CN107907738A - The distortion analysis method of space telemetry signal - Google Patents
The distortion analysis method of space telemetry signal Download PDFInfo
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- CN107907738A CN107907738A CN201711023900.8A CN201711023900A CN107907738A CN 107907738 A CN107907738 A CN 107907738A CN 201711023900 A CN201711023900 A CN 201711023900A CN 107907738 A CN107907738 A CN 107907738A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R23/00—Arrangements for measuring frequencies; Arrangements for analysing frequency spectra
- G01R23/16—Spectrum analysis; Fourier analysis
- G01R23/165—Spectrum analysis; Fourier analysis using filters
- G01R23/167—Spectrum analysis; Fourier analysis using filters with digital filters
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Abstract
The present invention relates to a kind of distortion analysis method of space telemetry signal, including：S1. standard filtering signal and test filtering signal are obtained；S2. cross-correlation analysis is carried out to the standard filtering signal and the test filtering signal；S3. output device output analysis result, by directly using standard frequency spectrum data, and test signal is converted into frequency spectrum data and is analyzed so as to ensure that to be smoothed out comparing between test frequency spectrum data and standard frequency spectrum data, simplify processing procedure early period of test filtering signal and standard filtering signal.So as to be conducive to reduce the time delay of the test signal distortion analysis sent to spacecraft, the real-time to spacecraft-testing signal analysis preferably ensure that.
Description
Technical field
The present invention relates to a kind of distortion analysis method of telemetered signal, more particularly to it is a kind of for the abnormal of space telemetry signal
Become analysis method.
Background technology
Need to establish radio frequency link between spacecraft and ground checkout equipment during spacecraft-testing, pass through rf chain
Telecommand, telemetry, image voice data etc. are transmitted in road between spacecraft and ground, in order to find in time on spacecraft
Or ground installation sends radiofrequency signal exception, and because the disturbing factors such as multipath effect are led under spacecraft wireless status test mode
The states such as radiofrequency signal is unstable between the spacecraft of cause and ground to the frequency spectrum of radio frequency link, it is necessary to carry out monitoring analysis.Currently
In spacecraft integration test, generally use frequency spectrograph receives radiofrequency signal, and the frequency spectrum to being obtained after processing shows, surveys
Examination personnel monitor that the display page of frequency spectrograph carries out frequency spectrum and analyzes in real time, and the result of this manual analysis is inevitably subject to
The influence of factor and individual subjective factor, and there is a situation where fail to judge during long-time monitors.When signal spectrum distortion continues
Time is short, is difficult often to find in the case that distortion degree is small, is only applicable to signal spectrum and distorts more apparent and stablize what is occurred
When.
In addition, in spacecraft-testing, as the increase of spacecraft TTC channel is, it is necessary to which the radiofrequency signal monitored at the same time is got over
Come it is more, current manual analysis method can only select wherein to monitor all the way, or continually switching monitoring, heavy workload, and
It can not realize the real-time analysis of multiple signals.
For example, Authorization Notice No. is CN103869334B, entitled " automatic identification of GNSS spacing waves distortion and processing
The patent of invention of method " discloses a kind of scheme.Wherein, signal distortion model library is initially set up, secondly, to utilizing data acquisition
The satellite navigation signals of card collection are analyzed and processed, and then, establish signal analysis comparison model storehouse, finally, establish distortion letter
Number model library.Satellite-signal is analyzed and processed in this programme, and carries out the distortion class that repeatedly contrast determines satellite-signal
Type etc., causes the processing procedure of whole process extremely complex, further results in analysis result display delay, be unfavorable for spacecraft
Signal carry out in real time monitor and analyze.
The content of the invention
It is an object of the invention to provide a kind of distortion analysis method of space telemetry signal, solves signal distortion analysis and prolongs
The problem of slow.
For achieving the above object, the present invention provides a kind of distortion analysis method of space telemetry signal, including：
S1. standard filtering signal and test filtering signal are obtained；
S2. cross-correlation analysis is carried out to the standard filtering signal and the test filtering signal；
S3. output device output analysis result,
Wherein, the step of carrying out cross-correlation analysis to the standard filtering signal and the test filtering signal includes：
S21. FFT is carried out to the standard filtering signal and the first result data is calculated；
S22. FFT is carried out to the test filtering signal and the second result data is calculated, and to second number of results
The 3rd result data is calculated according to conjugation is carried out；
S23. first result data and the 3rd result data complex multiplication are drawn into the 4th result data；
S24. frequency domain weighting is carried out to the 4th result data and the 5th result data is calculated；
S25. the 5th result data is analyzed.
