CN117874400A - Aircraft model dynamic derivative test data processing system - Google Patents
Aircraft model dynamic derivative test data processing system Download PDFInfo
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Abstract
The invention discloses an aircraft model dynamic derivative test data processing system, which belongs to the field of aircraft dynamic derivative processing, and comprises: the device comprises a data acquisition module, a data processing module and a data display module; the data acquisition module is used for synchronously acquiring a moment signal and a displacement signal of the aircraft model in a forced vibration state in the wind tunnel test or acquiring a displacement signal of the aircraft model in a free damping vibration state in the wind tunnel test; the data processing module is used for carrying out aircraft dynamic derivative calculation based on the displacement acquisition signal and the moment acquisition signal to obtain an aircraft dynamic derivative calculation result, or carrying out aircraft dynamic derivative calculation based on the displacement acquisition signal to obtain an aircraft dynamic derivative calculation result; the data display module is used for displaying the calculation result of the dynamic derivative of the aircraft. The system can accurately obtain the dynamic derivative test data of the aircraft model with low cost.
Description
Technical Field
The invention relates to the field of aircraft dynamic derivative processing, in particular to an aircraft model dynamic derivative test data processing system.
Background
The dynamic derivative is also called dynamic stability derivative, is an essential aerodynamic parameter indispensable to the design and dynamic quality analysis of an aircraft, and describes aerodynamic characteristics of the aircraft when maneuver or being disturbed. There are three main methods for obtaining the dynamic derivative of an aircraft: wind tunnel test, model free flight test and flight test. In wind tunnel tests, there are generally two methods for obtaining the dynamic derivative of an aircraft: forced vibration and free damped vibration. The key of successful test is to accurately acquire the forced vibration data and the free damping vibration data of the aircraft, and then obtain the dynamic derivative of the aircraft through data processing. In the test, the forced vibration method needs to collect moment signals and displacement signals of the aircraft model, the automatic damping vibration method needs to collect displacement signals of the aircraft model, and the data collection precision directly relates to the calculation precision of the dynamic derivative.
The existing system comprises:
the method is currently applied to a dynamic derivative data processing system in a wind tunnel test, and the data processing flow is shown in figure 1.
When the forced vibration method is utilized, firstly, a conventional data acquisition card, such as a PXI acquisition system, is utilized to synchronously acquire a displacement original signal and a moment original signal generated by an aircraft model in the forced vibration in cooperation with LABVIEW software.
And then, respectively carrying out average calculation on the acquired displacement original signal and the moment original signal to obtain an average value of the displacement original signal and an average value of the moment original signal. Subtracting the average value of the displacement original signal from the displacement original signal to obtain a displacement filtering signal for filtering the direct current component and part of white noise; and subtracting the average value of the moment original signal from the moment original signal to obtain a moment filtering signal for filtering the direct current component and part of white noise.
And finally, calculating the displacement filtering signal and the moment filtering signal by a digital correlation method to obtain a dynamic derivative.
When the free vibration method is utilized, the acquisition system only has one circuit to work, and the displacement original signal generated by the aircraft model in free attenuation is acquired; and then, carrying out average calculation on the acquired displacement original signals to obtain an average value of the displacement original signals. Subtracting the average value of the displacement original signal from the displacement original signal to obtain a displacement filtering signal for filtering the direct current component and part of white noise; finally, digital correlation method calculation is carried out on the displacement filtering signals, and dynamic derivatives are obtained.
The existing system is simple to realize, does not need autonomous hardware design, and can acquire dynamic derivative test data by purchasing a mature acquisition system. However, the data acquisition card used in the system is not designed for the dynamic derivative test orientation, and is a universal data acquisition card, so that the acquired signal has direct current components and white noise, and the dynamic derivative data processing precision is affected. When the data is processed, the direct current component and the white noise are filtered only through average calculation, the effect is poor, and the direct current component and the white noise still exist in the filtered data; because only the digital correlation method is adopted to process the displacement filtering signal and the moment filtering signal, the dynamic derivative calculation accuracy is not high under the influence of sampling in an incomplete period. In addition, the existing system needs a computer to operate LABVIEW software to collect data and operate data analysis software to process the sampled data, and the hardware cost is high.
Disclosure of Invention
The invention aims to obtain accurate dynamic derivative test data of an aircraft model in a low-cost mode.
To achieve the above object, the present invention provides an aircraft model dynamic derivative test data processing system, the system comprising:
the device comprises a data acquisition module, a data processing module and a data display module; the data acquisition module is used for synchronously acquiring a moment signal and a displacement signal of the aircraft model in a forced vibration state in the wind tunnel test or acquiring a displacement signal of the aircraft model in a free damping vibration state in the wind tunnel test; the data acquisition module is also used for amplifying the acquired signals, processing direct current components, filtering noise and performing analog-to-digital conversion to acquire displacement acquisition signals and moment acquisition signals; the data processing module is used for carrying out aircraft dynamic derivative calculation based on the displacement acquisition signals and the moment acquisition signals acquired by the forced vibration to obtain an aircraft dynamic derivative calculation result, or carrying out aircraft dynamic derivative calculation based on the displacement acquisition signals acquired by the free damping vibration to obtain an aircraft dynamic derivative calculation result; the data display module is used for displaying the calculation result of the dynamic derivative of the aircraft.
