A method and device for processing and classifying helicopter flight vibration data

Abstract

The present application belongs to the field of helicopter vibration data processing, and relates to a method and device for processing and classifying helicopter flight vibration data. The method comprises: collecting flight vibration data of each measuring point position of a helicopter; classifying the helicopter flight vibration data according to a helicopter flight profile to determine the flight state in which the vibration response is located; classifying the flight vibration data according to the vibration environment requirements of the helicopter to determine the influence of different vibration sources of the helicopter on the measuring point position; for the same measuring point position, processing the flight vibration data of the measuring point position to obtain the vibration response of the measuring point position under the concerned vibration source in different flight states according to the flight profile; analyzing the obtained vibration response, analyzing the vibration response of each part of the helicopter in combination with the full-aircraft transfer function test and the component dynamic characteristic test, judging the accuracy and rationality of the vibration response of the machine body, and analyzing the helicopter full-aircraft flight vibration level in combination with the helicopter dynamics theory.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of helicopter vibration data processing, and relates to a helicopter flight vibration data processing and classification method and device. BACKGROUND

[0002] The helicopter has the hovering, side flight and reverse flight performance, which leads to the harsh vibration environment of the helicopter compared with other aircrafts. The vibration of the conventional helicopter is derived from the main rotor, tail rotor, speed reducer gear meshing and transmission system. It is necessary to measure the vibration response of the key positions in the scientific research flight test phase, on the one hand, to monitor whether the components are abnormal through the vibration of the key positions, and on the other hand, to provide the vibration environment spectrum for the on-board equipment. The reasonable vibration data processing and classification ensures the rationality of the on-board vibration response results, and provides support for the flight safety and vibration environment spectrum. SUMMARY

[0003] The purpose of the application is to provide a helicopter flight vibration data processing and classification method to meet the requirements of engineering design and application.

[0004] The technical scheme is:

[0005] In the first aspect, a helicopter flight vibration data processing and classification method is provided, comprising:

[0006] Collecting flight vibration data of each measuring point position of the helicopter;

[0007] Classifying the helicopter flight vibration data according to the helicopter flight spectrum to determine the flight state in which the vibration response is located;

[0008] Classifying the flight vibration data according to the helicopter vibration environment requirements to determine the influence of different vibration sources of the helicopter on the measuring point position;

[0009] For the same measuring point position, processing the flight vibration data of the measuring point position, and obtaining the vibration response of the measuring point position in different flight states under the concerned vibration source according to the flight spectrum;

[0010] Analyzing the obtained vibration response, analyzing the vibration response of each part of the helicopter in combination with the full machine transfer function test and the component dynamic characteristic test, judging the accuracy and rationality of the machine vibration response, and analyzing the helicopter full machine flight vibration level in combination with the helicopter dynamics theory.

[0011] Further, classifying the helicopter flight vibration data according to the helicopter flight spectrum to determine the flight state in which the vibration response is located, comprising:

[0012] Referring to the helicopter flight profile, vibration data of all flight cycles during flight is statistically analyzed according to flight states of specific conditions, to obtain helicopter flight state distribution of all flight cycles.

[0013] The flight vibration data is segmented according to the helicopter flight state distribution of all flight cycles.

[0014] Further, the flight vibration data is classified according to the helicopter vibration environment requirements, to determine the influence of different vibration sources of the helicopter on the measurement point position, including:

[0015] Referring to the relevant content of the helicopter vibration environment, the area where the measurement point is located is divided into a main speed reducer measurement point area, a cockpit vibration measurement point area and a transmission shaft part measurement point area, so as to realize the classification of the flight vibration data.

[0016] Further, for the same measurement point position, the flight vibration data of the measurement point position is processed, and the vibration response of the measurement point position under the concerned vibration source in different flight states is obtained according to the flight profile, including:

[0017] The flight vibration data of different areas is subjected to Fourier transform FFT, to obtain the vibration response of the measurement point position under the concerned vibration source in different flight states.

[0018] In a second aspect, a helicopter flight vibration data processing and classification device is provided, including:

[0019] The acquisition module is configured to acquire flight vibration data of each measurement point position of the helicopter;

[0020] The classification module is configured to classify the helicopter flight vibration data according to the helicopter flight profile, to determine the flight state in which the vibration response is located, and to classify the flight vibration data according to the helicopter vibration environment requirements, to determine the influence of different vibration sources of the helicopter on the measurement point position.

[0021] The processing module is configured to process the flight vibration data of the same measurement point position, to obtain the vibration response of the measurement point position under the concerned vibration source in different flight states according to the flight profile.

[0022] The analysis and judgment module is configured to analyze the obtained vibration response, to analyze the vibration response of each part of the helicopter in combination with the full machine transfer function test and the component dynamic characteristic test, to judge the accuracy and rationality of the machine vibration response, and to analyze the helicopter full machine flight vibration level in combination with the helicopter dynamics theory.