According to an aspect of the present invention, the step of analyzing the 5th result data includes：
S251. IFFT is carried out to the 5th result data and the 6th result data is calculated, and to the 6th result
Data carry out modulus and obtain the 7th result data；
S252. obtain the maximum in the 7th result data and with the threshold value comparison of setting.
According to an aspect of the present invention, the step of obtaining the standard filtering signal includes：
S11. standard frequency spectrum data are obtained from ground data source；
S12. digital filtering is carried out to the standard frequency spectrum data and obtains the standard filtering signal.
According to an aspect of the present invention, the step of obtaining the test filtering signal includes：
S13. the test signal that spacecraft is sent is gathered；
S14. the test frequency spectrum data of the test signal is obtained；
S15. digital filtering is carried out to the test frequency spectrum data, obtains the test filtering signal.
According to an aspect of the present invention, the test frequency spectrum data of acquisition is Serial No..
According to an aspect of the present invention, the step of output device output analysis result further comprises：
S31. the maximum in the 7th result data is shown by the output device.
According to an aspect of the present invention, it is described defeated when the maximum in the 7th result data is less than the threshold value of setting
Go out device display reminding information.
According to an aspect of the present invention, the test frequency spectrum data of acquisition is stored, and the 7th result data will be obtained
In maximum storage.
According to an aspect of the present invention, the maximum in the 7th result data is shown by curve mode.
According to an aspect of the present invention, the test signal is changed by the frequency spectrograph with frequency spectrum data output interface
To test frequency spectrum data.
A scheme according to the present invention, is converted into by directly using standard frequency spectrum data, and by test signal
Frequency spectrum data can be smoothed out comparing analysis so as to ensure that between test frequency spectrum data and standard frequency spectrum data, simplify survey
Try processing procedure early period of filtering signal and standard filtering signal.It is abnormal to the test signal of spacecraft transmission so as to be conducive to reduce
Become the time delay of analysis, preferably ensure that the real-time to spacecraft-testing signal analysis.Meanwhile to testing frequency spectrum data
Carrying out digital filtering with standard frequency spectrum data can ensure to remove wherein unnecessary and unwanted interference, to accelerating follow-up test filter
The efficiency of ripple signal and standard filtering signal cross-correlation analysis plays beneficial effect.Further reach to spacecraft-testing signal
The requirement analyzed in real time.
A scheme according to the present invention, by carrying out frequency domain weighting to the 4th result data, is realized to the 4th number of results
According to further filtering, it is suppressed that the clutter in the 4th result data influences, while causes the 4th result data dynamic range greatly, frequently
Bandwidth, high sensitivity, further effectively increase the accuracy of the result during subsequent analysis.Particularly with spacecraft
Speech, by improving the accuracy of subsequent analysis process, effectively avoids the interference of uncorrelated signal, is more conducive to timely and accurate
Ground obtains the status information of space flight, and the accurate control to spacecraft.
A scheme according to the present invention, the 5th number of results is allowed to carry out by carrying out frequency domain weighting to the 4th result data
Error in being calculated according to IFFT reduces, so that the error of the 6th result data is small, further effectively increases and obtains the 7th knot
The accuracy of fruit data.By the above-mentioned means, during testing the test signal that spacecraft is sent, pass through raising
The accuracy for the data result that analytic process obtains, is conducive to obtain the running state information of space flight in real time, and to spacecraft
Accurate control.Meanwhile raising precision of analysis also helps and avoids shadow of other uncorrelated signals to analysis result
Ring, avoid erroneous judgement of the analysis method of the present invention to spacecraft real-time status.By to the 7th result data modulus and obtaining
Maximum and threshold value comparison therein, it is not necessary to each value and threshold value comparison in the 7th result data, effectively reduce
The complexity of the analytic process of the present invention, simplifies analytic process, also ensure that the precision of the analysis method of the present invention and reliable
Property, further increase an ability analyzed in real time of clearly demarcated analysis method.
