CN107766611B - Real-time calculation method for vibration monitoring parameters of power device accessory system in flight test - Google Patents
Real-time calculation method for vibration monitoring parameters of power device accessory system in flight test Download PDFInfo
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- CN107766611B CN107766611B CN201710804427.0A CN201710804427A CN107766611B CN 107766611 B CN107766611 B CN 107766611B CN 201710804427 A CN201710804427 A CN 201710804427A CN 107766611 B CN107766611 B CN 107766611B
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Abstract
The invention relates to a method for calculating vibration monitoring parameters of an accessory system of a power device in real time in a flight test, which comprises the steps of acquiring vibration signals of the accessory system and engine speed signals in real time in the vibration monitoring technology of the accessory system of the power device, inputting the vibration signals and the engine speed signals into embedded airborne acquisition/processing equipment, loading a real-time calculation program of vibration total amount/component of the accessory system of the power device in the equipment, resolving the vibration total amount and the component value of the accessory system in real time, and outputting a calculation result to an airborne telemetering system for ground safety monitoring. The invention has the main advantages that: 1) A broadband noise filtering function is integrated into the algorithm, and the reliability of a calculation result is guaranteed under airborne test environments such as a flight test and the like; 2) Error correction is introduced after time-frequency analysis, so that the calculation precision is improved while enough time resolution is ensured, and the transient response and the calculation precision of the vibration monitoring quantity are considered; 3) The method can adapt to airborne acquisition/processing hardware equipment of different platforms, and has strong universality and expansibility.
Description
Technical Field
The invention belongs to a real-time monitoring technology for vibration signals of an aviation power device.
Background
The vibration monitoring technology of the aviation power device is that vibration signals of typical parts of the power device are collected in real time in a flight test, and vibration characteristic parameters with high correlation degree with faults which are easy to occur, such as a vibration total value, a vibration component value of a key component and the like, are calculated in real time. By monitoring the vibration characteristic quantity value and giving alarm information when the vibration characteristic quantity value is abnormal, the fault deterioration is prevented, and the flight safety is guaranteed.
The vibration monitoring technology of the aeronautical power device belongs to a branch of engine state monitoring and fault diagnosis technology, in the 20 th century and 80 years, in order to support the concept of engine maintenance according to circumstances, aeronautical developed countries such as the United states and the like begin to develop the engine vibration monitoring technology, the system is sequentially equipped on the aspects of military machines on the models of F404, TF34, ALL-31 phi and the like, and the vibration monitoring components are equipped on the aspects of civil machines, CF34-10A, CFM56-7B and the like. Almost all new-developed aircraft engines today are equipped with sophisticated, reliable vibration monitoring systems. However, since the overall technical development of the aircraft engine lags behind, domestic autonomous development of power plant vibration monitoring technology is still immature.
Engine accessories and aircraft accessories are one of the most important transmission systems in an aircraft, and are bridges for connecting a power plant and various accessory devices and realizing power transmission. However, in practical flight applications, gear transmission systems such as part of engine accessories and airplane accessories are always fault-prone components, the replacement frequency is high, and there is an urgent need for introducing vibration safety monitoring. The power device accessory system is a gear transmission mechanism, and vibration sources are mostly gear meshing frequencies, so that the vibration frequency is high, the frequency changes along with the rotating speed, higher time resolution is needed in the real-time extraction process of vibration characteristic parameters, and the calculation precision can be obviously reduced if the existing time-frequency analysis technology is simply utilized. In addition, long-term test flight vibration data processing experience shows that broadband noise signals are often mixed in airborne test signals, and calculation results are seriously interfered if effective filtering measures are not taken.
Disclosure of Invention
The purpose of the invention is:
the method is used for calculating the vibration total quantity/component of the power device accessory system in real time in flight test, and real-time calculation and safety monitoring of the vibration characteristic quantity of the engine accessory and the aircraft accessory in flight are realized by combining the algorithm with necessary hardware equipment. The invention provides a real-time vibration total and component calculation method aiming at the vibration characteristics of a power device accessory system and an airborne test environment, and the method can be applied to the vibration monitoring of the power device accessory system in a flight test.
