CN112345199B - Method for correcting impact of vibration of attack angle sensor of temporary-impulse high-speed wind tunnel - Google Patents
Method for correcting impact of vibration of attack angle sensor of temporary-impulse high-speed wind tunnel Download PDFInfo
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- CN112345199B CN112345199B CN202011182088.5A CN202011182088A CN112345199B CN 112345199 B CN112345199 B CN 112345199B CN 202011182088 A CN202011182088 A CN 202011182088A CN 112345199 B CN112345199 B CN 112345199B
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
Abstract
The invention discloses a method for correcting the impact of vibration of an attack angle sensor of a temporary-impulse high-speed wind tunnel, which is characterized in that two triaxial acceleration sensors are additionally arranged in the axial direction of the attack angle sensor, the centrifugal acceleration of the attack angle sensor in different directions and different vibration modes is calculated, and further the correction of angle measurement errors of the attack angle sensor caused by vibration can be realized.
Description
Technical Field
The invention relates to the technical field of aerodynamic wind tunnel tests, in particular to a vibration influence correction method of a temporary-impulse high-speed wind tunnel attack angle sensor based on a triaxial acceleration sensor, which is suitable for real-time measurement of a test model attack angle under the condition of model jitter in a wind tunnel test.
Background
Compared with optical measurement, mechanical measurement based on stress strain and the like, the attack angle measurement mode based on the inertia technology has the characteristics of small size, direct detection and high precision of a sensor device, so that the attack angle measurement mode is widely applied to attack angle measurement of a test model during high-speed wind tunnel test. The attack angle sensor is a quartz flexible pendulum sensor, essentially a high-precision servo linear accelerometer, and mainly comprises elements such as a quartz flexible mass pendulum piece, a displacement sensing element, a torquer winding and the like. The sensor can achieve the measuring precision of +/-0.01 degrees under the working condition that the working environment has no vibration or has little vibration.
In a conventional force measurement test of a high-speed wind tunnel, in order to reduce disturbance of a model support system to a flow field, an aircraft model is usually fixed in a wind tunnel test section in a tail support mode, so that a tested model, a force measurement balance, a support rod and a bent blade mechanism form a cantilever type structure with approximately concentrated mass, and the structure has the characteristics of low rigidity and lower first-order natural frequency on the whole. In a blowing test, due to the air flow noise of a test section and the air flow pulsation of an internal flow field, the air pressure change acting on the surface of a model caused by air flow disturbance is very uncertain, and further, an aircraft model and a support system generate strong low-frequency random vibration.
Although the model vibration in general does not cause structural damage to the wind tunnel test, the vibration of the model and the support rod generates centrifugal acceleration along the axial direction of the support rod, and the attack angle sensor based on the inertia measurement principle cannot distinguish the gravity acceleration from the centrifugal acceleration caused by the model vibration, so that the measured value deviation of the attack angle sensor installed in the model reaches 0.1-0.5 degrees.
At present, the vibration influence correction of the high-speed wind tunnel attack angle sensor at home and abroad mainly comprises a frequency domain signal processing method and a centrifugal acceleration compensation method based on an effective vibration radius. The frequency domain signal processing method measures natural frequency from the frequency spectrum characteristic of an acceleration signal along the tangent line of a support rod, measures amplitude at twice the natural frequency from the frequency spectrum of an unfiltered attack angle sensor signal, and further obtains angle measurement deviation caused by vibration, but the method has poor compensation precision for angle measurement errors when a plurality of vibration modes exist at the same time; the method comprises the steps of firstly carrying out an excitation test on a model supporting system under a wind tunnel windless condition based on an effective vibration radius, estimating effective vibration radii of different vibration modes, then measuring acceleration peak values corresponding to natural vibration frequencies from yaw and pitch acceleration frequency spectrums during a wind tunnel blowing test, further calculating centrifugal acceleration caused by vibration, and finally compensating angle measurement deviation of a test model caused by vibration.
Disclosure of Invention
The invention aims to improve the performance of the existing high-speed wind tunnel test model attack angle measurement technology, and provides a system and a method for correcting attack angle sensor vibration, which can effectively correct angle measurement errors of an attack angle sensor caused by vibration.
