CN114088274A - Amplitude-phase comprehensive correlation identification method for bending moment identification of helicopter main shaft - Google Patents
Amplitude-phase comprehensive correlation identification method for bending moment identification of helicopter main shaft Download PDFInfo
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Abstract
A method for amplitude-phase comprehensive correlation identification of bending moment identification of a main shaft of a helicopter, comprising the following steps of: measuring original data of section bending moment of a rotor wing spindle of a helicopter, and performing harmonic analysis on the original data of the section bending moment of the rotor wing spindle to obtain an amplitude sequence and a phase sequence; respectively calculating the Pearson product moment correlation coefficient of the amplitude sequence of the first-order harmonic components of any two test channels and the Pearson product moment correlation coefficient of the phase sequence; respectively carrying out arithmetic mean calculation on the Pearson product moment correlation coefficient of the amplitude sequence and the Pearson product moment correlation coefficient of the phase sequence to obtain an amplitude correlation coefficient arithmetic mean and a phase correlation coefficient arithmetic mean; multiplying the arithmetic mean of the amplitude correlation coefficient and the arithmetic mean of the phase correlation coefficient to obtain the amplitude-phase comprehensive correlation coefficient r of the two test channelsFψ(ii) a According to amplitude-phase comprehensive correlation coefficient rFψAnd judging whether the bending moment identifications of the two test channels are accurate or not.
Description
Technical Field
The invention is used for the field of helicopter test data analysis, and particularly relates to an amplitude-phase comprehensive correlation identification method for helicopter main shaft bending moment identification.
Background
With the development of modern test sensor performance, test methods and inspection technologies, the required main shaft bending moment can be accurately measured, the load on the main shaft of the rotor wing of the helicopter and the heading force, the lateral force, the pitching bending moment and the rolling bending moment of the hub center are obtained, and the method is used for real-time monitoring and evaluation of main shaft load threshold, main shaft service life evaluation, flight safety control and the like. Meanwhile, the measuring end points of the bending moment of the main shaft are very many, so that the phenomenon of false identification is easily caused. If measurement identification errors occur, misleading result data and characteristic analysis and subsequent multi-dimensional application bring direct technical hidden dangers and risks to flight safety and new aircraft development. In the technical development process of helicopters, people develop and form some measurement mark authenticity identification methods, and the methods are generally applied to helicopters before starting flight tests. Once the flight test is initiated, the limitations of these methods in terms of efficiency and effectiveness present difficulties and challenges to the test data verification.
Disclosure of Invention
The application provides a method for comprehensively identifying amplitude-phase correlation of bending moment marks of a main shaft of a helicopter, which can accurately discriminate the bending moment measuring marks of the main shaft of the helicopter and ensure the validity and the accuracy of the bending moment measuring data of the main shaft.
The technical scheme is as follows: a method for amplitude-phase comprehensive correlation identification of bending moment identification of a main shaft of a helicopter, comprising the following steps of:
measuring original data of section bending moment of a rotor wing spindle of a helicopter, and performing harmonic analysis on the original data of the section bending moment of the rotor wing spindle to obtain an amplitude sequence and a phase sequence;
respectively calculating the Pearson product moment correlation coefficient of the amplitude sequence of the first-order harmonic components of any two test channels and the Pearson product moment correlation coefficient of the phase sequence;
respectively carrying out arithmetic mean calculation on the Pearson product moment correlation coefficient of the amplitude sequence and the Pearson product moment correlation coefficient of the phase sequence to obtain an amplitude correlation coefficient arithmetic mean and a phase correlation coefficient arithmetic mean;
multiplying the arithmetic mean of the amplitude correlation coefficient and the arithmetic mean of the phase correlation coefficient to obtain the amplitude-phase comprehensive correlation coefficient r of the two test channelsFψ；
According to amplitude-phase comprehensive correlation coefficient rFψAnd judging whether the bending moment identifications of the two test channels are accurate or not.
Specifically, it is right rotor main shaft cross-section bending moment raw data carries out harmonic analysis, obtains amplitude sequence and phase sequence, includes:
and carrying out n whole-period data sequences of the amplitude and the phase of the front k-order harmonic component of 4 measurement channels of the helicopter rotor main shaft on the original data of the section bending moment of the rotor main shaft.
