CN118088429B - A vibration collection system and use method for aviation high-pressure axial piston pump - Google Patents

Abstract

The invention discloses a vibration acquisition system of an aviation high-pressure axial plunger pump and a use method thereof, belonging to the technical field of aircraft hydraulic systems, wherein the vibration acquisition system comprises a test bed, a plurality of acceleration sensors, a charge amplifier and a signal analyzer; an axial plunger pump flange is fixed on the test stand; the charge amplifier is electrically connected with the signal analyzer; the contribution degree of each component of the aviation high-pressure axial plunger pump to vibration is judged by establishing a ground test bench, arranging acceleration sensors in different directions, collecting and decomposing vibration signals in different frequency bands, and the instantaneous acceleration value, the effective value and the full-period vibration characteristic in different frequency bands can be accurately captured, so that the characteristics in the signals are extracted and analyzed, a fault formation mechanism is finally obtained, the device is suitable for working environment sounds with loud noise in an aircraft system, and the problem that a hydraulic plunger pump fault diagnosis device in the prior art cannot be suitable for the aircraft system is solved.

Description

A vibration collection system and use method for aviation high-pressure axial piston pump

Technical Field

The invention belongs to the technical field of aircraft hydraulic systems, and in particular relates to an aviation high-pressure axial piston pump vibration collection system and a use method thereof.

Background technique

The hydraulic system is one of the three core systems of an aircraft. It is widely used in the aircraft's front wheel turning, landing gear retraction and extension, ailerons, slats, spoiler operation, main brakes, speed brake retraction and extension, elevators and rudders, etc., and is directly related to flight safety. The aviation high-pressure axial piston pump is the core component of the aircraft hydraulic system, and it is also one of the most faulty components in the hydraulic system. With the rapid development of high-pressure and high-speed aviation high-pressure axial piston pumps, the structure of the hydraulic system has become more complex, and the forms of failure have also increased.

In the prior art, there are diagnostic devices specifically for hydraulic piston pump faults, such as the patent publication number CN114109800A, which is named a hydraulic piston pump fault diagnosis device and method based on sound recognition technology. The device includes a microphone, a shielded wire, a sound card, a DSP sound processor, an AC contactor switch, etc. The hydraulic piston pump fault diagnosis device and method collect the working environment sound of the hydraulic piston pump and then analyze the fault of the hydraulic piston pump. It has the advantages of simple structure, fast response speed and high accuracy. However, the hydraulic piston pump fault diagnosis device and method are not suitable for aircraft systems, because in aircraft systems, the engine noise is much greater than the piston pump sound. The hydraulic piston pump fault diagnosis device and method cannot accurately collect the working environment sound of the hydraulic piston pump, resulting in the inability to accurately analyze the hydraulic piston pump fault and provide a theoretical basis for optimizing the various components in the axial piston pump.

Summary of the invention

In view of the above-mentioned deficiencies in the prior art, the present invention provides an aviation high-pressure axial piston pump vibration collection system and analysis method, which solves the problem that the hydraulic piston pump fault diagnosis device in the prior art cannot be applied to aircraft systems and thus cannot provide a theoretical basis for optimizing the various components in the axial piston pump.

In order to achieve the above-mentioned object of the invention, the technical solution adopted by the present invention is:

Provided is an aviation high-pressure axial piston pump vibration acquisition system, which includes a test bench, multiple acceleration sensors, a charge amplifier and a signal analyzer; an axial piston pump flange for mounting the axial piston pump is fixed on the test bench; the multiple acceleration sensors include an X-axis acceleration sensor, a Y-axis acceleration sensor and a Z-axis acceleration sensor electrically connected to the charge amplifier; the charge amplifier is electrically connected to the signal analyzer.

Furthermore, as specific selections of the X-axis acceleration sensor, the Y-axis acceleration sensor and the Z-axis acceleration sensor, the X-axis acceleration sensor, the Y-axis acceleration sensor and the Z-axis acceleration sensor are charge-type piezoelectric acceleration sensors with a measuring range of 1000g, a response frequency of 25KHz and an accuracy of ±0.5%.