In order to achieve the purpose, the invention adopts the following technical scheme:
a method for correcting the vibration influence of an attack angle sensor of a temporary rush type high-speed wind tunnel comprises the following steps:
s1, symmetrically arranging a triaxial acceleration sensor at each axial side of the angle of attack sensor in the test model provided with the angle of attack sensor;
s2, during a blowing test, synchronously acquiring unfiltered signals of two triaxial acceleration sensors and an attack angle sensor, carrying out spectrum analysis, power spectrum analysis and cross-spectrum coherence function calculation on the signals, identifying vibration frequencies corresponding to multi-order vibration modes in different directions of a test model supporting system, and carrying out band-pass filtering on output signals of the two triaxial acceleration sensors around the vibration frequencies of different orders to obtain acceleration signals after band-pass filtering;
s3: integrating the acceleration signals after the band-pass filtering to obtain acceleration integral signals, and then calculating the centrifugal acceleration caused by the vibration modes of different orders in different directions as follows:
wherein V1dji(t) and V2dji(t) acceleration integral signals of the two triaxial acceleration sensors are respectively shown, and r is the distance between the two triaxial acceleration sensors;
s4: obtaining the sum of angle errors of the attack angle sensor caused by centrifugal acceleration caused by vibration:
wherein: g is the gravity acceleration, and epsilon (t) is the cumulative sum of the centrifugal accelerations caused by the vibration modes of different orders in different directions;
and S5, adding an angle measurement error caused by the centrifugal acceleration to the angle value measured by the attack angle sensor in real time, and then carrying out 1Hz low-pass filtering to obtain the test model attack angle value after the vibration influence is corrected.
In the above technical solution, the acceleration integral signal is obtained by the following process:
s201, synchronously acquiring output signals q (t), a of three sensors1j(t)、a2j(t), j is x, y, z, q (t) is an output signal of the attack angle sensor, a1j(t) is the output signal of the first acceleration sensor in the j direction, a2j(t) is the output signal of the second acceleration sensor in the j direction;
s202, calculating the frequency spectrum signal of q (t), calculating q (t) and a1j(t) calculating a cross-power spectrum and a cross-spectrum coherence function;
s203, identifying the frequency of the corresponding vibration mode based on the frequency spectrum correlation of the frequency spectrum signal and the cross-spectrum correlation function;
s204: respectively carrying out band-pass filtering processing on the two triaxial acceleration signals around the vibration modal frequency to obtain band-pass filtered signals;
and S205, integrating the acceleration signal after the band-pass filtering to obtain an acceleration integral signal.
In the above technical solution, the frequency of the ith order vibration mode of the test model in the j direction is defined as ωjiI 1, …, n, for acceleration signal a1j(t)、a2j(t) j component of [ omega ]ji-0.5,ωji+0.5]The band-pass filtering process of (2).
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
according to the method, the two triaxial acceleration sensors are additionally arranged in the axial direction of the attack angle sensor, the centrifugal acceleration of the attack angle sensor under different vibration modes can be calculated, and further the correction of the angle measurement error of the attack angle sensor caused by vibration can be realized.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic view of an angle of attack sensor vibration effect correction sensor arrangement;
FIG. 2 is a schematic flow diagram of the present invention;
FIG. 3 is a comparison of angle measurement before correction of the effect of vibration of the angle of attack sensor to the true angle of attack value;
FIG. 4 is a difference between an angle measurement before an effect of vibration of an angle of attack sensor is corrected and a true angle of attack value;
FIG. 5 is a centrifugal acceleration induced by a first order vibrational mode in the Y-axis direction;
FIG. 6 is a centrifugal acceleration due to a second order vibration mode in the Y-axis direction;
FIG. 7 is the centrifugal acceleration due to the first order vibrational mode in the X-axis direction;
FIG. 8 is a centrifugal acceleration due to a first order vibrational mode in the Z-axis direction;
FIG. 9 is an angular deviation amount due to centrifugal acceleration caused by vibration;
FIG. 10 is a difference between an angle measurement and a true angle of attack value after an effect of vibration of an angle of attack sensor has been corrected;
wherein: 1. 2 is a triaxial acceleration sensor, 3 is an attack angle sensor, and theta is the attack angle value of the test model at the moment.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification (including any accompanying claims, abstract and drawings), may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
In the embodiment, two triaxial acceleration sensors are additionally arranged to correct the vibration influence of the attack angle sensor, the sensor arrangement structure is shown in fig. 1, the attack angle sensor and the two triaxial acceleration sensors are placed in the test model along the coaxial direction of the supporting rod, the two triaxial acceleration sensors are symmetrically placed on two sides of the attack angle sensor, and the distance between the two triaxial acceleration sensors is r. The output signals of the three sensors are connected to a data processing computer through a signal amplifier and a high-precision synchronous data acquisition card, and the correction of the vibration influence of the attack angle sensor is finally realized in the data processing computer through three steps of data preprocessing, centrifugal acceleration estimation and angle data correction.