Specifically, 4 measurement channels of helicopter rotor main shaft are two directions of mutually quadrature in two parallel cross-sections with helicopter rotor main shaft, namely cross-section IN direction, cross-section IP direction, cross-section IIN direction and cross-section IIP direction, 4 measurement channels that correspond.
Specifically, the calculation process of the n whole-period data sequence of the amplitude and the phase of the front k-order harmonic component of the 4 measurement channels of the helicopter rotor main shaft on the original data of the rotor main shaft section bending moment is as follows:
intercepting the number N of sampling points of a rotor wing rotating for one circle of data sequence harmonic waves, a time domain measured amplitude Fj of each point and a relative azimuth angle psi j of each point j according to a rotor wing rotating speed signal, wherein N is a quotient integer obtained for fc/omega, and fc is the sampling frequency of a main shaft bending moment data signal;
performing cosine discrete Fourier transform on each sampling point N to obtain a cosine component Fic of a harmonic wave; and sinusoidal discrete Fourier transform to obtain a sinusoidal component Fis, i of the harmonic wave as a harmonic component order;
and respectively calculating the amplitude Fi of the ith order harmonic quantity and the phase angle psi i thereof in one rotation according to the cosine component Fic and the sine component Fis.
Specifically, calculating the pearson product-moment correlation coefficient of the amplitude sequence of the first-order harmonic component of any two test channels and the pearson product-moment correlation coefficient of the phase sequence respectively includes:
constructing equidistant discrete amplitude data F of any two test channels of main shaftbiAnd equidistant discrete phase data psi of any two test channels of the spindlebi；
Respectively calculating discrete amplitude data F by adopting a Pearson product moment correlation coefficient calculation methodbiAnd discrete phase data ΨbiCalculating the correlation coefficient r of the Pearson product moment of the amplitude sequence of the first-order harmonic component of any two measuring channelsF1biCorrelation coefficient r of Pearson product moment with phase sequenceΨ1bi。
In particular, the amplitude-phase comprehensive correlation coefficient rFψIs a dimensionless quantity, the amplitude is in the range of [ -1,1 [ ]]In the meantime.
In particular, according to the amplitude-phase integrated correlation coefficient rFψThe size of (2) judges whether the bending moment identifications of the two test channels are accurate, and specifically comprises the following steps:
if the amplitude-phase comprehensive correlation coefficient r of two test channelsFψSatisfies the following conditions: r is more than or equal to 0.81Fψ≦ 1.0, then the two test channels are test channels of different cross-sections in the same direction.
Specifically, k is 4 or more.
In summary, the amplitude-phase comprehensive correlation identification method for the bending moment identifier of the main shaft of the helicopter provided by the invention has the following advantages: the identification of the bending moment mark of the main shaft is simply, directly, accurately and intelligently completed by utilizing the correlation between the amplitude and the phase of each order of harmonic wave of different measurement channel data of the bending moment of the main shaft of the helicopter rotor.
Drawings
Fig. 1 is a schematic diagram of a comprehensive amplitude-phase correlation identification method for a bending moment identifier of a main shaft of a helicopter provided by the present application.
Detailed Description
The invention provides a multi-order harmonic amplitude-phase comprehensive related main shaft bending moment identification method based on a big sample, which is applied to discrimination of authenticity of a bending moment measurement identification of a main shaft of a helicopter, validity and accuracy of main shaft bending moment measurement data are ensured, and verification of the method is completed by utilizing actual measurement data of bending moment flight of a main shaft of a certain helicopter. The method provides an efficient and reliable new means and a new choice for discriminating the authenticity of the main shaft bending moment measuring mark, can solve the limitation of the existing identification method, and improves the identification precision of the authenticity of the main shaft bending moment measuring mark. The method can be popularized and applied to intelligent identification of authenticity of the measurement channel marks of the bending moment in the orthogonal direction of the parallel section of a similar rotating structural member and the shimmy and flapping bending moment of different sections of the helicopter blade in the spanwise direction.