Furthermore, the sampling frequency of the signal analyzer is 2 to 5 times the response frequency of the acceleration sensor. If the sampling rate is low when the plunger pump fails, the fault frequency may not be accurately sampled, but if it is 2 to 5 times, the fault frequency can be accurately included.

Furthermore, as a specific installation method of the X-axis acceleration sensor, the Y-axis acceleration sensor and the Z-axis acceleration sensor, the installation direction of the X-axis acceleration sensor and the Y-axis acceleration sensor is perpendicular to the axial piston pump rotation axis; the installation direction of the Z-axis acceleration sensor is parallel to the axial piston pump rotation axis.

Furthermore, the present invention also provides a method for using an aviation high-pressure axial piston pump vibration collection system, which comprises:

Step S1, installing the axial piston pump on the axial piston pump flange;

Step S2, starting the axial piston pump, and collecting acceleration signals of the three axes of X, Y, and Z in full frequency bands under different working conditions of the axial piston pump;

Step S3, obtaining effective values and maximum values of acceleration signals of multiple different frequency bands;

Step S4, comparing the effective values and maximum values of acceleration signals in multiple frequency segments, obtaining the components of the axial piston pump that affect the acceleration amplitude, and proposing an optimization rule.

Furthermore, in step S2, at least three cycles are collected for each working condition.

Further, in step S3, effective values of acceleration signals in frequency ranges of 0-1000 Hz, 1000 Hz-3000 Hz, 3000 Hz-6000 Hz and 6000 Hz-10000 Hz are obtained by band-pass filtering.

0~1000Hz is the base frequency range of the plunger pump, which mainly identifies the changes in the base frequency of the plunger pump; 1000Hz~3000Hz is the 1st or 2nd frequency of the plunger pump, and 3000Hz~6000Hz is the 3rd or 4th frequency of the plunger pump, which mainly identifies the high-order frequencies excited by the failure of the rotating parts; if 1000Hz~3000Hz cannot be identified, 3000Hz~6000Hz contains the corresponding characteristic high-order frequencies. 6000Hz~10000Hz is the high-frequency noise band.

Furthermore, in step S3, the effective value calculation formula of the acceleration signal is:

Where x(t) is the instantaneous acceleration amplitude at a certain moment, T is a cycle time, X _RMS is the effective value of acceleration in the T cycle, and t is a certain moment;

The maximum value of the acceleration signal is calculated as follows:

Among them, max is the symbol for finding the maximum value.

The beneficial effects of the present invention are as follows: the present invention provides an aviation high-pressure axial piston pump vibration collection system and use method, which determines the contribution of various components of the aviation high-pressure axial piston pump to the vibration by establishing a ground test bench, arranging acceleration sensors in different directions, and collecting and decomposing vibration signals in different frequency bands. The instantaneous value, effective value and full-cycle vibration characteristics of acceleration in different frequency bands can be accurately captured, thereby extracting and analyzing the features in the signal, and finally obtaining the mechanism of fault formation. The system can be applicable to the noisy working environment sound in the aircraft system, and solves the problem that the hydraulic piston pump fault diagnosis device in the prior art cannot be applied to the aircraft system.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG1 is a schematic diagram of the structure of a vibration collection system for an aviation high-pressure axial piston pump.

FIG. 2 is a schematic diagram of Z-axis acceleration values collected by a Z-axis acceleration sensor.

FIG. 3 is a schematic diagram of effective values of acceleration signals in the Z direction and the X direction.

FIG. 4 is a schematic diagram of effective values of Z-axis acceleration signals in multiple frequency bands.

FIG. 5 is a schematic diagram of the effective value of the Z-axis acceleration signal of the axial piston pump including the buffer bottle.

FIG. 6 is a schematic diagram of the effective value of the Z-axis acceleration signal of the axial piston pump without a buffer bottle.

Among them, 1. Ground test bench; 2. Z-axis acceleration sensor; 3. Y-axis acceleration sensor; 4. X-axis acceleration sensor; 5. Axial piston pump flange; 6. Axial piston pump; 7. Charge amplifier; 8. Signal analyzer.

