CN112556930B - Helicopter movable part vibration signal data quality calculation method - Google Patents
Helicopter movable part vibration signal data quality calculation method Download PDFInfo
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- CN112556930B CN112556930B CN202011562132.5A CN202011562132A CN112556930B CN 112556930 B CN112556930 B CN 112556930B CN 202011562132 A CN202011562132 A CN 202011562132A CN 112556930 B CN112556930 B CN 112556930B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/14—Determining unbalance
- G01M1/16—Determining unbalance by oscillating or rotating the body to be tested
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
- G06F17/10—Complex mathematical operations
- G06F17/14—Fourier, Walsh or analogous domain transformations, e.g. Laplace, Hilbert, Karhunen-Loeve, transforms
- G06F17/141—Discrete Fourier transforms
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention provides a helicopter movable part vibration signal data quality calculation method, which comprises the following steps of: A. setting vibration sampling frequency and sampling time, and synchronously acquiring vibration signals and rotation speed signals; B. averagely dividing the vibration signal and the rotating speed signal into n sections, and intercepting each section of vibration signal according to the synchronous rotating speed signal to carry out time domain average processing; C. sequentially carrying out FFT conversion on the n time domain synchronous average signals, and extracting the amplitude and the phase of the n rotating speed same-frequency vibration signals; D. eliminating abnormal values of the amplitudes of the n rotating speed same-frequency vibration signals by using a 3 delta rule; E. calculating the quality of dynamic balance data according to the maximum value and the minimum value of the amplitude of the residual rotating speed same-frequency vibration signals; F. and if the mass of the dynamic balance data is smaller than the mu, calculating the average value of the amplitude and the phase of the residual rotating speed same-frequency vibration signal, and otherwise, returning to the step A. The method can effectively improve the accuracy of the helicopter dynamic balance test result and reduce the on-site dynamic balance adjustment times.
Description
Technical Field
The invention relates to the field of helicopter vibration health monitoring, in particular to a method for calculating the data quality of vibration test signals of a helicopter rotor system and a transmission system.
Background
The helicopter maneuvering components mainly comprise a main rotor, a tail rotor, a speed reducer, an engine, a transmission system and the like, and the flight safety of the helicopter can be directly and seriously affected by the structural damage of various maneuvering components, so that the monitoring and the evaluation of the structural health condition of the helicopter maneuvering components have very important significance. Structural damage or abnormality of helicopter movable parts can be generally expressed as vibration abnormality of each movable part of the helicopter, and the health condition of the movable parts can be accurately evaluated through vibration monitoring.
The helicopter mobile component balance test mainly adopts the steps of simultaneously measuring a rotating speed signal and a vibration signal, carrying out time domain synchronous average algorithm processing on a time domain signal, and then extracting amplitude and phase information of the vibration signal with the same frequency as the rotating speed. However, when a main rotor and a tail rotor of the helicopter run on the ground and fly in the air, due to the influence of external air flow and the structure of a rotor system of the helicopter, a vertical vibration signal of the main rotor and a vibration signal of the tail rotor are actually nonstationary signals with variable amplitudes, a plurality of measurement results calculated by the method have large deviation, field personnel cannot evaluate the accuracy of the test results, and the dynamic balance adjustment times of the main rotor and the tail rotor are increased. Therefore, the proper helicopter rotor system vibration signal data judging method is selected to judge the quality of the vibration signal in a certain test time interval, the accuracy of the dynamic balance test result can be effectively improved, and the on-site dynamic balance adjusting times are reduced.
Disclosure of Invention
The invention aims to provide a helicopter dynamic component vibration signal data quality calculation method which can effectively improve the accuracy of helicopter dynamic balance test results and reduce the on-site dynamic balance adjustment times.
In order to achieve the purpose, the invention adopts the technical scheme that:
a helicopter moving part vibration signal data quality calculation method comprises the following steps:
A. setting vibration sampling frequency and sampling time, and synchronously acquiring a vibration signal and a rotating speed signal according to the vibration sampling frequency and the sampling time;
B. averagely dividing the vibration signal and the rotating speed signal into n sections, intercepting each section of vibration signal according to the synchronous rotating speed signal, and carrying out time domain average processing to obtain n time domain synchronous average signals;
C. sequentially carrying out FFT conversion on the n time domain synchronous average signals, and extracting the amplitude and the phase of the n rotating speed same-frequency vibration signals;
D. eliminating abnormal values of the amplitudes of the n rotating speed same-frequency vibration signals by using a 3 delta rule, and searching the maximum value and the minimum value of the amplitudes of the residual rotating speed same-frequency vibration signals;
E. calculating the mass DATA _ qty = (Mag _ max-Mag _ min)/Mag _ max of the dynamic balance DATA, wherein the Mag _ max is the maximum value of the amplitude of the residual rotating speed co-frequency vibration signal, and the Mag _ min is the minimum value of the amplitude of the residual rotating speed co-frequency vibration signal;
F. and if the dynamic balance DATA quality DATA _ qty is smaller than mu, calculating the average value of the amplitude and the phase of the residual rotation speed same-frequency vibration signal, taking the average value as the amplitude and the phase of the current dynamic balance, and otherwise, returning to the step A.