The technical scheme of the invention is as follows:
the vibration monitoring technology of the accessory system of the power device needs to acquire the vibration signal of the accessory system and the rotating speed signal of an engine in real time and input the signals into embedded airborne acquisition/processing equipment, load a real-time calculation program of the vibration total amount/component of the accessory system of the power device in the equipment, calculate the vibration total amount and the component value of the accessory system in real time, and output the calculation result to an airborne telemetering system for ground safety monitoring, wherein the working principle of the system is shown in figure 1.
The invention relates to a real-time calculation method for vibration total amount/component of an aircraft engine accessory system in a flight test, an algorithm flow is shown in figure 2, and the method mainly comprises the following steps:
1) Calculating the rotating speed in real time and adding a correction limit to the vibration data; the algorithm calculates the engine speed N at fixed time intervals Deltat 2 Let the relative error of the rotation speed be E n Adding a correction limit to the vibration data, and converting the voltage value output by the vibration sensor into a vibration physical quantity a (n);
2) Calculating vibration component frequency bands; according to the rotational speed N 2 Calculating the frequency band range of the vibration component of interest, wherein C n Is the frequency conversion coefficient between the engine speed and the related vibration component, and deltaf is the short-time Fourier transform frequency resolution;
[N 2 *C n -(N 2 *C n *E n +Δf)，N 2 *C n +(N 2 *C n *E n +Δf)]
3) Carrying out short-time Fourier transform on the vibration data; obtaining frequency spectrum data as A (m), and the frequency resolution is as follows:
4) Extracting an original vibration component; extracting peak value A in vibration component frequency band in frequency spectrum data c As the original vibration component;
5) Screening vibration data frequency domains; for frequency spectrum dataA (m) sets a noise filtering threshold value L according to the broadband noise level counted by observation n Screening out the effective component A in the frequency domain e (k)；
6) Correcting time-frequency analysis errors; according to the distribution rule of the error after the short-time Fourier transform in the frequency spectrum, the original vibration component value A is divided into c With the active ingredient A e (k) Error correction is carried out, and result precision is improved;
7) Synthesizing the vibration total amount; according to the effective component A e (k) The result after error correction is synthesized into a vibration total amount result A in the concerned frequency band t ；
8) Smoothing and filtering the result; because the instantaneous fluctuation in the working process of the power device and the noise error introduced in the signal processing process can cause the fluctuation of the calculation result, the real-time monitoring is inconvenient, and the output vibration total amount result A needs to be obtained t And performing smooth filtering on the corrected vibration component result to improve the stability of the result.
The invention has the advantages that:
the invention has the main advantages that: 1) A broadband noise filtering function is integrated into the algorithm, and the reliability of a calculation result is guaranteed under airborne test environments such as a flight test and the like; 2) Error correction is introduced after time-frequency analysis, so that the calculation precision is improved while sufficient time resolution is ensured for equipment with fast vibration source frequency change, such as a power device accessory transmission system, and the transient response and the calculation precision of the vibration monitoring quantity are considered; 3) The adopted embedded development vibration monitoring system framework can adapt to airborne acquisition/processing hardware equipment of different platforms, has strong universality, can freely set calculation parameters to adapt to vibration monitoring of different objects, and has strong expansibility.
Drawings
Fig. 1 is a schematic diagram of the system operation.
FIG. 2 is a schematic diagram of real-time calculation of total/component vibration of an accessory system.
Detailed Description
Examples
In the embodiment, in the test flight process of the turbofan engine, the airborne vibration monitoring system adopts airborne acquisition/processing equipment with the algorithm program and the ARM + FPGA framework to monitor the total vibration amount and the characteristic components of the aeroengine accessory casing and the airplane accessory casing in a flight test in real time.