The present embodiment is divided into three parts:
data preprocessing: the method comprises the steps of synchronously acquiring unfiltered signals of three sensors, carrying out spectrum analysis, power spectrum analysis and cross-spectrum coherence function calculation, identifying vibration frequencies corresponding to multi-order vibration modes in different directions of a test model supporting system, and carrying out band-pass filtering on output signals of two triaxial acceleration sensors around the vibration frequencies of different orders to obtain acceleration signals after band-pass filtering.
Estimating centrifugal acceleration: and integrating the acceleration signals subjected to the band-pass to obtain acceleration integral signals, then calculating the centrifugal acceleration caused by different orders of vibration modes, and further obtaining the sum of the centrifugal acceleration caused by the vibration.
Angle data correction: and calculating the sum of angle measurement errors caused by centrifugal acceleration, adding the sum of the angle measurement errors and the angle value measured by the attack angle sensor in real time, and then carrying out 1Hz low-pass filtering to obtain the test model attack angle value after the vibration influence is corrected.
The specific steps for correcting the vibration influence are as follows:
s1, synchronously acquiring output signals of three sensors by using a high-precision synchronous data acquisition card, and respectively recording the output signals as q (t), a1j(t) and a2j(t)，j＝x,y,z；
S2, calculating the frequency spectrum signal F of q (t)q(ω), calculating q (t) and a1j(t) ofSelf-power spectrum Sqq(omega) and S1jj(omega), calculating the cross-power spectrum Sqj(omega) and the cross-spectral coherence function Hqj(ω)；
S3-based on Fq(omega) and Hqj(omega) spectral dependence identifying a corresponding vibrational mode frequency spectrum omegajiI is 1, …, n, where i is the order of the vibration mode;
s4 surrounding the vibration mode frequency omegajiRespectively carrying out [ omega ] on the j components of the two triaxial acceleration signalsji-0.5,ωji+0.5]Obtaining the signal a after band-pass filtering1dji(t) and a2dji(t)；
S5, integrating the acceleration signal after the band-pass to obtain an acceleration integral signal V1dji(t) and V2dji(t)；
S6, calculating the centrifugal acceleration caused by the vibration modes of different orders in different directions by the following formula:
s7, adding the sum of the centrifugal accelerations caused by the vibration modes of different orders in different directions into the following steps:
s8, calculating the angle deviation amount caused by centrifugal acceleration caused by vibration:
wherein: g is the gravitational acceleration.
S9, carrying out 1Hz low-pass filtering on the angle of attack sensor signal q (t), and then calculating the corresponding model angle alphaq(t)；
S10, correcting the model angle value measured by the attack angle sensor to obtain the measured value alpha (t) ═ alphaq(t)+αε(t); thereby making it possible to further improve the quality of the imageAnd alpha (t) is subjected to 1Hz low-pass filtering to obtain a model attack angle value after the vibration influence is corrected.
Example one
Take one test run with mach number of 0.76 as an example: a triaxial acceleration sensor is respectively arranged at the front and the back 5cm positions of the x-axis direction of the attack angle sensor, and the sampling frequency of 1000Hz is adopted to synchronously acquire real-time data of the attack angle sensor and the two acceleration sensors.
Carrying out 1Hz low-pass filtering on the attack angle sensor, and calculating the measured value alpha of the attack angle sensorq(t), the accurate angle of attack value and the uncorrected angle of attack value measured by the angle of attack sensor are shown in FIG. 3. Fig. 4 shows the difference between the angle measurement value before the correction of the influence of the vibration of the angle of attack sensor and the true angle of attack value.
Calculating the frequency spectrum signal F of the angle of attack sensorq(ω), calculating q (t) and a1j(t) self-Power Spectrum Sqq(omega) and S1jj(omega), calculating the cross-power spectrum Sqj(omega) and the cross-spectral coherence function Hqj(ω); based on Fq(omega) and Hqj(ω) the spectral dependence of (ω) identifies a corresponding vibration modal frequency spectrum ωjiI is 1, …, n, where i is the order of the vibration mode; the first-order vibration frequency in the Y-axis direction is 7.53Hz, the second-order vibration frequency in the Y-axis direction is 14.65Hz, the first-order vibration frequency in the X-axis direction is 7.54Hz, and the first-order vibration frequency in the Z-axis direction is 6.48 Hz.