And C, correcting the amplitudes and the phases of the extracted n rotating speed same-frequency vibration signals by adopting a ratio-based interpolation correction method.
And in the step B, the value of n is 10.
And F, taking the value of the mu to be 0.05.
According to the invention, by calculating the data quality of the vibration test result of the rotor system, the stability of the current helicopter rotor system signal can be effectively evaluated, so that the accuracy of the dynamic balance test result of the rotor system on site is improved, the external field dynamic balance adjustment times are reduced, the fault elimination efficiency on site is improved, the startup times are reduced, and the service life of an engine is prolonged.
Drawings
FIG. 1 is a schematic flow diagram of the present invention;
fig. 2 is a schematic diagram of a vibration signal interception process in the embodiment of the present invention.
Detailed Description
As shown in fig. 1, the method for calculating the data quality of the vibration signal of the helicopter moving component according to the present invention comprises the following steps:
A. and setting proper vibration sampling frequency and sampling time, and synchronously acquiring a vibration signal and a rotating speed signal according to the vibration sampling frequency and the sampling time.
As shown in fig. 2, in this embodiment, the sampling frequency of the vibration signal and the rotation speed signal is 4096Hz according to the rotation speeds of the main rotor and the tail rotor of the helicopter, and the synchronous sampling time is the time interval of 50 times of triggering of the rotation speed sensor by the measured component.
B. Averagely dividing the vibration signal and the rotating speed signal into n sections, intercepting each section of vibration signal according to the synchronous rotating speed signal, and carrying out time domain average processing to obtain n time domain synchronous average signals.
As shown in fig. 2, in this embodiment, the time interval of continuously triggering the high level for 5 times by the rotation speed signal is a cycle, the vibration signal acquired synchronously with the rotation speed signal is divided into 10 segments, and 10 vibration signals triggered by the rotation speed signal are intercepted to perform time domain average processing.
By adopting time domain synchronous average processing, signal components irrelevant to the rotation frequency of the shaft, including noise and irrelevant periodic signals, can be effectively eliminated, and the signal-to-noise ratio of the known periodic signals is improved. The time domain synchronous averaging processing is the prior art, and the implementation process is as follows:
(1) Establishing a frequency conversion time scale according to the rotating speed signal; (2) Segmenting the vibration signal according to the frequency conversion time scale, wherein 10 frequency conversion time scales are taken in the embodiment; (3) And superposing and averaging the signals after each section of resampling interpolation to obtain an averaged signal.
C. And sequentially carrying out FFT (fast Fourier transform) conversion on the n time domain synchronous average signals, and extracting the amplitude and the phase of the n rotating speed same-frequency vibration signals.
Furthermore, the embodiment also adopts an interpolation correction method based on the ratio to correct the amplitude and the phase of the extracted n rotating speed same-frequency vibration signals, so that the precision of the frequency, the amplitude and the phase in the discrete frequency spectrum obtained by Fourier transform can be effectively improved.
Firstly, determining a spectral peak to be interpolated by an interpolation correction method based on a ratio; then, the amplitude ratio of the highest peak and the secondary peak in the main lobe is obtained (the ratio depends on the type of the window function, the width of the frequency interval and the position of the main peak in the interval); and establishing an equation with the correction frequency as a variable, solving the correction frequency, and then correcting the amplitude and the phase.
D. And (3) eliminating abnormal values of the amplitudes of the n rotating speed same-frequency vibration signals by using a 3 delta rule, namely eliminating vibration amplitudes exceeding 3 times of standard deviation from the n vibration amplitudes, leaving vibration amplitudes within 3 times of the standard deviation, and then searching the maximum value and the minimum value of the amplitudes of the remaining rotating speed same-frequency vibration signals.