The principle of the system is as follows: the system collects and processes wind tunnel dynamic derivative test data, directionally designs a collection module and a data processing module, and aims at a hardware collection circuit specially designed for an aircraft dynamic derivative test to be superior to the existing universal collection card, so that more accurate data can be obtained, a parameter estimation processing mode suitable for dynamic derivative test data characteristics is embedded in the data processing module, more accurate dynamic derivative can be obtained, and compared with a traditional system, the system does not adopt a high-cost data collection card and LABVIEW software and does not need another computer to operate, so that the system reduces hardware cost compared with the traditional system.
In the prior art, those skilled in the art only use a data processing system, including acquisition and calculation algorithms, and the like, do not study the data processing system, and mainly work in making an aircraft model, forcing a vibration device, and a free vibration device, and work in the front end, but neglect acquisition and calculation of the rear end, so that those skilled in the art do not easily think of replacing a data acquisition card and processing software of an aircraft model dynamic derivative test data processing system with a hardware module, and the system overcomes the technical bias inherent in the art, improves the data acquisition equipment, designs corresponding hardware acquisition equipment, provides a new system design concept, and reduces the cost of the system.
In some embodiments, the data acquisition module includes a displacement signal acquisition circuit, a torque signal acquisition circuit and a power supply circuit, the displacement signal acquisition circuit and the torque signal acquisition circuit are identical in structure and are respectively used for acquiring a displacement signal and a torque signal, and the power supply circuit is used for supplying power to the displacement signal acquisition circuit and the torque signal acquisition circuit.
Wherein, in some embodiments, the torque signal acquisition circuit comprises: the device comprises a first amplifying circuit, a first filtering circuit and a first analog-to-digital conversion circuit, wherein the first amplifying circuit is used for amplifying a moment signal to obtain an amplified moment signal, the first filtering circuit is used for filtering the amplified moment signal to filter direct current components and white noise in the moment signal to obtain a filtered moment signal, and the first analog-to-digital conversion circuit is used for carrying out analog-to-digital conversion on the filtered moment signal to convert an analog moment signal into a digital moment signal;
the displacement signal acquisition circuit includes: the second amplifying circuit is used for amplifying the displacement signals to obtain amplified displacement signals, the second filtering circuit is used for filtering the amplified displacement signals to filter direct current components and white noise in the displacement signals to obtain filtered displacement signals, and the second analog-to-digital conversion circuit is used for performing analog-to-digital conversion on the filtered displacement signals to convert analog displacement signals into digital displacement signals.
In some embodiments, the invention improves the data processing method in the data processing module in order to obtain more accurate dynamic derivatives of the aircraft, specifically:
the data processing module is used for carrying out aircraft dynamic derivative calculation based on the displacement acquisition signals to obtain an aircraft dynamic derivative calculation result, and specifically comprises the following steps:
step 1: based on a data acquisition module, obtaining a sampling signal of the aircraft model in a free damping vibration state, and truncating the sampling signal to obtain a truncated signal;
step 2: obtaining a spectrum maximum index of the truncated signal based on the truncated signal;
step 3: obtaining a rough estimate of the spectral offset, a rough estimate of the attenuation factor, a rough estimate of the initial phase and a rough estimate of the amplitude of the truncated signal based on the spectral maximum index of the truncated signal;
step 4: constructing an orthogonal component of the truncated signal based on the spectrum maximum index of the truncated signal, the rough estimate of the spectrum offset, the rough estimate of the amplitude and the rough estimate of the initial phase;
step 5: synthesizing the truncated signal and the orthogonal component of the truncated signal to obtain an intermediate variable;
step 6: obtaining a fine estimate of the frequency of the truncated signal, a fine estimate of the attenuation factor, a fine estimate of the amplitude and a fine estimate of the primary phase based on the intermediate variable;
step 7: and obtaining a fine estimation value of the frequency of the truncated signal, a fine estimation value of the attenuation factor, a fine estimation value of the amplitude and a fine estimation value of the initial phase based on the sampling signal, and performing aircraft dynamic derivative calculation to obtain an aircraft dynamic derivative calculation result.
Wherein, in step 5, an intermediate variable is constructed, and the truncated signal and the orthogonal component thereof are synthesized to obtain an intermediate variable r (n) capable of suppressing the influence of negative frequency spectrum leakage, thereby obtaining more accurate dynamic derivative of the aircraft.
Wherein, in some embodiments, step 2 comprises:
point-by-point searching is performed in the order of N from 0 to N-1 to find the first occurrence of x (N)<0 and x (n+1)>0, where the index n is denoted as n 1 Calculating to obtain n 1 And n 1 First rising zero crossing time value t between +1 1 N represents a sampling time point, N represents the length of the truncated signal, x (N) is the truncated signal, and x (n+1) is the truncated signal corresponding to the sampling time point n+1;
obtaining t 1 Then, according to n, from n 1 +1 to N-1, find the second occurrence of x (N)<0 and x (n+1)>0, where the index n is denoted as n 2 Calculating to obtain n 2 And n 2 Second rising zero crossing time value t between +1 2 ；
According to the first rising zero crossing time value t 1 And a second rising zero crossing time value t 2 Calculating the frequency of the sampled signalThe spectral maximum index k.