The amplitude-phase comprehensive correlation identification method for the bending moment identification of the helicopter main shaft is applied to measurement of the bending moment of the helicopter rotor main shaft. As shown in fig. 1, the measurement of the bending moment of the main shaft of the helicopter rotor is realized by measuring the bending moments in two directions orthogonal to each other in two parallel sections, i.e., the N direction (ln measurement channel) of the section i-i, the P direction (ip measurement channel) of the section i-i, the N direction (ln measurement channel) of the section ii-ii, and the P direction (lp measurement channel) of the section ii-ii, corresponding to 4 measurement channels. The method comprises the steps of firstly carrying out harmonic analysis on original data of 4 measurement channels of a main shaft on the basis of data effectiveness by using original data of section bending moment of a main shaft of a rotor wing measured in scientific research test flight and shaping test flight stages of a helicopter to obtain n whole-period data sequences of amplitude and phase of front 6-order harmonic components of each measurement channel. Secondly, carrying out Pearson product moment coefficient calculation on the amplitude sequence of a certain order harmonic component of any two test channels to obtain the Pearson product moment correlation coefficient of the amplitude of the certain order harmonic component of the two test channels. And thirdly, performing arithmetic mean calculation on the amplitude correlation coefficients of the front k-order harmonic components of the two test channels to obtain the arithmetic mean of the amplitude correlation coefficients of the two test channels. Finally, the same flow and method can calculate the arithmetic mean value of the phase correlation coefficients of the two test channels, multiply the amplitude value with the arithmetic mean value of the phase correlation coefficients to obtain the amplitude-phase comprehensive correlation coefficients of the two test channels, and judge whether the identifiers of the two test channels are accurate according to the amplitude-phase comprehensive correlation coefficients.
The application provides a method for comprehensively identifying amplitude-phase correlation of bending moment marks of a main shaft of a helicopter, which comprises the following steps:
step 10: measuring original data of section bending moment of a rotor main shaft of the helicopter, and carrying out harmonic analysis on the original data of the section bending moment of the rotor main shaft to obtain an amplitude sequence and a phase sequence.
In practical application, the original data of the section bending moment of the rotor main shaft is the original data of the section bending moment of the rotor main shaft measured in the scientific research test flight and shaping test flight stages of the helicopter.
Specifically, it is right rotor main shaft cross-section bending moment raw data carries out harmonic analysis, obtains amplitude sequence and phase sequence, includes: and carrying out n whole-period data sequences of the amplitude and the phase of the front k-order harmonic component of 4 measurement channels of the helicopter rotor main shaft on the original data of the section bending moment of the rotor main shaft.
In practical application, k is greater than or equal to 4.
Specifically, 4 measurement channels of helicopter rotor main shaft are two directions of mutually quadrature in two parallel cross-sections with helicopter rotor main shaft, namely cross-section IN direction, cross-section IP direction, cross-section IIN direction and cross-section IIP direction, 4 measurement channels that correspond.
More specifically, the calculation process of the n whole-period data sequence of the amplitude and the phase of the front k-order harmonic component of 4 measurement channels of the helicopter rotor main shaft on the raw data of the section bending moment of the rotor main shaft is as follows:
step 101: according to the rotor wing rotating speed signal, intercepting the number N of sampling points of one rotation of the rotor wing of the data sequence harmonic wave, the time domain measured amplitude Fj of each point and the relative azimuth angle psi j of each point j, wherein N is the quotient rounding obtained for fc/omega, and fc is the sampling frequency of the main shaft bending moment data signal.
It should be noted that the sampling points N are equally distributed.
Step 102: performing cosine discrete fourier transform on each sampling point N to obtain a cosine component Fic of the harmonic; and performing sinusoidal discrete Fourier transform to obtain a sinusoidal component Fis, i of the harmonic as the order of the harmonic component.
Step 103: and respectively calculating the amplitude Fi of the ith order harmonic quantity and the phase angle psi i thereof in one rotation according to the cosine component Fic and the sine component Fis.
Through the processing, the amplitudes F of different harmonic bending moment components of n rotation periods in the orthogonal direction of the two sections of the main shaft are obtainedbipB represents a measuring channel, namely bending moments measured in two orthogonal directions of two sections, b is 1, 2, 3 and 4, 1 represents the R direction of the section I-I, 2 represents the P direction of the section I-I, 3 represents the R direction of the section II-II, and 4 represents the P direction of the section II-II, wherein the section I-I is parallel to the section II-II, and the R direction and the P direction are in the same section and are orthogonal.