E. And calculating the dynamic balance DATA quality DATA _ qty = (Mag _ max-Mag _ min)/Mag _ max, wherein Mag _ max is the maximum value of the amplitude of the same-frequency vibration signals of the residual rotating speed, and Mag _ min is the minimum value of the amplitude of the same-frequency vibration signals of the residual rotating speed.
F. And if the dynamic balance DATA quality DATA _ qty is smaller than the [ mu ], calculating the average value of the amplitude and the phase of the residual rotation speed same-frequency vibration signals, taking the average value as the amplitude and the phase of the current dynamic balance, otherwise, returning to the step A, and performing the helicopter dynamic balance test again. In this embodiment, the value of μ is 0.05.
According to the invention, the stability of the current helicopter rotor system signal can be effectively evaluated by calculating the data quality of the test result of the helicopter rotor system. The smaller the data quality calculation value is, the more stable the test signal is, and the more accurate the helicopter dynamic balance test result is. Otherwise, the test signal is unstable, and the dynamic balance test of the rotor system needs to be carried out again. When the test result is more accurate, field maintenance personnel can quickly calculate the weight of the counterweight plate by the helicopter balance eight diagrams or a vector decomposition method, so that the fault elimination efficiency of the field is improved, the starting test times are reduced, and the service life of an engine is prolonged.
Claims (2)
1. A helicopter moving part vibration signal data quality calculation method is characterized by comprising the following steps:
A. setting vibration sampling frequency and sampling time, and synchronously acquiring a vibration signal and a rotating speed signal according to the vibration sampling frequency and the sampling time; setting the sampling frequency of a vibration signal and a rotating speed signal according to the rotating speeds of a main rotor and a tail rotor of the helicopter, wherein the synchronous sampling time is a time interval of triggering a rotating speed sensor by a tested part for 50 times;
B. averagely dividing the vibration signal and the rotating speed signal into n sections, and intercepting each section of vibration signal according to the synchronous rotating speed signal to carry out time domain average processing to obtain n time domain synchronous average signals; taking the time interval of continuous triggering of high level for 5 times by the rotating speed signal as a period, dividing the vibration signal synchronously acquired with the rotating speed signal into 10 sections, and intercepting 10 vibration signals triggered by the rotating speed signal for time domain average processing; by adopting time domain synchronous average processing, the signal component irrelevant to the rotation frequency of the shaft is effectively eliminated, and the signal-to-noise ratio of the known periodic signal is improved;
the time domain synchronous averaging process is realized as follows: (1) establishing a frequency conversion time scale according to the rotating speed signal; (2) Segmenting the vibration signal according to the frequency conversion time scale, and taking 10 frequency conversion time scales; (3) Superposing and averaging the signals after each section of resampling interpolation to obtain an averaged signal;
C. sequentially carrying out FFT conversion on the n time domain synchronous average signals, and extracting the amplitude and the phase of the n rotating speed same-frequency vibration signals;
the amplitude and the phase of the extracted n rotating speed same-frequency vibration signals are corrected by adopting an interpolation correction method based on the ratio, so that the precision of the frequency, the amplitude and the phase in the discrete frequency spectrum obtained by Fourier transform is effectively improved;
firstly, determining a spectral peak to be interpolated by an interpolation correction method based on a ratio; then, the amplitude ratio of the highest peak and the secondary peak in the main lobe is calculated; establishing an equation with the correction frequency as a variable, solving the correction frequency, and then correcting the amplitude and the phase;
D. removing abnormal values of the amplitudes of the n rotating speed same-frequency vibration signals by using a 3 delta rule, namely removing vibration amplitudes exceeding 3 times of standard deviation from the n vibration amplitudes, leaving vibration amplitudes within 3 times of the standard deviation, and then searching the maximum value and the minimum value of the amplitudes of the remaining rotating speed same-frequency vibration signals;
E. calculating the mass DATA _ qty = (Mag _ max-Mag _ min)/Mag _ max of the dynamic balance DATA, wherein the Mag _ max is the maximum value of the amplitude of the residual rotating speed co-frequency vibration signal, and the Mag _ min is the minimum value of the amplitude of the residual rotating speed co-frequency vibration signal;
F. if the dynamic balance DATA quality DATA _ qty is smaller than mu, calculating the average value of the amplitude and the phase of the residual rotating speed same-frequency vibration signals, taking the average value as the amplitude and the phase of the current dynamic balance, otherwise, returning to the step A, and performing the helicopter dynamic balance test again; the mu value is 0.05.
2. The helicopter mobile vibration signal data quality calculation method of claim 1, characterized by a sampling frequency of 4096Hz.
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