Wherein, in some embodiments, the first rising zero crossing time value t 1 Second rising zero crossing time value t 2 And the spectrum maximum index k of the truncated signal is calculated by respectively:
；
；
；
wherein x (n 1 ) For sampling time point n 1 Corresponding truncated signal amplitude, x (n 1 +1) is the sampling time point n 1 The truncated signal amplitude corresponding to +1, x (n 2 ) For sampling time point n 2 Corresponding truncated signal amplitude, x (n 2 +1) is the sampling time point n 2 The truncated signal amplitude corresponding to +1,the representation is closest +.>Is an integer of (a).
Wherein, in some embodiments, the step 3 specifically includes:
the step 3 specifically includes:
performing spectrum interpolation calculation at intervals of 0.5 on two sides of a spectrum maximum index k to obtain a first interpolation point spectrum X (k-0.5), and obtaining a second interpolation point spectrum X (k+0.5);
calculating a rough estimate of the spectral offset of the truncated signal based on the obtained first interpolation point spectrum X (k-0.5) and the second interpolation point spectrum X (k+0.5)And a rough estimate of the attenuation factor of the truncated signal +.>；
Coarse estimation of spectral offset based on truncated signalAnd a rough estimate of the attenuation factor of the truncated signal +.>Obtaining the complex amplitude A of the truncated signal 1 ；
Signal complex amplitude A based on truncated signal 1 Calculating to obtain rough estimation of initial phase of truncated signalAnd rough estimate of amplitude +.>。
In some embodiments, the first interpolation point spectrum X (k-0.5) is calculated by:
；
the second interpolation point spectrum X (k+0.5) is calculated in the following manner:
；
coarse estimation of spectral offset of truncated signalAnd a rough estimate of the attenuation factor of the truncated signal +.>The calculation mode of (a) is as follows:
；
wherein,and->Respectively represent the plural->I is an imaginary unit;
signal complex amplitude a of truncated signal 1 The calculation mode of (a) is as follows:
；
coarse estimation of the initial phase of a truncated signalAnd rough estimate of amplitude +.>The calculation mode of (a) is as follows:
；
wherein,and->Respectively represent the complex amplitude A 1 Is a die and angle of (c).
Wherein, in some embodiments, the orthogonal component y (n) of the constructed truncated signal x (n) is:
；
based on the truncated signal and the orthogonal component of the truncated signal, the synthesized intermediate variable r (n) is:
；
wherein,for a rough estimate of the initial phase of the truncated signal, < > x->For a rough estimate of the amplitude of the truncated signal e is a natural base, n represents the sampling instant,/o>For a rough estimate of the spectral offset of the truncated signal,/or->For a rough estimate of the attenuation factor of the truncated signal, N represents the length of the truncated signal, k is the index of the spectral maximum of the truncated signal, a is the amplitude of the truncated signal x (N), and +.>Is the attenuation factor of the truncated signal, f is the frequency of the truncated signal x (n), f s For the sampling frequency +.>I is an imaginary unit for shortening the initial phase of the signal x (n).
Wherein, in some embodiments, the step 6 comprises:
the step 6 comprises the following steps:
performing spectrum interpolation calculation on the intermediate variable to obtain a third interpolation point spectrumAnd fourth interpolation point spectrum->；
Based on the third interpolation point spectrumAnd fourth interpolation point spectrum->Calculating to obtain a refined estimate of the spectral offset of the truncated signal +.>And a fine estimate of the attenuation factor of the truncated signal +.>；
Fine estimate of spectral offset based on truncated signalAnd a fine estimate of the attenuation factor of the truncated signal +.>Calculating complex amplitude A of truncated signal 2 ；
Complex amplitude a based on truncated signal 2 Calculating to obtain a fine estimate of the amplitude of the truncated signalAnd a fine estimate of the initial phase of the truncated signal +.>；
Fine estimate of spectral offset based on truncated signalCalculating to obtain a fine estimate of the frequency of the truncated signal；
Wherein:
；
；
；
wherein,andrespectively represent the plural->I is an imaginary unit;
；
；
；
wherein,for the rough estimation of the initial phase of the truncated signal, k is the index of the maximum value of the spectrum of the truncated signal, N represents the length of the truncated signal, r (N) is an intermediate variable, e is a natural base, N represents the sampling instant point,For a rough estimate of the spectral offset of the truncated signal, x (n) is the truncated signal,/->To coarsely estimate the amplitude of the truncated signal, f s Is the sampling frequency.
The one or more technical schemes provided by the invention have at least the following technical effects or advantages:
the system is low in cost, and accurate aircraft model dynamic derivative test data can be obtained through the system.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention;
FIG. 1 is a schematic diagram of a conventional data processing flow of a dynamic derivative data processing system applied to a wind tunnel test;
FIG. 2 is a schematic block diagram of an aircraft model dynamic derivative test data processing system designed according to the present invention;
FIG. 3 is a schematic illustration of the operational flow of the aircraft model dynamic derivative test data processing system.