Where i represents the harmonic order, and i is 1, 2, 3, …, k. k is generally not more than 6. And p represents the spindle rotation cycle sequence number in the selected flight test time period, and p is 1, 2, 3, … and n.
Meanwhile, the phases psi of different harmonic bending moment components of n rotation periods in the orthogonal direction of two sections of the main shaft are obtainedbip。
Step 20: respectively calculating the Pearson product moment correlation coefficient of the amplitude sequence of the first-order harmonic components of any two test channels and the Pearson product moment correlation coefficient of the phase sequence;
specifically, step 20 includes:
step 201: constructing equidistant discrete amplitude data F of any two test channels of main shaftbiAnd equally spaced discrete phase data Ψ for any two test channels of the principal axisbi；
See, for example, the discrete amplitude data F of equation (5)biEach set of data has n subsamples, the size of n being determined by the selected flight time period.
In the above formula, FbipIn which is a set of equally spaced amplitude discrete quantities Fbi1、Fbi2、Fki3、…、Fkin。
Step 202: respectively calculating discrete amplitude data F by adopting a Pearson product moment correlation coefficient calculation methodbiAnd discrete phase data ΨbiCalculating the Pearson product moment correlation coefficient r of the amplitude sequence of the first-order harmonic components of any two measurement channelsF1biCorrelation coefficient r of Pearson product moment with phase sequenceΨ1bi。
For example: and (3) performing correlation calculation on the two groups of amplitude discrete quantities when b is 1 and b is 1, 2, 3 and 4 respectively by using the formula (6) and the formula (7), and obtaining an amplitude correlation coefficient array r of each harmonic component of each measurement channel of the selected flight time periodF1bi。
Similarly, a Pearson product-moment correlation coefficient calculation method is adopted to calculate and obtain the Pearson product-moment correlation coefficient of the phase sequence of the first-order harmonic components of any two measurement channels.
For example, calculating to obtain each harmonic component phase correlation coefficient array r of each measurement channel of the selected flight time periodΨ1biSee formula (8).
Step 30: and respectively carrying out arithmetic mean calculation on the Pearson product-moment correlation coefficient of the amplitude sequence and the Pearson product-moment correlation coefficient of the phase sequence to obtain an amplitude correlation coefficient arithmetic mean and a phase correlation coefficient arithmetic mean.
Specifically, according to equation (9), for the pearson product-moment correlation coefficient of the amplitude sequence of the two test channels, for the correlation coefficient value of each row, the arithmetic mean of the correlation coefficient values is obtained, and the arithmetic mean of the amplitude correlation coefficients between any two measurement channels is obtained:
specifically, according to formula (10), for the pearson product-moment correlation coefficient of the two test channel phase sequences, for the correlation coefficient value of each row, the arithmetic mean of the correlation coefficient values is obtained, and the arithmetic mean of the phase correlation coefficients between any two measurement channels is obtained:
step 40: multiplying the arithmetic mean of the amplitude correlation coefficient and the arithmetic mean of the phase correlation coefficient by using a formula (11) to obtain the amplitude-phase comprehensive correlation coefficient r of the two test channelsFψ；
rFψ＝rFbb m×rψbb m (11)
It should be noted that the amplitude-phase integrated correlation coefficient rFψIs oneDimensionless, amplitude range of [ -1,1]In the meantime.
Step 50: according to amplitude-phase comprehensive correlation coefficient rFψAnd judging whether the bending moment identifications of the two test channels are accurate or not.
In particular, if the amplitude-phase integrated correlation coefficient r of two test channelsFψSatisfies the following conditions: r is not less than 0.81Fψ≦ 1.0, then the two test channels are test channels of different cross-sections in the same direction.
And if the root mean square value of the Pearson coefficient of each order of harmonic component amplitude and phase of the two test channels is less than 0.81, the two test channels are the test channels with different sections and in the orthogonal directions. Accordingly, the authenticity identification criterion of the main shaft bending moment measurement channel mark is established and is shown in table 1.
TABLE 1 Authenticity identification criterion for main shaft measuring channel
In summary, the amplitude-phase comprehensive correlation identification method for the bending moment identifier of the main shaft of the helicopter provided by the invention has the following advantages: the identification of the bending moment identification of the main shaft is simply, directly, accurately and intelligently completed by utilizing the correlation between the amplitude and the phase of each order of harmonic wave of different measurement channel data of the bending moment of the main shaft of the helicopter rotor.
