outputting an analysis result by an output device,
wherein the step of performing a cross-correlation analysis on the standard filtered signal and the test filtered signal comprises:
s21, performing FFT calculation on the standard filtering signal to obtain first result data;
s22, carrying out FFT calculation on the test filtering signal to obtain second result data, and carrying out conjugate calculation on the second result data to obtain third result data;
s23, carrying out complex multiplication on the first result data and the third result data to obtain fourth result data;
s24, performing frequency domain weighting calculation on the fourth result data to obtain fifth result data;
s25, analyzing the fifth result data;
s251, performing IFFT calculation on the fifth result data to obtain sixth result data, and performing modulus extraction on the sixth result data to obtain seventh result data;
and S252, acquiring the maximum value in the seventh result data and comparing the maximum value with a set threshold value.
2. A distortion analysis method as set forth in claim 1, wherein the step of obtaining the standard filtered signal comprises:
s11, acquiring standard frequency spectrum data from a ground data source;
and S12, carrying out digital filtering on the standard frequency spectrum data to obtain the standard filtering signal.
3. A distortion analysis method as set forth in claim 2, wherein the step of obtaining the test filtered signal comprises:
s13, collecting a test signal sent by the spacecraft;
s14, obtaining test frequency spectrum data of the test signal;
and S15, carrying out digital filtering on the test frequency spectrum data to obtain the test filtering signal.
4. A distortion analysis method as set forth in claim 3, wherein the acquired test spectrum data is a digital sequence.
5. A distortion analysis method as set forth in claim 1, wherein the step of outputting the analysis result by the output device further comprises:
and S31, displaying the maximum value in the seventh result data through the output device.
6. A distortion analyzing method as set forth in claim 5, wherein the output means displays a prompt message when the maximum value in the seventh result data is smaller than a set threshold value.
7. A distortion analyzing method as set forth in claim 3, wherein the acquired test spectrum data is stored, and a maximum value among the acquired seventh result data is stored.
8. A distortion analysis method as set forth in claim 5, wherein the maximum value in the seventh result data is displayed in a curved manner.
9. A distortion analysis method as set forth in claim 3, wherein the test signal is converted into test spectral data by a spectrometer having a spectral data output interface.
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