A scheme according to the present invention, shown by using curve mode enable the 7th result data intuitively by
Show, be conducive to user and intuitively the curve of display is observed, improve identification.In this real-time mode, when
When maximum in seven result datas is less than the threshold value of setting, output device display reminding information.In this way, further
User be ensure that when the curve to display is observed, the distorted signal produced can be found in time, avoid and distortion is believed
Number fail to judge, be further ensured that user can obtain the status information of spacecraft in time.
A scheme according to the present invention, replaces being accomplished manually dividing test signal using the analysis method of the present invention
Analysis, and the automatically prompting user when test signal distorts, improve test automation degree.Pass through the analysis side of the present invention
Method, the test signal that spacecraft is sent carry out quantification and intuitively show, and by being avoided compared with the threshold value of setting
The influence of differentiation result of the subjective factor of user to test signal.By way of sending prompt message and reminding user, keep away
Exempt from situation of failing to judge under user's long-time monitored state caused by the factor such as fatigue., can be at the same time by the analysis method of the present invention
Multiple signals Spectrum Distortion is analyzed in real time, reduces the workload of manual analysis, further such that user is to spacecraft
Every status information of working status can obtain in real time, ensure that the normal operation of spacecraft.
Brief description of the drawings
Fig. 1 schematically shows a kind of flow of the cross-correlation analysis method of the signal distortion of embodiment according to the present invention
Figure；
Fig. 2 schematically shows a kind of flow of the cross-correlation analysis method of the signal distortion of embodiment according to the present invention
Figure；
Fig. 3 schematically shows the mutual of the cross-correlation analysis method of the signal distortion of another embodiment according to the present invention
Correlation analysis flow chart.
Embodiment
, below will be to embodiment in order to illustrate more clearly of embodiment of the present invention or technical solution of the prior art
Needed in attached drawing be briefly described.It should be evident that drawings in the following description are only some of the present invention
Embodiment, for those of ordinary skills, without creative efforts, can also be according to these
Attached drawing obtains other attached drawings.
When being described for embodiments of the present invention, term " longitudinal direction ", " transverse direction ", " on ", " under ", " preceding ",
" rear ", "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", the orientation expressed by " outer " or position relationship are to be based on phase
Orientation shown in the drawings or position relationship are closed, it is for only for ease of the description present invention and simplifies description, rather than instruction or dark
Show that the device of meaning or element there must be specific orientation, with specific azimuth configuration and operation, therefore above-mentioned term cannot
It is interpreted as limitation of the present invention.
The present invention is described in detail with reference to the accompanying drawings and detailed description, embodiment cannot go to live in the household of one's in-laws on getting married one by one herein
State, but therefore embodiments of the present invention are not defined in implementation below.
As shown in Figure 1, a kind of embodiment according to the present invention, the distortion analysis of space telemetry signal according to the present invention
Method, including：
S1. standard filtering signal and test filtering signal are obtained；
S2. cross-correlation analysis is carried out to the standard filtering signal and the test filtering signal；
S3. output device output analysis result.
As shown in Fig. 2, a kind of embodiment, the acquisition of standard filtering signal are needed by following step according to the present invention
Suddenly：
S11. standard frequency spectrum data are obtained from ground data source, standard frequency spectrum number is Serial No..
Ground data source is stored with the standard frequency spectrum data of standard, by the standard frequency spectrum data in the data source of ground into
Row reading can be obtained conveniently.
S12. digital filtering is carried out to standard frequency spectrum data and obtains standard filtering signal.
As shown in Fig. 2, a kind of embodiment according to the present invention, testing the acquisition of filtering signal needs by following step
Suddenly：
S13. the test signal that spacecraft is sent is gathered；
In the present embodiment, by establishing radio frequency link between ground and spacecraft, received and navigated by radio frequency link
The test signal that its device is sent.
S14. the test frequency spectrum data of the test signal is obtained, test frequency spectrum data is Serial No.；
In the present embodiment, by the test signal input spectrum instrument received, will be tested by the effect of frequency spectrograph
Signal is converted to test frequency spectrum data.In the present embodiment, test signal passes through the frequency spectrum with frequency spectrum data output interface
Instrument is converted to test frequency spectrum data.Meanwhile the test frequency spectrum data that test signal is converted into by frequency spectrograph is Serial No..