Detailed Description
In order that the above-recited objects, features and advantages of the present invention will be more clearly understood, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description. In addition, the embodiments of the present invention and the features in the embodiments may be combined with each other without collision.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, however, the present invention may be practiced in other ways than within the scope of the description, and the scope of the invention is therefore not limited to the specific embodiments disclosed below.
Embodiment one;
the schematic block diagram of the aircraft model dynamic derivative test data processing system designed by the invention is shown in fig. 2. The operation flow of the aircraft model dynamic derivative test data processing system is shown in fig. 3, and the invention provides an aircraft model dynamic derivative test data processing system, which comprises:
the device comprises a data acquisition module, a data processing module and a data display module; the data acquisition module is used for synchronously acquiring a moment signal and a displacement signal of the aircraft model in a forced vibration state in the wind tunnel test or acquiring a displacement signal of the aircraft model in a free damping vibration state in the wind tunnel test; the data acquisition module is also used for amplifying the acquired signals, processing direct current components, filtering noise and performing analog-to-digital conversion to acquire displacement acquisition signals and moment acquisition signals; the data processing module is used for carrying out aircraft dynamic derivative calculation based on the displacement acquisition signals and the moment acquisition signals acquired by the forced vibration to obtain an aircraft dynamic derivative calculation result, or carrying out aircraft dynamic derivative calculation based on the displacement acquisition signals acquired by the free damping vibration to obtain an aircraft dynamic derivative calculation result; the data display module is used for displaying the calculation result of the dynamic derivative of the aircraft.
The system aims at wind tunnel dynamic derivative test data processing, and the aircraft model dynamic derivative test data processing system which is directionally designed comprises three parts: the device comprises a data acquisition module, a data processing module and a data display module.
The data acquisition module realizes synchronous real-time acquisition of the moment signal and the displacement signal of the aircraft in the wind tunnel test, and the acquired signal does not contain a direct current component through signal conditioning, so that the noise component in the sampled signal is greatly reduced.
The data processing module adopts a high-performance data processor, a high-precision parameter estimation algorithm is embedded, the acquired signals are directly processed, and the calculation precision of the dynamic derivative is high and the cost is low.
The data display module directly displays the calculated dynamic derivative, test data and the like by using a display screen.
In the embodiment of the invention, the data acquisition module comprises a displacement signal acquisition circuit, a moment signal acquisition circuit and a power supply circuit, wherein the displacement signal acquisition circuit and the moment signal acquisition circuit have the same structure and are respectively used for acquiring displacement signals and moment signals, and the power supply circuit is used for supplying power to the displacement signal acquisition circuit and the moment signal acquisition circuit.
In an embodiment of the present invention, the torque signal acquisition circuit includes: the device comprises a first amplifying circuit, a first filtering circuit and a first analog-to-digital conversion circuit, wherein the first amplifying circuit is used for amplifying a moment signal to obtain an amplified moment signal, the first filtering circuit is used for filtering the amplified moment signal to filter direct current components and white noise in the moment signal to obtain a filtered moment signal, and the first analog-to-digital conversion circuit is used for carrying out analog-to-digital conversion on the filtered moment signal to convert an analog moment signal into a digital moment signal;
the displacement signal acquisition circuit includes: the second amplifying circuit is used for amplifying the displacement signals to obtain amplified displacement signals, the second filtering circuit is used for filtering the amplified displacement signals to filter direct current components and white noise in the displacement signals to obtain filtered displacement signals, and the second analog-to-digital conversion circuit is used for performing analog-to-digital conversion on the filtered displacement signals to convert analog displacement signals into digital displacement signals.
In the embodiment of the invention, the designed system is different from the existing system in operation flow, firstly, when a forced vibration method is utilized, the synchronous acquisition of the displacement signal and the moment signal of the aircraft is completed by utilizing a data acquisition module, the acquired signals are subjected to conditioning such as filtering, amplifying and the like by a hardware circuit, the displacement acquisition signal and the moment acquisition signal are obtained, the acquired signals are not influenced by a direct current component, and the influence of white noise is small. And then, directly transmitting the acquired displacement signals and moment signals into a high-performance computing chip, and obtaining sampling signal parameters by utilizing a high-precision parameter estimation algorithm, thereby computing the dynamic derivative of the aircraft. And finally, directly transmitting the calculated dynamic derivative to a display screen for display, and completing the data processing of the aircraft model dynamic derivative test.
When the free vibration method is utilized, a moment signal acquisition circuit of a sampling module in the aircraft model dynamic derivative test data processing system does not work, and only a displacement signal acquisition circuit works. After the displacement signal is obtained, the collected displacement signal is directly transmitted into a high-performance computing chip, and the high-precision parameter estimation algorithm is utilized to obtain the sampling signal parameter, so that the dynamic derivative of the aircraft is computed. And finally, directly transmitting the calculated dynamic derivative to a display screen for display, and completing the data processing of the aircraft model dynamic derivative test.