[0023] Further, the induction module is specifically configured to:

[0024] Referring to the helicopter flight profile, vibration data of all flight cycles during flight is statistically analyzed according to flight states under specific conditions, so as to obtain helicopter flight state distribution under all flight cycles.

[0025] The flight vibration data is segmented according to the helicopter flight state distribution under all flight cycles.

[0026] Further, the induction module is specifically used for:

[0027] Referring to the relevant content of the helicopter vibration environment, the area where the measuring point is located is divided into a main speed reducer measuring point area, a cockpit vibration measuring point area and a transmission shaft part measuring point area, so as to realize the classification of the flight vibration data.

[0028] Further, the processing module is specifically used for:

[0029] The flight vibration data of different areas is subjected to Fourier transform FFT, so as to obtain the vibration response of the measuring point position under the concerned vibration source under different flight states. DETAILED DESCRIPTION

[0030] A helicopter flight vibration data processing and classification method, the specific steps of which are as follows.

[0031] Step one, helicopter flight vibration data and flight parameter data acquisition

[0032] The vibration response of different positions of the machine body is collected through the on-board equipment, and the commonly used vibration sensor is a piezoelectric sensor. In order to better process the collected vibration data and flight parameter data, the storage format of the data is agreed as follows. The original signal data (after A / D conversion) is stored in binary (or decimal) format, and the channel number, data type and data unit and other information are marked in text mode. The data storage format is as follows.

[0033] Table 1 data storage format

[0034] Data Parameter 1 Data Parameter 2 …… 1st sample float (4 bytes) float (4 bytes) float (4 bytes) 2nd sample float (4 bytes) float (4 bytes) float (4 bytes) …… …… …… …… Nth sample float (4 bytes) float (4 bytes) float (4 bytes)

[0035] Step two, helicopter flight vibration data classification

[0036] 1. Vibration data and flight parameter data state classification based on helicopter flight state

[0037] From the helicopter dynamics theory, the flight state of the helicopter determines the size and direction of the hub force, and directly determines the vibration response of the vibration measuring point position. Referring to the helicopter flight profile, the vibration data of all flight cycles during the flight of the helicopter is statistically analyzed according to certain flight conditions, and the flight state distribution of the helicopter under all flight cycles is obtained. The helicopter flight dynamics theory points out that the flight state of the helicopter can be represented by the flight speed, flight height, flight weight center, pitch angle, roll angle and heading angle of the helicopter. The above parameters are selected to represent the flight state of the helicopter, and the specific information is shown in Table 2.

[0038] Table 2 Flight state judgment table

[0039]

[0040] According to the flight state judgment table, the state of the aircraft is judged by using a self-programmed program, and the flight state matrix FS is obtained as follows:

[0041]

[0042] t is represents the start time of the i-th flight state, t id represents the end time of the i-th flight state, and Sti represents the related parameters of the helicopter in the i-th flight state, which is composed of the flight parameters in Table 2.

[0043] Furthermore, by using the flight state matrix FS, the vibration data of all flight cycles of the helicopter is processed to obtain the vibration data matrix set VDi corresponding to the flight state,

[0044]

[0045] where m represents the length of the vibration time domain signal, n represents the channel of the measuring point on the machine, P = Fs*(t id -t is ), Fs is the sampling rate, and VD i represents the vibration data time domain signal corresponding to the i-th flight state.

[0046] 2. Classification of flight vibration data based on the influence area of vibration source

[0047] The helicopter body vibration is affected by multiple vibration sources simultaneously, and in the frequency domain of the helicopter measuring point, multiple frequencies act simultaneously, but in different areas of the helicopter, each vibration source has different effects. Referring to the relevant requirements of the helicopter vibration environment, the area where the helicopter vibration measuring point is located is divided into main speed reducer area measuring point, cockpit vibration area measuring point, transmission shaft area measuring point, engine area measuring point and helicopter tail area measuring point, and according to the position of the measuring point, the time domain signal of the measuring point is classified and divided. In different measuring point areas, refer to the requirements of the helicopter vibration environment, select the appropriate vibration source frequency as the frequency point of frequency domain analysis.

[0048] Step three, processing and analysis of classified helicopter flight vibration data

[0049] After the helicopter flight vibration data is classified in step two, the vibration time domain signals of each measuring point in different areas under all flight conditions are obtained.

[0050]

[0051] where P = Fs*(t id -t is ), Fs is the sampling rate, VD ij represents the vibration data time domain signal corresponding to the i-th flight state in the j-th area. Fj represents the considered vibration source frequency in the j-th area.

[0052] 1. Flight vibration data processing based on fast FFT calculation

[0053] First, the classified flight vibration signal is processed by fast FFT to obtain the vibration response Fr i in different flight conditions in different areas of the measuring point.

