CN111104374B - Actually measured vibration data processing method and system - Google Patents
Actually measured vibration data processing method and system Download PDFInfo
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Abstract
The application belongs to the technical field of data processing, and relates to a method and a system for processing actually measured vibration data. The method comprises the steps of obtaining preset sampling rate and intercepting length parameters, and obtaining a plurality of original vibration data transmitted by each sensor channel of the airplane; intercepting data according to the interception length and the set step length in each flight state time period in each original vibration data; determining first intercepted data, wherein the first intercepted data is the intercepted data with the largest time domain amplitude mean value in each flight state time period in each original vibration data; and carrying out Fourier transform on the first intercepted data to obtain second intercepted data. According to the method and the device, the intercepted data are subjected to frequency domain conversion through intercepting the data and drawing the time domain curve, the frequency domain data are automatically classified and stored, the frequency domain curve is drawn, and all the intercepted data are summarized conveniently and subsequently according to a summarization method. According to the method and the device, the precision is ensured, and meanwhile, the data processing efficiency is improved by nearly two orders of magnitude.
Description
Technical Field
The application belongs to the technical field of data processing, and particularly relates to a method and a system for processing actually measured vibration data.
Background
The induction processing of the measured data of the airplane is an important means for developing the analysis of the measured data, but is also a very huge work at the same time, and is mainly embodied in the following aspects that firstly, the data reading is difficult, the number of data lines acquired by adopting a high sampling rate sensor is more, most software cannot be read or is slow to read, the sampling rate of the sensor is 12.8K, the number of data lines in 3-hour flight time is over hundred million lines, the reading time of individual software is longer, and meanwhile, higher requirements are put forward on the performance of a computer; secondly, data interception is difficult, and the data interception is very difficult due to the fact that the data are long and difficult to position; thirdly, the operation process is too complex, when dividing according to the flight states such as ground driving, rollout, takeoff and the like, a single channel needs to be intercepted for more than ten sections, when the number of the channels and the flight rise and fall are more, the number is very huge, and the manual processing process is very complicated; finally, the inductive processing of the power spectral density needs to be manually completed, which takes a long time.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present application provides a method and a system for processing measured vibration data, which are used to increase the data processing speed of the vibration data.
In a first aspect of the present application, a method for processing measured vibration data includes: acquiring preset sampling rate and interception length parameters, and acquiring a plurality of original vibration data transmitted by each sensor channel of the airplane; acquiring time periods of all flight states of the airplane; determining an absolute time sequence of each sampling point for intercepting each original vibration data; acquiring a time domain curve of each original vibration data according to the absolute time sequence; intercepting data according to the interception length and the set step length in each flight state time period in each original vibration data; determining first intercepted data, wherein the first intercepted data is the intercepted data with the largest time domain amplitude mean value in each flight state time period in each original vibration data; and carrying out Fourier transform on the first intercepted data to obtain second intercepted data.
Preferably, after the obtaining the second intercepted data, the method further includes: determining original vibration data and a flight state corresponding to the first intercepted data and the second intercepted data; constructing a storage structure defined by the source of the original vibration data and the flight state; storing the first and second truncated data in corresponding memory locations in the memory structure.
Preferably, the time period for acquiring each flight state of the aircraft includes: according to the flight state parameters of the airplane, the start time and the stop time of ground driving, sliding, taking off, climbing, cruising, flat flying acceleration and deceleration, hovering, high altitude M number, sideslip, rolling, gliding, landing impact and landing sliding of the airplane are determined.
Preferably, windowing of the data is included prior to performing the fourier transform.
In a second aspect of the present application, a measured vibration data processing system includes: the initialization module is used for acquiring preset sampling rate and intercepting length parameters and acquiring a plurality of original vibration data transmitted by each sensor channel of the airplane; the flight state time acquisition module is used for acquiring time periods of all flight states of the airplane; the absolute time sequence determining module is used for determining the absolute time sequence of each sampling point for intercepting the data of each original vibration data; the time domain curve acquisition module is used for acquiring a time domain curve of each original vibration data according to the absolute time sequence; the data interception module is used for intercepting data according to the interception length and the set step length in each flight state time period in each original vibration data; the intercepted data sampling module is used for determining first intercepted data, and the first intercepted data is the intercepted data with the largest time domain amplitude mean value in each flight state time period in each original vibration data; and the intercepted data processing module is used for carrying out Fourier transform on the first intercepted data to obtain second intercepted data.
Preferably, the data storage module is further included, configured to perform data storage after obtaining the second intercepted data, and the data storage module includes: the data source determining unit is used for determining original vibration data and a flight state corresponding to the first intercepted data and the second intercepted data; the data storage structure construction unit is used for constructing a storage structure limited by the source and the flight state of the original vibration data; and the classification storage unit is used for storing the first intercepted data and the second intercepted data in corresponding storage units in the storage structure.