And (3) matching with an attenuation signal parameter estimation algorithm, so that the aircraft model dynamic derivative test data processing based on the free vibration method can be completed.
In order to ensure synchronous sampling of the moment signal and the displacement signal, the moment signal acquisition and conditioning circuit and the displacement signal acquisition and conditioning circuit are completely symmetrical.
When the moment signals of the aircraft are collected, firstly, weak moment signals pass through an amplifying circuit, namely INA128 and peripheral circuits thereof, and the moment signals are amplified to obtain amplified moment signals; then, the moment signal passes through a filter circuit, namely U5A and peripheral circuits thereof, and the direct current component and part of white noise in the moment signal are filtered, so that the filtered moment signal is obtained; finally, the moment signal is converted into a digital moment signal by an analog-to-digital conversion circuit, namely an ADS1255 and a peripheral circuit thereof, and the moment signal is transmitted to a computing chip TMS320F28335 for further processing.
When the displacement signal of the aircraft is collected, firstly, the weak displacement signal passes through an amplifying circuit, namely INA128 and peripheral circuits thereof, and the displacement signal is amplified to obtain an amplified displacement signal; then, the displacement signal passes through a filter circuit, namely U5A and peripheral circuits thereof, and the direct current component and part of white noise in the displacement signal are filtered, so that a filtered displacement signal is obtained; finally, the displacement signal is converted into a digital signal displacement signal by an analog-to-digital conversion circuit, namely an ADS1255 and a peripheral circuit thereof, and the displacement signal is transmitted to a data processing circuit, namely a TMS320F28335 chip and a peripheral circuit thereof, and is further processed.
The data processing module is embedded with a high-precision signal processing algorithm, and parameter estimation is carried out on the moment signal and the displacement signal respectively to obtain the amplitude, the frequency and the initial phase of the moment signal and the attenuation factor, the amplitude, the frequency and the initial phase of the displacement signal, so that the dynamic derivative of the aircraft is obtained.
Embodiment two;
on the basis of the first embodiment, the data processing system for the dynamic derivative test of the aircraft model comprises two groups of data processing algorithms, wherein the algorithms are used for processing moment signals and displacement signals obtained based on forced vibration, the algorithm designed by the invention patent ZL202210509556.8 is directly utilized for processing the dynamic derivative test data of the aircraft, and the algorithms are used for processing displacement signals obtained based on free damping vibration, namely the data processing algorithm embedded by the data processing module is the data processing method for the dynamic derivative test of the aircraft.
The key point of the scheme is that free attenuation data of an aircraft model can be correctly acquired, and then the data are rapidly analyzed to obtain high-precision signal parameters. When the model is in a free attenuation state, the data acquired by the designed data acquisition system is a single-frequency attenuation real signal, and the truncated signal x (n) is:
；
wherein a, f,And->Representing the amplitude, frequency, initial phase and attenuation factor of the truncated signal x (n), respectively, wherein a>0，，；f s Representing sampling frequency, N represents sampling time point, N represents length of truncated signal, and e represents natural base number; z (n) is 0 in mean and +.>Additive white gaussian noise of (c).
And processing the acquired free attenuation data of the aircraft model to obtain signal amplitude, frequency, initial phase and attenuation factors, so as to obtain the dynamic derivative of the aircraft.
In order to improve the processing precision of the aircraft dynamic derivative test data, reduce the calculated amount and improve the calculated speed, the invention provides a processing method of the aircraft dynamic derivative test data, which comprises the following steps:
step 1: based on a data acquisition module, obtaining a sampling signal of the aircraft model in a free damping vibration state, and truncating the sampling signal to obtain a truncated signal;
step 2: obtaining a spectrum maximum index of the truncated signal based on the truncated signal;
step 3: obtaining a rough estimate of the spectral offset, a rough estimate of the attenuation factor, a rough estimate of the initial phase and a rough estimate of the amplitude of the truncated signal based on the spectral maximum index of the truncated signal;
step 4: constructing an orthogonal component of the truncated signal based on the spectrum maximum index of the truncated signal, the rough estimate of the spectrum offset, the rough estimate of the amplitude and the rough estimate of the initial phase;
step 5: synthesizing the truncated signal and the orthogonal component of the truncated signal to obtain an intermediate variable;
step 6: obtaining a fine estimate of the frequency of the truncated signal, a fine estimate of the attenuation factor, a fine estimate of the amplitude and a fine estimate of the primary phase based on the intermediate variable;
step 7: and obtaining a fine estimation value of the frequency of the truncated signal, a fine estimation value of the attenuation factor, a fine estimation value of the amplitude and a fine estimation value of the initial phase based on the sampling signal, and performing aircraft dynamic derivative calculation to obtain an aircraft dynamic derivative calculation result.