S15. digital filtering is carried out to test frequency spectrum data, obtains the test filtering signal.
By above-mentioned steps, frequency spectrum data is converted into by directly using standard frequency spectrum data, and by test signal
It can be smoothed out comparing analysis between test frequency spectrum data and standard frequency spectrum data so as to ensure that, simplify test filtering letter
Number and standard filtering signal processing procedure early period.So as to be conducive to reduce the test signal distortion analysis sent to spacecraft
Time delay, preferably ensure that the real-time to spacecraft-testing signal analysis.Meanwhile to test frequency spectrum data and standard frequency
Modal data, which carries out digital filtering, can ensure to remove wherein unnecessary and unwanted interference, to accelerate follow-up test filtering signal and
The efficiency of standard filtering signal cross-correlation analysis plays beneficial effect, has further reached and spacecraft-testing signal is carried out in real time
The requirement of analysis.
As shown in figure 3, a kind of embodiment according to the present invention, carries out standard filtering signal and test filtering signal mutual
Correlation analysis.In the present embodiment, the step of carrying out cross-correlation analysis to standard filtering signal and test filtering signal is into one
Step includes：
S21. the standard filtering signal generated in previous step is received, and FFT (discrete Fouriers are carried out to standard filtering signal
The fast algorithm of conversion) the first result data is calculated, with X1(ω) is represented；
S22. the test filtering signal generated in previous step is received, and FFT is carried out to test filtering signal and is calculated
Second result data, with X2(ω) is represented.Meanwhile by the second result data of acquisition, carry out conjugation and the 3rd knot is calculated
Fruit data, withRepresent；
S23. the first result data and the 3rd result data being transmitted are received at the same time.In this step, it is necessary to receiving
The first result data and the 3rd result data carry out complex multiplication draw the 4th result data, with G12(ω) is represented；
In this step, the 4th result data meets the following formula：
Wherein：X1(ω) represents the first result data；Represent the 3rd result data；G12(ω) represents the 4th result
Data.
S24. frequency domain PHAT weighted calculations are carried out to the 4th result data and draws the 5th result data.In present embodiment
In, by carrying out frequency domain weighting to the 4th result data, realize and the 4th result data is further filtered, it is suppressed that the 4th result
Clutter in data influences, while make it that the 4th result data dynamic range is big, bandwidth, high sensitivity, further effectively carries
The accuracy of result during high subsequent analysis.For spacecraft, by the standard for improving subsequent analysis process
True property, effectively avoids the interference of uncorrelated signal, is more conducive to the status information for timely and accurately obtaining space flight, and right
The accurate control of spacecraft.
In this step, need to show that PHAT is weighted during carrying out frequency domain PHAT weighted calculations to the 4th result data
The factor, the expression formula of PHAT weighted factors are：
Wherein, ψ12(ω) represents PHAT weighted factors；G12(ω) represents the 4th result data.
S25. the 5th result data is analyzed.
In the present embodiment, the step of analyzing the 5th result data includes：
S251. the 6th result data being calculated to the 5th result data progress IFFT, (the 6th result data is with R12(τ) table
Show), and modulus is carried out to the 6th result data and obtains the 7th result data.
In this step, the 6th result data meets the following formula：
Wherein, R12(τ) represents the 6th result data；ψ12(ω) represents PHAT weighted factors；G12(ω) represents the 4th result
Data.
In the present embodiment, the deviation for the 5th result data that frequency domain PHAT is weighted is carried out to the 4th result data
Small, the accuracy for the 6th result data for the 5th result data obtain after IFFT calculating is high, so as to more accurately
Obtain the 7th result data.
S252. obtain the 7th result data in maximum and with the threshold value comparison of setting.
By above-mentioned steps, the 5th result data IFFT meters are allowed to carry out by carrying out frequency domain weighting to the 4th result data
Error in calculation reduces, so that the error of the 6th result data is small, further effectively increases and obtains the 7th result data
Accuracy.By the above-mentioned means, during testing the test signal that spacecraft is sent, by improving analytic process
The accuracy of obtained result data, is conducive to obtain the running state information of space flight, and the accurate control to spacecraft in real time
System.Meanwhile raising precision of analysis also helps and avoids other influences of the uncorrelated signal to analysis result, avoids
Erroneous judgement of the analysis method of the present invention to spacecraft real-time status.By to the 7th result data modulus and obtaining maximum therein
Value and threshold value comparison, it is not necessary to each value and threshold value comparison in the 7th result data, effectively reduce dividing for the present invention
The complexity of analysis process, simplifies analytic process, also ensure that the precision and reliability of the analysis method of the present invention, further carries
The high ability analyzed in real time of this clearly demarcated analysis method.