Preferably, the time of flight acquisition module includes: according to the flight state parameters of the airplane, the starting time and the ending time of ground driving, sliding, taking off, climbing, cruising, flat flying acceleration and deceleration, hovering, high altitude large M number, sideslip, rolling, gliding, landing impact and landing sliding of the airplane are determined.
Preferably, the system further comprises a windowing module for windowing the data before performing fourier transform.
The application has the advantages that: the original data are sequentially and continuously and automatically read, intercepted and subjected to frequency domain conversion, so that time consumed by fussy manual operation is saved, meanwhile, the data are classified and stored, the data are convenient to summarize, and the data processing efficiency is improved by nearly two orders of magnitude.
Drawings
Fig. 1 is a flow chart of a method for processing measured vibration data according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are implementations that are part of this application and not all implementations. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
A first aspect of the present application provides a method for processing measured vibration data, as shown in fig. 1, which mainly includes:
s1, acquiring preset sampling rate and intercepting length parameters, and acquiring a plurality of original vibration data transmitted by each sensor channel of the airplane;
s2, acquiring time periods of all flight states of the airplane;
s3, determining absolute time sequences of sampling points for intercepting the original vibration data;
s4, acquiring a time domain curve of each original vibration data according to the absolute time sequence;
s5, intercepting data according to the interception length and the set step length in each flight state time period in each original vibration data;
s6, determining first intercepted data, wherein the first intercepted data are the intercepted data with the largest time domain amplitude mean value in each flight state time period in each original vibration data;
and S7, carrying out Fourier transform on the first intercepted data to obtain second intercepted data.
In the present application, step S1 is used to perform parameter initialization setting on each parameter, and mainly includes setting a sampling rate, setting a read filename, setting the on and off time of the acquisition instrument, saving a file directory setting, and intercepting a length setting.
In step S2, the specific time of each flight phase of the aircraft is obtained, so as to perform data interception from the original data according to the acquisition time, and it can be understood that, for different flight tests, the time of each flight phase of each flight is different, and step S2 is used for determining the specific start time and end time of each flight phase of different flight processes.
In the step S3, an absolute time sequence is generated by combining the sampling rate and the starting time of the recorder, then, a time domain curve related to the absolute time sequence and the vibration acceleration can be drawn for each original data, and the picture is stored according to a specified path so as to facilitate the judgment of data acquisition quality.
In step S5, data is intercepted according to the interception length and the set step length, for example, a takeoff phase, the time span of which is 11.
And S7, performing Fourier transform of the improved periodogram method on the first intercepted data to obtain second intercepted data.
It should be understood that the present application implements the above process through a plurality of nested loops, where the outermost layer processes the raw data for each channel, the middle layer processes the data of each flight phase in each raw data, and the innermost layer performs a plurality of data interception processes of each raw data segment, and the selection of intercepted data.
In some optional embodiments, after obtaining the second intercepted data, the method further includes:
determining original vibration data and flight states corresponding to the first intercepted data and the second intercepted data;
constructing a storage structure defined by the source of the original vibration data and the flight state;
and storing the first and second intercepted data in corresponding storage units in the storage structure.
It can be understood that the storage structure of the present application is generally a tree structure, such as a folder system of window, and by storing different data according to the source, it is convenient to summarize all intercepted data according to a summarization method in the following, and provide summarized data and curves.
In some optional embodiments, the acquiring the time period of each flight state of the aircraft includes:
according to the flight state parameters of the airplane, the starting time and the ending time of ground driving, sliding, taking off, climbing, cruising, flat flying acceleration and deceleration, hovering, high altitude large M number, sideslip, rolling, gliding, landing impact and landing sliding of the airplane are determined.
In some optional embodiments, before performing the fourier transform, a windowing process is included on the data. It should be appreciated that to reduce spectral leakage, the present application windows the signal after sampling, such as triangular windows, hanning windows, hamming windows, gaussian windows, and the like. The frequency resolution of the fourier analysis is mainly affected by the main lobe width of the window function, while the degree of leakage depends on the relative amplitude magnitude of the main lobe and the side lobes. The sidelobe is the highest without windowing, the frequency resolution is the highest, and the spectrum leakage is the largest. Different window functions are a compromise between frequency resolution and spectral leakage, and the application preferably uses a hanning window.
According to the method, the automation of the processes of complex data interception, processing, induction and the like is realized through an MATLAB program, the program firstly reads test data of each channel in sequence, an absolute time sequence of each sampling point is generated by combining given initial time and a sampling rate, vibration data in each flight state is automatically intercepted through a time system of flight parameters, intercepted data is automatically classified and stored, a time domain curve is drawn, then the intercepted time domain data is subjected to frequency domain conversion, the frequency domain data is automatically classified and stored, the frequency domain curve is automatically drawn, all intercepted data are conveniently induced subsequently according to an induction method, induced data and curves are given, and root mean square values are calculated and stored. The invention ensures the precision and improves the data processing efficiency by nearly two orders of magnitude.