The sampling signal is truncated to obtain a truncated signal, and the length of the truncated signal is N;
point-by-point searching is performed in the order of N from 0 to N-1 to find the first occurrence of x (N)<0 and x (n+1)>0, where the index n is denoted as n 1 Calculating to obtain n 1 And n 1 First rising zero crossing time value t between +1 1 ；
Obtaining t 1 Then, according to n, from n 1 +1 to N-1, find the second occurrence of x (N)<0 and x (n+1)>Two points of 0 are used for the purpose of,the index n at this time is denoted as n 2 Calculating to obtain n 3 And n 2 Second rising zero crossing time value t between +1 2 ；
According to the first rising zero crossing time value t 1 And a second rising zero crossing time value t 2 Calculating to obtain rough frequency value f of truncated signal c ；
In this embodiment of the present invention, the first rising zero crossing time value t 1 The second rising zero crossing time value t 2 The calculation modes are respectively as follows:
；
。
the spectrum maximum index k of the truncated signal is calculated by the following steps:
；
wherein,the representation is closest +.>Is an integer of (a).
In the embodiment of the invention, after the spectrum maximum value index k is obtained, spectrum interpolation calculation is performed at the intervals of 0.5 on two sides of the spectrum maximum value index k.
In the embodiment of the present invention, the first interpolation point spectrum value is X (k-0.5), the second interpolation point spectrum value is X (k+0.5), and the rough estimate of the spectrum offset of the truncated signal isRough estimate of attenuation factor of truncated signal is +.>Wherein:
；
；
；
wherein,and->Respectively represent the plural->I is the imaginary unit.
Then, the complex amplitude A of the truncated signal is obtained 1 。
；
Thereby obtaining a rough estimate of the amplitude of the truncated signalAnd coarse estimation of the initial phase +.>。/>
；
Wherein,and->Respectively are provided withRepresenting complex amplitude A 1 Is a die and angle of (c).
And thirdly, constructing an intermediate variable.
Constructing an orthogonal component y (n) of the truncated signal x (n) by using the spectrum maximum value index, the spectrum offset coarse estimation value, the amplitude coarse estimation value and the initial phase coarse estimation value of the truncated signal obtained in the step 2:
；
then, the truncated signal and its orthogonal components are synthesized to obtain an intermediate variable r (n) that can suppress the influence of negative frequency spectrum leakage:
；
where i is an imaginary unit.
And obtaining a fine estimation value of the frequency of the truncated signal, a fine estimation value of the attenuation factor, a fine estimation value of the amplitude and a fine estimation value of the initial phase.
After the intermediate variable is obtained, spectrum interpolation calculation is carried out on the intermediate variable, and more accurate signal parameters are obtained. During interpolation calculation, inAnd performing spectrum interpolation calculation at the interval between two sides of 0.5.
Preferably, in the method, the third interpolation point has a spectral value ofThe fourth interpolation point has a spectral value ofThe fine estimate of the spectral offset of the truncated signal is +.>The fine estimate of the attenuation factor of the truncated signal is +.>Wherein:
；
；
；/>
wherein,andrespectively represent the plural->I is the imaginary unit.
Obtaining the complex amplitude A of the signal after obtaining the fine estimated value of the spectrum offset of the truncated signal and the fine estimated value of the attenuation factor 2 。
；
Thereby obtaining a fine estimate of the amplitude of the truncated signalAnd the fine estimate of the initial phase +.>。
；
Finally obtaining the precise estimated value of the frequency of the truncated signal。
；
Finally, obtaining the precise estimated value of the frequency of the truncated signalRefined estimate of amplitude +.>Fine estimate of primary phaseAnd a fine estimate of the attenuation factor +.>After that, the method can be used for calculating the dynamic derivative parameters of the aircraft, and the specific calculation mode can be referred to Guo Leitao. Phi.1 m hypersonic wind tunnel dynamic derivative test technical research [ D ]]Center of aerodynamic research and development, 2013.
Compared with the method and the system for tracking the vibration frequency of the coriolis flowmeter disclosed by the invention patent ZL202211173308.7 and the method for processing the digital signal of the coriolis flowmeter disclosed by the invention patent ZL202211171907.5, the invention content disclosed by the invention of the two patents relates to the method for processing the vibration signal with constant amplitude. The invention utilizes the acquisition thought of the maximum value index k of the signal spectrum in the two patents, but the patent content of the invention is essentially different from the patent content of the two aspects, and the invention is specifically characterized in that:
the present invention is different from the signal model for which the two patent inventions are directed. The two patent inventions are aimed at the vibration signals of the coriolis flowmeter in the stable amplitude vibration state, the acquisition signals are amplitude constant signals, and the acquisition signals only comprise 3 parameters of amplitude, frequency and primary phase, so that the parameters are few, and the data processing is easy to realize. The invention aims at the dynamic derivative test data of the aircraft model in the free attenuation state, the sampling signal is an amplitude attenuation signal, and the sampling signal contains 4 parameters of amplitude, frequency, initial phase and attenuation factor, so that the design difficulty of a data processing method is increased, and the methods disclosed by the two invention patents cannot be directly used.