As shown in Fig. 2, according to the present invention a kind of real-time mode, output device output analysis result the step of further wrap
Include：
S31. the maximum in the 7th result data is shown by output device.In this real-time mode, the 7th knot
Maximum in fruit data is shown by curve mode.Shown by using curve mode and enable the 7th result data
Intuitively it is demonstrated out, is conducive to user and intuitively the curve of display is observed, improve identification.In this real-time mode
In, when the maximum in the 7th result data is less than the threshold value of setting, output device display reminding information.Pass through this side
Formula, further ensures user when the curve to display is observed, and can find the distorted signal produced in time, avoid
Fail to judge to distorted signal, be further ensured that user can obtain the status information of spacecraft in time.
In this way, the analysis being accomplished manually to test signal is substituted using the analysis method of the present invention, and is worked as
Automatically prompting user when test signal distorts, improves test automation degree.By the analysis method of the present invention, by space flight
The test signal that device is sent carries out quantification and intuitively shows, and by avoiding the master of user compared with the threshold value of setting
The influence of differentiation result of the sight factor to test signal.By way of sending prompt message and reminding user, when avoiding using the head of a household
Between fail to judge caused by the factor such as fatigue under monitored state situation., can be at the same time to multiple signals by the analysis method of the present invention
Spectrum Distortion is analyzed in real time, reduces the workload of manual analysis, further such that user is to the working status of spacecraft
Every status information can obtain in real time, ensure that the normal operation of spacecraft.
A kind of real-time mode according to the present invention, the test frequency spectrum data of acquisition is deposited in the storage device on ground
Storage, so as to can quickly be read during ensureing subsequent analysis, makes whole analysis method only need test signal of progress to exist
The conversion of frequency spectrograph, so as to improve the analysis efficiency of whole analysis method subsequent step.At the same time by the 7th number of results of acquisition
Maximum storage in, analyzes the distorted signal in test signal so as to be conducive to user, so sets and not only carries
It is high in real-time analytic process to the analysis efficiency of test signal, it is ensured that other users can put forward test signal
Analysis distortion reason is taken, the influence between different user is avoided, further increases the real-time of whole analysis method.
The above is only enumerating for the concrete scheme of the present invention, should for the equipment and structure of wherein not detailed description
When being interpreted as taking the existing common apparatus in this area and universal method to be practiced.
The foregoing is merely the scheme of the present invention, it is not intended to limit the invention, for the technology of this area
For personnel, the invention may be variously modified and varied.Within the spirit and principles of the invention, that is made any repaiies
Change, equivalent substitution, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of distortion analysis method of space telemetry signal, including：
S1. standard filtering signal and test filtering signal are obtained；
S2. cross-correlation analysis is carried out to the standard filtering signal and the test filtering signal；
S3. output device output analysis result,
Wherein, the step of carrying out cross-correlation analysis to the standard filtering signal and the test filtering signal includes：
S21. FFT is carried out to the standard filtering signal and the first result data is calculated；
S22. FFT is carried out to the test filtering signal and is calculated the second result data, and to second result data into
The 3rd result data is calculated in row conjugation；
S23. first result data and the 3rd result data complex multiplication are drawn into the 4th result data；
S24. frequency domain weighting is carried out to the 4th result data and the 5th result data is calculated；
S25. the 5th result data is analyzed.
2. distortion analysis method according to claim 1, it is characterised in that analyzed the 5th result data
Step includes：
S251. IFFT is carried out to the 5th result data and the 6th result data is calculated, and to the 6th result data
Carry out modulus and obtain the 7th result data；
S252. obtain the maximum in the 7th result data and with the threshold value comparison of setting.
3. distortion analysis method according to claim 2, it is characterised in that the step of obtaining the standard filtering signal is wrapped
Include：
S11. standard frequency spectrum data are obtained from ground data source；
S12. digital filtering is carried out to the standard frequency spectrum data and obtains the standard filtering signal.