The vibration signal of the engine accessory system is formed by superposing five sinusoidal signals of 1000Hz-200g, 5000Hz-50g, 8000Hz-100g, 950Hz-20g and 4970Hz-150 g.
The vibration monitoring equipment calculates the total vibration to be 269.4g, and the relative error to the theoretical value of 274.6g is 1.9%.
Adjusting the frequency of a rotating speed signal input by the vibration monitoring equipment as follows in sequence: 1000Hz, the calculation result of the vibration component is 197g, and the error relative to the theoretical value is 1.5 percent; 5000Hz, the calculation result of the vibration component is 49.3g, and the error relative to the theoretical value is 1.4 percent; 950Hz, and the vibration component was calculated to be 20g, which was consistent with the theoretical value.
Assuming that the accessory system signal is composed of a 1000Hz-50g sinusoidal signal and a certain proportion of broadband random noise, the vibration monitoring system calculation results are shown in Table 1 below:
TABLE 1 anti-noise test results of the inventive Algorithm
The embodiment can obtain that the established real-time calculation method for the vibration total amount/component of the accessory system of the power device has higher calculation precision and stronger anti-interference characteristic, and completely meets the actual requirement of vibration monitoring of the accessory system of the power device in a flight test.
Claims (3)
1. The real-time calculation method for the vibration monitoring parameters of the accessory system of the power device in the flight test is characterized by comprising the following steps of: the vibration monitoring technology of the accessory system of the power device needs to acquire the vibration signal of the accessory system and the rotating speed signal of an engine in real time and input the vibration signal and the rotating speed signal of the accessory system into embedded airborne acquisition/processing equipment, a real-time calculation program of the vibration total amount/component of the accessory system of the power device is loaded in the equipment, the vibration total amount and the component value of the accessory system are calculated in real time, and the calculation result is output to an airborne telemetering system, and the method for monitoring and calculating the ground safety comprises the following steps:
1) Calculating the rotating speed in real time and adding a correction limit to the vibration data; the algorithm calculates the engine speed N at fixed time intervals Deltat 2 Let E be the relative error of the rotation speed n Adding a correction limit to the vibration data, and converting the voltage value output by the vibration sensor into a vibration physical quantity a (n);
2) Calculating vibration component frequency bands; according to the rotational speed N 2 Calculating the frequency band range of the vibration component of interest, wherein C n Is the frequency conversion coefficient between the engine speed and the related vibration component, and deltaf is the short-time Fourier transform frequency resolution;
[N 2 *C n -(N 2 *C n *E n +Δf)，N 2 *C n +(N 2 *C n *E n +Δf)]
3) Carrying out short-time Fourier transform on the vibration data; obtaining frequency spectrum data as A (m), and the frequency resolution is as follows:
4) Extracting an original vibration component; extracting peak value A in vibration component frequency band in frequency spectrum data c As the original vibration component;
5) Screening vibration data frequency domains; setting a noise filtering threshold value L for the frequency spectrum data A (m) according to the observed and counted broadband noise level n Screening out the effective component A in the frequency domain e (k)；
6) Correcting time-frequency analysis errors; according to the distribution rule of the error after the short-time Fourier transform in the frequency spectrum, the original vibration component value A is divided into c With the active ingredient A e (k) And error correction is carried out, and result precision is improved.
2. The calculation method according to claim 1, wherein step 6) is followed by vibration sum synthesis; according to the effective component A e (k) The result after error correction is synthesized into a vibration total amount result A in the concerned frequency band t 。
3. The calculation method according to claim 2, wherein the synthesized vibration amount and the corrected vibration component are subjected to smoothing filtering processing; because the instantaneous fluctuation in the working process of the power device and the noise error introduced in the signal processing process can cause the fluctuation of the calculation result, the real-time monitoring is inconvenient, and the output vibration total amount result A needs to be obtained t And performing smooth filtering with the corrected vibration component result to improve the stability of the result.
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