The invention utilizes the acquisition thought of the maximum value index k of the signal spectrum in the two patents to reduce the complexity of the processing of the dynamic derivative test data of the aircraft, and the content of the part only occupies a very small part of the content of the invention. The invention mainly comprises an aircraft dynamic derivative test data acquisition processing system and an aircraft dynamic derivative test data processing method. The method for processing the data of the aircraft dynamic derivative test has the main innovation points that orthogonal components of the sampling signals are constructed, the influence of spectrum leakage in the sampling signals is restrained by synthesizing intermediate variables, and the accuracy of the method for processing the data of the aircraft dynamic derivative test is improved. Compared with other parameter estimation algorithms aiming at the attenuation signals, the method has the advantages of smaller calculated amount and higher parameter estimation precision.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. It is therefore intended that the following claims be interpreted as including the preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the spirit or scope of the invention. Thus, it is intended that the present invention also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
Claims (10)
1. An aircraft model dynamic derivative test data processing system, the system comprising:
the device comprises a data acquisition module, a data processing module and a data display module; the data acquisition module is used for synchronously acquiring a moment signal and a displacement signal of the aircraft model in a forced vibration state in the wind tunnel test or acquiring a displacement signal of the aircraft model in a free damping vibration state in the wind tunnel test; the data acquisition module is also used for amplifying the acquired signals, processing direct current components, filtering noise and performing analog-to-digital conversion to acquire displacement acquisition signals and moment acquisition signals; the data processing module is used for carrying out aircraft dynamic derivative calculation based on the displacement acquisition signals and the moment acquisition signals acquired by the forced vibration to obtain an aircraft dynamic derivative calculation result, or carrying out aircraft dynamic derivative calculation based on the displacement acquisition signals acquired by the free damping vibration to obtain an aircraft dynamic derivative calculation result; the data display module is used for displaying the calculation result of the dynamic derivative of the aircraft.
2. The system of claim 1, wherein the data acquisition module comprises a displacement signal acquisition circuit, a torque signal acquisition circuit and a power supply circuit, the displacement signal acquisition circuit and the torque signal acquisition circuit are identical in structure and are respectively used for acquiring displacement signals and torque signals, and the power supply circuit is used for supplying power to the displacement signal acquisition circuit and the torque signal acquisition circuit.
3. The aircraft model dynamic derivative test data processing system of claim 2, wherein the torque signal acquisition circuit comprises: the device comprises a first amplifying circuit, a first filtering circuit and a first analog-to-digital conversion circuit, wherein the first amplifying circuit is used for amplifying a moment signal to obtain an amplified moment signal, the first filtering circuit is used for filtering the amplified moment signal to filter direct current components and white noise in the moment signal to obtain a filtered moment signal, and the first analog-to-digital conversion circuit is used for carrying out analog-to-digital conversion on the filtered moment signal to convert an analog moment signal into a digital moment signal;
the displacement signal acquisition circuit includes: the second amplifying circuit is used for amplifying the displacement signals to obtain amplified displacement signals, the second filtering circuit is used for filtering the amplified displacement signals to filter direct current components and white noise in the displacement signals to obtain filtered displacement signals, and the second analog-to-digital conversion circuit is used for performing analog-to-digital conversion on the filtered displacement signals to convert analog displacement signals into digital displacement signals.
4. The system for processing the data of the aircraft model dynamic derivative test according to claim 1, wherein the data processing module performs the calculation of the aircraft dynamic derivative based on the displacement acquisition signal to obtain the calculation result of the aircraft dynamic derivative, and specifically comprises:
step 1: based on a data acquisition module, obtaining a sampling signal of the aircraft model in a free damping vibration state, and truncating the sampling signal to obtain a truncated signal;
step 2: obtaining a spectrum maximum index of the truncated signal based on the truncated signal;
step 3: obtaining a rough estimate of the spectral offset, a rough estimate of the attenuation factor, a rough estimate of the initial phase and a rough estimate of the amplitude of the truncated signal based on the spectral maximum index of the truncated signal;
step 4: constructing an orthogonal component of the truncated signal based on the spectrum maximum index of the truncated signal, the rough estimate of the spectrum offset, the rough estimate of the amplitude and the rough estimate of the initial phase;
step 5: synthesizing the truncated signal and the orthogonal component of the truncated signal to obtain an intermediate variable;
step 6: obtaining a fine estimate of the frequency of the truncated signal, a fine estimate of the attenuation factor, a fine estimate of the amplitude and a fine estimate of the primary phase based on the intermediate variable;
step 7: and carrying out aircraft dynamic derivative calculation based on the fine estimation value of the frequency of the truncated signal, the fine estimation value of the attenuation factor, the fine estimation value of the amplitude and the fine estimation value of the initial phase to obtain an aircraft dynamic derivative calculation result.
5. The aircraft model dynamic derivative test data processing system of claim 4, wherein step 2 comprises:
point-by-point searching is performed in the order of N from 0 to N-1 to find the first occurrence of x (N)<0 and x (n+1)>0, where the index n is denoted as n 1 Calculating to obtain n 1 And n 1 First rising zero crossing time value t between +1 1 N represents a sampling time point, N represents the length of the truncated signal, x (N) is the truncated signal corresponding to the sampling time point N, and x (n+1) is the truncated signal corresponding to the sampling time point n+1;
obtaining t 1 Then, according to n, from n 1 +1 to N-1, find the second occurrence of x (N)<0 and x (n+1)>0, where the index n is denoted as n 2 Calculating to obtain n 2 And n 2 Second rising zero crossing time value t between +1 2 ；
According to the first rising zero crossing time value t 1 And a second rising zero crossing time value t 2 And calculating to obtain the spectrum maximum value index k of the sampling signal.