Detailed ways

The specific implementation modes of the present invention are described below so that those skilled in the art can understand the present invention. However, it should be clear that the present invention is not limited to the scope of the specific implementation modes. For those of ordinary skill in the art, as long as various changes are within the spirit and scope of the present invention as defined and determined by the attached claims, these changes are obvious, and all inventions and creations utilizing the concept of the present invention are protected.

As shown in Figure 1, the present invention provides an aviation high-pressure axial piston pump vibration acquisition system, which is characterized in that it includes a test bench, multiple acceleration sensors, a charge amplifier 7 and a signal analyzer 8; an axial piston pump flange 5 for mounting an axial piston pump 6 is fixed on the test bench; the multiple acceleration sensors include an X-axis acceleration sensor 4, a Y-axis acceleration sensor 3 and a Z-axis acceleration sensor 2 electrically connected to the charge amplifier 7; the charge amplifier 7 is electrically connected to the signal analyzer 8.

Specifically, as the specific selection of X-axis acceleration sensor 4, Y-axis acceleration sensor 3 and Z-axis acceleration sensor 2, X-axis acceleration sensor 4, Y-axis acceleration sensor 3 and Z-axis acceleration sensor 2 are charge-type piezoelectric acceleration sensors with a measuring range of 1000g, a response frequency of 25KHz and an accuracy of ±0.5%.

The sampling frequency of the signal analyzer 8 is 2 to 5 times the response frequency of the acceleration sensor.

As a specific installation method of the X-axis acceleration sensor 4, the Y-axis acceleration sensor 3 and the Z-axis acceleration sensor 2, the installation direction of the X-axis acceleration sensor 4 and the Y-axis acceleration sensor 3 is perpendicular to the rotation axis of the axial piston pump 6; the installation direction of the Z-axis acceleration sensor 2 is parallel to the rotation axis of the axial piston pump 6.

The present invention also provides a method for using an aviation high-pressure axial piston pump vibration collection system, which comprises:

Step S1, installing the axial piston pump 6 on the axial piston pump flange 5.

Step S2, start the axial piston pump 6, and collect acceleration signals of the three axes of X, Y, and Z of the axial piston pump 6 in full frequency bands under different working conditions; specifically, at least three cycles are collected for each working condition.

Step S3, obtaining effective values and maximum values of acceleration signals in multiple frequency bands. Specifically, obtaining effective values of acceleration signals in frequency bands of 0-1000 Hz, 1000 Hz-3000 Hz, 3000 Hz-6000 Hz and 6000 Hz-10000 Hz by bandpass filtering.

The calculation formula of the effective value of the acceleration signal is:

Where x(t) is the instantaneous acceleration amplitude at a certain moment, T is a cycle time, X _RMS is the effective value of acceleration in the T cycle, and t is a certain moment;

The maximum value of the acceleration signal is calculated as:

Among them, max is the symbol for finding the maximum value.

Step S4, comparing the effective values and maximum values of acceleration signals of multiple different frequency segments, obtaining the components of the axial piston pump 6 that affect the acceleration amplitude, and proposing an optimization rule.

A vibration collection system and a method for using an aviation high-pressure axial piston pump are used to collect vibrations of an aviation high-pressure axial piston pump. The high-pressure axial piston pump has two types: a buffer bottle and a buffer-free bottle. The outlet pressure of the high-pressure axial piston pump is 28 MPa. The test conditions of the high-pressure axial piston pump are shown in Table 1.