The second aspect of the present application provides a measured vibration data processing system corresponding to the above method, which mainly includes:
the initialization module is used for acquiring preset sampling rate and interception length parameters and acquiring a plurality of original vibration data transmitted by each sensor channel of the airplane;
the flight state time acquisition module is used for acquiring time periods of all flight states of the airplane;
the absolute time sequence determining module is used for determining the absolute time sequence of each sampling point for intercepting the data of each original vibration data;
the time domain curve acquisition module is used for acquiring a time domain curve of each original vibration data according to the absolute time sequence;
the data interception module is used for intercepting data according to the interception length and the set step length in each flight state time period in each original vibration data;
the intercepted data sampling module is used for determining first intercepted data, and the first intercepted data is the intercepted data with the largest time domain amplitude mean value in each flight state time period in each original vibration data;
and the intercepted data processing module is used for carrying out Fourier transform on the first intercepted data to obtain second intercepted data.
In some optional embodiments, the apparatus further comprises a data storage module for performing data storage after obtaining the second intercepted data, the data storage module comprising:
the data source determining unit is used for determining original vibration data and a flight state corresponding to the first intercepted data and the second intercepted data;
a data storage structure construction unit for constructing a storage structure defined by the source of the original vibration data and the flight status;
and the classification storage unit is used for storing the first intercepted data and the second intercepted data in corresponding storage units in the storage structure.
In some optional embodiments, the time of flight acquisition module comprises:
according to the flight state parameters of the airplane, the start time and the stop time of ground driving, sliding, taking off, climbing, cruising, flat flying acceleration and deceleration, hovering, high altitude M number, sideslip, rolling, gliding, landing impact and landing sliding of the airplane are determined.
In some optional embodiments, the apparatus further comprises a windowing module configured to perform windowing on the data before performing fourier transform.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A method for processing measured vibration data, comprising:
acquiring preset sampling rate and interception length parameters, and acquiring a plurality of original vibration data transmitted by each sensor channel of the airplane;
acquiring time periods of all flight states of the airplane;
determining an absolute time sequence of each sampling point for intercepting each original vibration data;
acquiring a time domain curve of each original vibration data according to the absolute time sequence;
intercepting data according to the interception length and the set step length in each flight state time period in each original vibration data;
determining first intercepted data, wherein the first intercepted data is the intercepted data with the largest time domain amplitude mean value in each flight state time period in each original vibration data;
and carrying out Fourier transform on the first intercepted data to obtain second intercepted data.
2. The measured vibration data processing method of claim 1, wherein after obtaining the second truncated data, further comprising:
determining original vibration data and flight states corresponding to the first intercepted data and the second intercepted data;
constructing a storage structure defined by the source of the original vibration data and the flight state;
storing the first and second truncated data in corresponding memory locations in the memory structure.
3. The measured vibration data processing method of claim 1, wherein said obtaining a time period for each flight condition of the aircraft comprises:
according to the flight state parameters of the airplane, the starting time and the ending time of ground driving, sliding, taking off, climbing, cruising, flat flying acceleration and deceleration, hovering, high altitude large M number, sideslip, rolling, gliding, landing impact and landing sliding of the airplane are determined.
4. The method of measured vibration data processing according to claim 1, wherein prior to performing the fourier transform, comprising windowing the data.
5. A measured vibration data processing system, comprising:
the initialization module is used for acquiring preset sampling rate and intercepting length parameters and acquiring a plurality of original vibration data transmitted by each sensor channel of the airplane;
the flight state time acquisition module is used for acquiring time periods of all flight states of the airplane;
the absolute time sequence determining module is used for determining the absolute time sequence of each sampling point for intercepting the data of each original vibration data;
the time domain curve acquisition module is used for acquiring a time domain curve of each original vibration data according to the absolute time sequence;
the data interception module is used for intercepting data according to the interception length and the set step length in each flight state time period in each original vibration data;
the intercepted data sampling module is used for determining first intercepted data, and the first intercepted data is the intercepted data with the largest time domain amplitude mean value in each flight state time period in each original vibration data;
and the intercepted data processing module is used for carrying out Fourier transform on the first intercepted data to obtain second intercepted data.
6. The measured vibration data processing system of claim 5, further comprising a data storage module for data storage after obtaining the second truncated data, the data storage module comprising:
the data source determining unit is used for determining original vibration data and a flight state corresponding to the first intercepted data and the second intercepted data;
a data storage structure construction unit for constructing a storage structure defined by the source of the original vibration data and the flight status;
and the classification storage unit is used for storing the first intercepted data and the second intercepted data in corresponding storage units in the storage structure.
7. The measured vibration data processing system of claim 5, wherein said time of flight acquisition module comprises:
according to the flight state parameters of the airplane, the starting time and the ending time of ground driving, sliding, taking off, climbing, cruising, flat flying acceleration and deceleration, hovering, high altitude large M number, sideslip, rolling, gliding, landing impact and landing sliding of the airplane are determined.
8. The measured vibration data processing system of claim 5 further comprising a windowing module for windowing the data prior to performing the Fourier transform.
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