4. distortion analysis method according to claim 3, it is characterised in that the step of obtaining the test filtering signal is wrapped
Include：
S13. the test signal that spacecraft is sent is gathered；
S14. the test frequency spectrum data of the test signal is obtained；
S15. digital filtering is carried out to the test frequency spectrum data, obtains the test filtering signal.
5. distortion analysis method according to claim 4, it is characterised in that the test frequency spectrum data of acquisition is numeral
Sequence.
6. distortion analysis method according to claim 2, it is characterised in that the step of the output device output analysis result
Suddenly further comprise：
S31. the maximum in the 7th result data is shown by the output device.
7. distortion analysis method according to claim 6, it is characterised in that when the maximum in the 7th result data is less than
During the threshold value of setting, the output device display reminding information.
8. distortion analysis method according to claim 4, it is characterised in that the test frequency spectrum data of acquisition is stored, with
And the maximum obtained in the 7th result data is stored.
9. distortion analysis method according to claim 6, it is characterised in that the maximum in the 7th result data is led to
Curve mode is crossed to be shown.
10. distortion analysis method according to claim 4, it is characterised in that the test signal passes through with spectrum number
Test frequency spectrum data is converted to according to the frequency spectrograph of output interface.
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10062571C1 (en) * | 2000-12-15 | 2002-05-16 | Infineon Technologies Ag | Simulation method for determining non-linear signal attenuation of tested analogue circuit has digital filter adjusted until it simulates analogue circuit with measurement of its intermodulation product |
| EP1819039A1 (en) * | 2006-02-14 | 2007-08-15 | Fujitsu Ltd. | Distortion compensating apparatus and method |
| CN102662106A (en) * | 2012-05-30 | 2012-09-12 | 重庆市电力公司长寿供电局 | Method for measuring electric energy of harmonic power network |
| CN104459398A (en) * | 2014-12-08 | 2015-03-25 | 东北电力大学 | Electric energy quality complex disturbance recognition method for lowering noise through two-dimensional morphology |
| CN106053976A (en) * | 2016-04-19 | 2016-10-26 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Civil aircraft variable-frequency power supply system power quality detection and analysis system and method |
| CN106771728A (en) * | 2016-12-03 | 2017-05-31 | 中国航空工业集团公司北京长城计量测试技术研究所 | A kind of uncertainty analysis method of distressed spectrum calibration result |
| CN109188332A (en) * | 2018-09-13 | 2019-01-11 | 中国航空工业集团公司北京长城计量测试技术研究所 | A kind of DC voltage distressed spectrum generating device and working method |
-
2017
- 2017-10-27 CN CN201711023900.8A patent/CN107907738B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10062571C1 (en) * | 2000-12-15 | 2002-05-16 | Infineon Technologies Ag | Simulation method for determining non-linear signal attenuation of tested analogue circuit has digital filter adjusted until it simulates analogue circuit with measurement of its intermodulation product |
| EP1819039A1 (en) * | 2006-02-14 | 2007-08-15 | Fujitsu Ltd. | Distortion compensating apparatus and method |
| CN102662106A (en) * | 2012-05-30 | 2012-09-12 | 重庆市电力公司长寿供电局 | Method for measuring electric energy of harmonic power network |
| CN104459398A (en) * | 2014-12-08 | 2015-03-25 | 东北电力大学 | Electric energy quality complex disturbance recognition method for lowering noise through two-dimensional morphology |
| CN106053976A (en) * | 2016-04-19 | 2016-10-26 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Civil aircraft variable-frequency power supply system power quality detection and analysis system and method |
| CN106771728A (en) * | 2016-12-03 | 2017-05-31 | 中国航空工业集团公司北京长城计量测试技术研究所 | A kind of uncertainty analysis method of distressed spectrum calibration result |
| CN109188332A (en) * | 2018-09-13 | 2019-01-11 | 中国航空工业集团公司北京长城计量测试技术研究所 | A kind of DC voltage distressed spectrum generating device and working method |
Non-Patent Citations (1)
| Title |
|---|
| 刘鹏: "地球指向镜图像畸变分析与研究", 《中国优秀硕士学位论文全文数据库信息科技辑》 * |
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