First, according to step S2, the Z-axis acceleration sensor 2 and the X-axis acceleration sensor 4 are used to collect the Z-axis acceleration value and the X-axis acceleration value of the two high-pressure axial piston pumps with a buffer bottle and without a buffer bottle respectively; the result of the Z-axis acceleration value collected by the Z-axis acceleration sensor 2 is shown in Figure 2; then according to step S3, the effective value of the Z-axis acceleration signal and the effective value of the X-axis acceleration signal in multiple different frequency bands are obtained, and the results are shown in Figures 3 and 4; the effective value of the Z-axis acceleration signal of the two high-pressure axial piston pumps with a buffer bottle and without a buffer bottle in multiple different frequency bands is compared, and the results are shown in Figures 5 and 6. From Figures 5 and 6, it can be seen that the acceleration amplitude is very small when there is no buffer bottle in the high-frequency range of 6000Hz~10000Hz, and the effective value of the acceleration in the high-frequency range of 0~10000Hz and 6000Hz~10000Hz is the same, and the peak-to-valley characteristics are the same, that is, the buffer bottle is the reason why the effective value of the acceleration of the aviation high-pressure axial piston pump is relatively large; for other components in the high-pressure axial piston pump, the above method can be used for analysis, that is, by extracting characteristic signals at different frequencies to judge the influence of different components in the aviation high-pressure axial piston pump on vibration, and finally obtaining the mechanism of axial piston pump failure formation, providing a theoretical basis for optimizing the components in the axial piston pump.

In summary, the present invention provides an aviation high-pressure axial piston pump vibration collection system and use method. By establishing a ground test bench 1, arranging acceleration sensors in different directions, and collecting and decomposing vibration signals in different frequency bands, the contribution of each component of the aviation high-pressure axial piston pump to the vibration can be determined. The instantaneous value, effective value and full-cycle vibration characteristics of acceleration in different frequency bands can be accurately captured, so as to extract and analyze the features in the signal, and finally the mechanism of fault formation is obtained. The system can be applied to the noisy working environment sound in the aircraft system, and the problem that the hydraulic piston pump fault diagnosis device in the prior art cannot be applied to the aircraft system is solved.

Claims (3)

1. A method for using an aviation high-pressure axial piston pump vibration collection system, characterized in that the aviation high-pressure axial piston pump vibration collection system comprises a test bench, a plurality of acceleration sensors, a charge amplifier and a signal analyzer; an axial piston pump flange for installing the axial piston pump is fixed on the test bench; the plurality of acceleration sensors comprise an X-axis acceleration sensor, a Y-axis acceleration sensor and a Z-axis acceleration sensor electrically connected to the charge amplifier; the charge amplifier is electrically connected to the signal analyzer; the installation direction of the X-axis acceleration sensor and the Y-axis acceleration sensor is perpendicular to the rotation axis of the axial piston pump; the installation direction of the Z-axis acceleration sensor is parallel to the rotation axis of the axial piston pump; The use of the aviation high-pressure axial piston pump vibration collection system includes: Step S1, installing the axial piston pump on the axial piston pump flange; Step S2, starting the axial piston pump, collecting acceleration signals of the three axes of X, Y, and Z in full frequency bands under different working conditions of the axial piston pump; at least three cycles are collected for each working condition; Step S3, obtaining the effective value and maximum value of multiple acceleration signals in different frequency bands; obtaining the effective value of the acceleration signal in the frequency bands of 0-1000 Hz, 1000 Hz-3000 Hz, 3000 Hz-6000 Hz and 6000 Hz-10000 Hz by band-pass filtering, and the calculation formula of the effective value of the acceleration signal is: Where x(t) is the instantaneous acceleration amplitude at a certain moment, T is a cycle time, X _RMS is the effective value of acceleration in the T cycle, and t is a certain moment; The maximum value of the acceleration signal is calculated as: Among them, max is the symbol for finding the maximum value; Step S4, comparing the effective values and maximum values of acceleration signals in multiple frequency segments, obtaining the components of the axial piston pump that affect the acceleration amplitude, and proposing an optimization rule. 2. The method for using the aviation high-pressure axial piston pump vibration acquisition system according to claim 1 is characterized in that the X-axis acceleration sensor, the Y-axis acceleration sensor and the Z-axis acceleration sensor are charge-type piezoelectric acceleration sensors with a range of 1000g, a response frequency of 25KHz, and an accuracy of ±0.5%. 3. The method for using the aviation high-pressure axial piston pump vibration acquisition system according to claim 2, characterized in that the sampling frequency of the signal analyzer is 2 to 5 times the response frequency of the acceleration sensor.