Claims (8)
1. A method for amplitude-phase comprehensive correlation identification of bending moment identification of a main shaft of a helicopter is characterized by comprising the following steps:
measuring original data of section bending moment of a rotor wing spindle of a helicopter, and performing harmonic analysis on the original data of the section bending moment of the rotor wing spindle to obtain an amplitude sequence and a phase sequence;
respectively calculating the Pearson product-moment correlation coefficient of the amplitude sequence of the first-order harmonic components of any two test channels and the Pearson product-moment correlation coefficient of the phase sequence;
respectively carrying out arithmetic mean calculation on the Pearson product moment correlation coefficient of the amplitude sequence and the Pearson product moment correlation coefficient of the phase sequence to obtain an amplitude correlation coefficient arithmetic mean and a phase correlation coefficient arithmetic mean;
multiplying the arithmetic mean of the amplitude correlation coefficient and the arithmetic mean of the phase correlation coefficient to obtain the amplitude-phase comprehensive correlation coefficient r of the two test channelsFψ；
According to amplitude-phase comprehensive correlation coefficient rFψAnd judging whether the bending moment identifications of the two test channels are accurate or not.
2. The method of claim 1, wherein performing harmonic analysis on the raw data of the rotor mast section bending moment to obtain an amplitude sequence and a phase sequence comprises:
and carrying out n whole-period data sequences of the amplitude and the phase of front k-order harmonic components of 4 measurement channels of the helicopter rotor main shaft on the original data of the section bending moment of the rotor main shaft.
3. The method according to claim 1, wherein the 4 measurement channels of the helicopter rotor mast are 4 measurement channels corresponding to two mutually orthogonal directions in two parallel sections of the helicopter rotor mast, namely a section ln direction, a section ip direction, a section iin direction and a section lp direction.
4. The method according to claim 2, wherein the calculation of the n whole-cycle data sequence of the amplitude and phase of the front k-th harmonic component of the 4 measurement channels of the helicopter rotor mast on the raw data of the rotor mast section bending moment is as follows:
intercepting the number N of sampling points of a rotor wing rotating for one circle of data sequence harmonic waves, a time domain measured amplitude Fj of each point and a relative azimuth angle psi j of each point j according to a rotor wing rotating speed signal, wherein N is a quotient integer obtained for fc/omega, and fc is the sampling frequency of a main shaft bending moment data signal;
performing cosine discrete fourier transform on each sampling point N to obtain a cosine component Fic of the harmonic; and sinusoidal discrete Fourier transform to obtain a sinusoidal component Fis, i of the harmonic wave as a harmonic component order;
and respectively calculating the amplitude Fi of the ith order harmonic quantity and the phase angle psi i thereof in one rotation according to the cosine component Fic and the sine component Fis.
5. The method of claim 4, wherein calculating the Pearson product-moment correlation coefficient of the amplitude sequence and the Pearson product-moment correlation coefficient of the phase sequence for the first harmonic components of any two test channels respectively comprises:
constructing equidistant discrete amplitude data F of any two test channels of main shaftbiAnd equally spaced discrete phase data Ψ for any two test channels of the principal axisbi；
Respectively calculating discrete amplitude data F by adopting a Pearson product moment correlation coefficient calculation methodbiAnd discrete phase data ΨbiCalculating the Pearson product moment correlation coefficient r of the amplitude sequence of the first-order harmonic components of any two measurement channelsF1biCorrelation coefficient r of Pearson product moment with phase sequenceΨ1bi。
6. The method of claim 1, wherein the amplitude-phase integrated correlation coefficient r isFψIs a dimensionless quantity, the amplitude is in the range of [ -1,1 [ ]]In the meantime.
7. The method of claim 1, wherein the correlation coefficient r is determined from amplitude-phase synthesisFψThe size of (2) judging whether the bending moment marks of the two test channels are accurate specifically comprises:
if the amplitude-phase comprehensive correlation coefficient r of two test channelsFψSatisfies the following conditions: r is more than or equal to 0.81Fψ≦ 1.0, then the two test channels are test channels of different cross-sections in the same direction.
8. The method of claim 1, wherein k is equal to or greater than 4.
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