[0054]

[0055] Fr i represents the vibration response corresponding to the i-th flight state.

[0056] 2. Dynamics analysis based on frequency domain measuring point vibration response

[0057] First, in order to analyze the helicopter flight vibration level, the vibration response of the measuring point in different positions is analyzed. According to the helicopter dynamics theory, the vibration response of the measuring point at different frequencies with the change of flight speed is analyzed, and the correlation between the vibration response of the measuring point at different frequencies and the flight speed is obtained.

[0058] Secondly, in order to analyze the correlation between the helicopter blade load and the body vibration response, the correlation between the body vibration and the main blade load is analyzed through the main speed reducer area measuring point, and the correlation between the measuring point vibration and the tail blade load is analyzed through the tail area measuring point, so as to obtain the relationship between the blade load and the body vibration and provide the basis for the flight safety monitoring.

[0059] Furthermore, the accuracy and rationality of the body vibration response are judged by combining the full machine transfer function test, the component dynamic characteristic test results and the vibration response of the corresponding parts of the helicopter.

[0060] Finally, the vibration response values of different vibration source frequencies in different areas are counted, the values of the helicopter vibration environment technical requirements are corrected, and the reasonable vibration environment spectrum is provided for the on-board equipment.

Claims

1. A method of processing and classifying helicopter flight vibration data, characterized in that, The method comprises the following steps: collecting flight vibration data of each measuring point position of the helicopter; classifying the flight vibration data of the helicopter according to a flight profile of the helicopter to determine a flight state in which the vibration response is located; classifying the flight vibration data according to vibration environment requirements of the helicopter to determine influences of different vibration sources of the helicopter on the measuring point position; processing the flight vibration data of the same measuring point position to obtain vibration responses of the measuring point position under the vibration source of interest in different flight states according to the flight profile; analyzing the obtained vibration responses, combining a full-aircraft transfer function test and a component dynamic characteristic test to analyze vibration response conditions of each part of the helicopter, judging accuracy and rationality of the vibration response of the machine body, and combining helicopter dynamics theory to analyze the flight vibration level of the helicopter; classifying the flight vibration data of the helicopter according to the flight profile of the helicopter to determine the flight state in which the vibration response is located, which comprises the following steps: statistically analyzing vibration data of all flight cycles during flight according to flight states of specific conditions by referring to the flight profile of the helicopter to obtain distribution conditions of the helicopter flight state under all flight cycles; segmenting the flight vibration data according to the distribution conditions of the helicopter flight state under all flight cycles; classifying the flight vibration data according to vibration environment requirements of the helicopter to determine influences of different vibration sources of the helicopter on the measuring point position, which comprises the following steps: dividing a region where the measuring point is located into a main speed reducer measuring point region, a cockpit vibration measuring point region and a transmission shaft part measuring point region by referring to relevant contents of the vibration environment of the helicopter, so as to classify the flight vibration data; processing the flight vibration data of the same measuring point position to obtain vibration responses of the measuring point position under the vibration source of interest in different flight states according to the flight profile, which comprises the following steps: performing Fourier transform (FFT) on the flight vibration data of different regions to obtain the vibration responses of the measuring point position under the vibration source of interest in different flight states.

2. Apparatus for processing and classifying helicopter flight vibration data, characterised in that The device adopts the processing and classification method of the flight vibration data of the helicopter according to claim 1, and the device comprises: a collecting module configured to collect flight vibration data of each measuring point position of the helicopter; a classifying module configured to classify the flight vibration data of the helicopter according to a flight profile of the helicopter to determine a flight state in which the vibration response is located, and to classify the flight vibration data according to vibration environment requirements of the helicopter to determine influences of different vibration sources of the helicopter on the measuring point position; a processing module configured to process the flight vibration data of the same measuring point position to obtain vibration responses of the measuring point position under the vibration source of interest in different flight states according to the flight profile; an analysis and judgment module configured to analyze the obtained vibration responses, combine a full-aircraft transfer function test and a component dynamic characteristic test to analyze vibration response conditions of each part of the helicopter, judge accuracy and rationality of the vibration response of the machine body, and combine helicopter dynamics theory to analyze the flight vibration level of the helicopter; the classifying module is specifically configured to: statistically analyze vibration data of all flight cycles during flight according to flight states of specific conditions by referring to the flight profile of the helicopter to obtain distribution conditions of the helicopter flight state under all flight cycles. The flight vibration data is segmented according to the helicopter flight state distribution of all flight missions; The induction module is specifically used for: According to the related content of the helicopter vibration environment, the area where the measuring point is located is divided into a main speed reducer measuring point area, a cockpit vibration measuring point area and a transmission shaft part measuring point area, so as to realize the classification of the flight vibration data; The processing module is specifically used for: The flight vibration data of different areas is subjected to Fourier transform FFT, so as to obtain the vibration response of the measuring point position under the concerned vibration source in different flight states.

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