6. The aircraft model dynamic derivative test data processing system of claim 5, wherein the first rising zero crossing time value t 1 Second rising zero crossing time value t 2 And the spectrum maximum index k of the truncated signal is calculated by respectively:
；
；
；
wherein x (n 1 ) For sampling time point n 1 Corresponding truncated signal amplitude, x (n 1 +1) is the sampling time point n 1 The truncated signal amplitude corresponding to +1, x (n 2 ) For sampling time point n 2 Corresponding truncated signal amplitude, x (n 2 +1) is the sampling time point n 2 The truncated signal amplitude corresponding to +1,the representation is closest +.>Is an integer of (a).
7. The aircraft model dynamic derivative test data processing system according to claim 5, wherein the step 3 specifically comprises:
performing spectrum interpolation calculation at intervals of 0.5 on two sides of a spectrum maximum index k to obtain a first interpolation point spectrum X (k-0.5), and obtaining a second interpolation point spectrum X (k+0.5);
calculating a rough estimate of the spectral offset of the truncated signal based on the obtained first interpolation point spectrum X (k-0.5) and the second interpolation point spectrum X (k+0.5)And a rough estimate of the attenuation factor of the truncated signal +.>；
Coarse estimation of spectral offset based on truncated signalAnd a rough estimate of the attenuation factor of the truncated signal +.>Obtaining the complex amplitude A of the truncated signal 1 ；
Signal complex amplitude A based on truncated signal 1 Calculating to obtain rough estimation of initial phase of truncated signalAnd rough estimate of amplitude +.>。
8. The system for processing aircraft model dynamic derivative test data according to claim 7, wherein the first interpolation point spectrum X (k-0.5) is calculated by:
；
the second interpolation point spectrum X (k+0.5) is calculated in the following manner:
；
coarse estimation of spectral offset of truncated signalAnd a rough estimate of the attenuation factor of the truncated signal +.>The calculation mode of (a) is as follows:
；
wherein,and->Respectively represent the plural->I is an imaginary unit;
signal complex amplitude a of truncated signal 1 The calculation mode of (a) is as follows:
；
truncating the signalCoarse estimation of initial phaseAnd rough estimate of amplitude +.>The calculation mode of (a) is as follows:
；
wherein,and->Respectively represent the complex amplitude A 1 Is a die and angle of (c).
9. The aircraft model dynamic derivative test data processing system of claim 4, wherein the quadrature component y (n) of the constructed truncated signal x (n) is:
；
based on the truncated signal and the orthogonal component of the truncated signal, the synthesized intermediate variable r (n) is:
；
wherein,for a rough estimate of the initial phase of the truncated signal, < > x->For a rough estimate of the amplitude of the truncated signal e is a natural base, n represents the sampling instant,/o>For a rough estimate of the spectral offset of the truncated signal,/or->For a rough estimate of the attenuation factor of the truncated signal, N represents the length of the truncated signal, k is the index of the spectral maximum of the truncated signal, a is the amplitude of the truncated signal x (N), and +.>Is the attenuation factor of the truncated signal, f is the frequency of the truncated signal x (n), f s For the sampling frequency +.>I is an imaginary unit for shortening the initial phase of the signal x (n).
10. The aircraft model dynamic derivative test data processing system according to claim 4, wherein said step 6 comprises:
performing spectrum interpolation calculation on the intermediate variable to obtain a third interpolation point spectrumAnd a fourth interpolation point spectrum；
Based on the third interpolation point spectrumAnd fourth interpolation point spectrum->Calculating to obtain a refined estimate of the spectral offset of the truncated signal +.>And a decay factor of the truncated signalRefined estimate->；
Fine estimate of spectral offset based on truncated signalAnd a fine estimate of the attenuation factor of the truncated signal +.>Calculating complex amplitude A of truncated signal 2 ；
Complex amplitude a based on truncated signal 2 Calculating to obtain a fine estimate of the amplitude of the truncated signalAnd a fine estimate of the initial phase of the truncated signal +.>；
Fine estimate of spectral offset based on truncated signalCalculating to obtain a refined estimate of the frequency of the truncated signal +.>；
Wherein:
；
；
；
wherein the method comprises the steps of，Andrespectively represent the complex numberI is an imaginary unit;
；
；
；
wherein,for the rough estimation of the initial phase of the truncated signal, k is the index of the maximum value of the spectrum of the truncated signal, N represents the length of the truncated signal, r (N) is an intermediate variable, e is a natural base, N represents the sampling instant point,For a rough estimate of the spectral offset of the truncated signal, x (n) is the truncated signal,/->To coarsely estimate the amplitude of the truncated signal, f s Is the sampling frequency.
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