Respectively carrying out [ omega ] on the j components of the two triaxial acceleration signals around the frequencies of different vibration modes in different directionsji-0.5,ωji+0.5]Obtaining a signal a after band-pass filtering1dji(t) and a2dji(t); integrating the acceleration signal after the band-pass to obtain an acceleration integral signal V1dji(t) and V2dji(t); and further calculating the centrifugal acceleration caused by the vibration modes of different orders in different directions.
The centrifugal acceleration caused by the first-order vibration mode in the Y-axis direction is shown in fig. 5, the centrifugal acceleration caused by the second-order vibration mode in the Y-axis direction is shown in fig. 6, the centrifugal acceleration caused by the first-order vibration mode in the X-axis direction is shown in fig. 7, and the centrifugal acceleration caused by the first-order vibration mode in the Z-axis direction is shown in fig. 8.
The sum of the centrifugal accelerations caused by the vibration modes of different orders in different directions is added up, and the total angular deviation amount caused by the centrifugal acceleration caused by the vibration is calculated as shown in fig. 9.
And correcting the model angle value measured by the attack angle sensor to obtain the model attack angle value after the vibration influence is corrected. Fig. 10 shows the difference between the corrected angle measurement value and the true angle of attack due to the influence of the vibration of the angle of attack sensor.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (3)
1. A method for correcting the influence of vibration of an attack angle sensor of a temporary rush type high-speed wind tunnel is characterized by comprising the following steps:
s1, symmetrically arranging a triaxial acceleration sensor at each axial side of the angle of attack sensor in the test model provided with the angle of attack sensor;
s2, during a blowing test, synchronously acquiring unfiltered signals of two triaxial acceleration sensors and an attack angle sensor, carrying out spectrum analysis, power spectrum analysis and cross-spectrum coherence function calculation on the signals, identifying vibration frequencies corresponding to multi-order vibration modes in different directions of a test model supporting system, and carrying out band-pass filtering on output signals of the two triaxial acceleration sensors around the vibration frequencies in different directions and different orders to obtain band-pass filtered acceleration signals;
s3: integrating the acceleration signals after the band-pass filtering to obtain acceleration integral signals, and then calculating the centrifugal acceleration caused by the vibration modes of different orders in different directions as follows:
wherein V1dji(t) and V2dji(t) are respectively two three axesAn acceleration integral signal of the acceleration sensor, wherein r is the distance between two triaxial acceleration sensors, j is the direction, and j is the order of a vibration mode;
s4: obtaining the sum of angle errors of the attack angle sensor caused by centrifugal acceleration caused by vibration:
wherein: g is the gravity acceleration, and epsilon (t) is the accumulated sum of the centrifugal accelerations caused by the vibration modes of different orders in different directions;
and S5, adding the angle measurement error caused by the centrifugal acceleration and the angle value measured by the attack angle sensor in real time, and then carrying out 1Hz low-pass filtering to obtain the attack angle value of the test model after the vibration influence is corrected.
2. The method for correcting the influence of the vibration of the attack angle sensor of the temporary rush high-speed wind tunnel according to claim 1, wherein the acceleration integral signal is obtained by the following steps:
s201, synchronously collecting output signals q (t), a of three sensors1j(t)、a2j(t), j is x, y, z, q (t) is an output signal of the attack angle sensor, a1j(t) is the output signal of the first acceleration sensor in the j direction, a2j(t) is the output signal of the second acceleration sensor in the j direction;
s202, calculating the frequency spectrum signal of q (t), calculating q (t) and a1j(t) self-power spectra, cross-power spectra, and cross-spectral coherence functions;
s203, identifying the frequency of the corresponding vibration mode based on the frequency spectrum correlation of the frequency spectrum signal and the cross-spectrum correlation function;
s204: performing band-pass filtering processing on the two triaxial acceleration signals respectively around the vibration modal frequency to obtain band-pass filtered signals;
and S205, integrating the acceleration signal after the band-pass filtering to obtain an acceleration integral signal.
3. The method according to claim 2, wherein the frequency of the ith order vibration mode of the test model in the j direction is defined as ωjiI is 1, …, n, for acceleration signal a1j(t)、a2j(t) j component of [ omega ]ji-0.5,ωji+0.5]The band-pass filtering process of (2).
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| CN113639954B (en) * | 2021-10-18 | 2021-12-28 | 中国空气动力研究与发展中心高速空气动力研究所 | Model inclination angle measuring device suitable for 1-meter-scale high-speed wind tunnel test |
| CN117419887B (en) * | 2023-12-19 | 2024-03-12 | 中国空气动力研究与发展中心高速空气动力研究所 | ABZ type inclination sensor Z signal interference correction method for wind tunnel test environment |
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