CN118088429B - A vibration collection system and use method for aviation high-pressure axial piston pump - Google Patents
A vibration collection system and use method for aviation high-pressure axial piston pump Download PDFInfo
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Abstract
Description
技术领域Technical Field
本发明属于飞机液压系统技术领域,尤其涉及一种航空高压轴向柱塞泵振动采集系统及使用方法。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.
背景技术Background technique
液压系统是飞机三大核心系统之一,广泛应用于飞机的前轮转弯、起落架收放、副翼、缝翼、扰流板操作、主刹车、减速板收放、升降舵和方向舵等机构中,直接关乎飞行安全。航空高压轴向柱塞泵是飞机液压系统的核心部件,同时也是液压系统中故障高发部件之一。随着航空高压轴向柱塞泵高压化、高速化的快速发展,液压系统的结构愈加复杂,故障形式也越来越多。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.
在现有技术中有专门针对于液压柱塞泵故障的诊断装置,如专利公开号为CN114109800A,名称为一种基于声音识别技术的液压柱塞泵故障诊断装置和方法,该装置包括麦克风、屏蔽线、声卡、DSP声音处理器、交流接触器开关等,液压柱塞泵故障诊断装置和方法通过采集液压柱塞泵的工作环境声音,进而分析出对液压柱塞泵的故障,具有结构简单、响应速度快及准确度高等优点。但是该液压柱塞泵故障诊断装置和方法不适用于飞机系统,因为在飞机系统中,发动机噪声远大于柱塞泵声音,该液压柱塞泵故障诊断装置和方法不能准确地采集液压柱塞泵的工作环境声音,导致无法准确分析出液压柱塞泵故障,无法为优化轴向柱塞泵中的各部件提供理论基础。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.
发明内容Summary of the invention
针对现有技术的上述不足,本发明提供了一种航空高压轴向柱塞泵振动采集系统及分析方法,解决了现有技术中的液压柱塞泵故障诊断装置因无法适用于飞机系统而导致无法为优化轴向柱塞泵中的各部件提供理论基础的问题。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.
为了达到上述发明目的,本发明采用的技术方案为:In order to achieve the above-mentioned object of the invention, the technical solution adopted by the present invention is:
提供了一种航空高压轴向柱塞泵振动采集系统,其包括试验台架、多个加速度传感器、电荷放大器和信号分析器;试验台架上固定有用于安装轴向柱塞泵的轴向柱塞泵法兰;多个加速度传感器包括与电荷放大器电性连接的X轴加速度传感器、Y轴加速度传感器和Z轴加速度传感器;电荷放大器与信号分析器电性连接。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.
进一步地,作为X轴加速度传感器、Y轴加速度传感器和Z轴加速度传感器的具体选型,X轴加速度传感器、Y轴加速度传感器和Z轴加速度传感器为电荷型压电式加速度传感器,量程为1000g,响应频率为25KHz,精度为±0.5%。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%.
进一步地,信号分析器的采样频率为加速度传感器响应频率的2~5倍。如果柱塞泵故障时采样率低的话可能无法采准确故障频率,2~5倍的话可以将故障频率准确包含。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.
进一步地,作为X轴加速度传感器、Y轴加速度传感器和Z轴加速度传感器的具体安装方式,X轴加速度传感器和Y轴加速度传感器的安装方向垂直于轴向柱塞泵旋转轴;Z轴加速度传感器的安装方向平行于轴向柱塞泵旋转轴。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.
进一步地,本发明还提供一种航空高压轴向柱塞泵振动采集系统的使用方法,其包括:Furthermore, the present invention also provides a method for using an aviation high-pressure axial piston pump vibration collection system, which comprises:
步骤S1、将轴向柱塞泵安装在轴向柱塞泵法兰上;Step S1, installing the axial piston pump on the axial piston pump flange;
步骤S2、启动轴向柱塞泵,采集轴向柱塞泵不同工况下全频段的X、Y、Z三个轴向的加速度信号;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;
步骤S3、获得多段不同频率段加速度信号的有效值和最大值;Step S3, obtaining effective values and maximum values of acceleration signals of multiple different frequency bands;
步骤S4、对比多段不同频率段加速度信号的有效值和最大值,获得影响加速度幅值的轴向柱塞泵的部件,提出优化规律。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.
进一步地,在步骤S2中,每个工况至少采集三个循环。Furthermore, in step S2, at least three cycles are collected for each working condition.
进一步地,在步骤S3中,通过带通滤波获取0~1000Hz、1000Hz~3000Hz、3000Hz~6000Hz和6000Hz~10000Hz频率段加速度信号的有效值。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是柱塞泵基频范围,主要识别柱塞泵基频的变化;1000Hz~3000Hz是柱塞泵1或2倍频,3000Hz~6000Hz是柱塞泵3~4倍频,主要识别旋转部件失效激发的高次频;若1000Hz~3000Hz无法识别,则3000Hz~6000Hz包含相应的特征高次频率。6000Hz~10000Hz是高频噪声频段。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.
进一步地,在步骤S3中,加速度信号的有效值计算公式为:Furthermore, in step S3, the effective value calculation formula of the acceleration signal is:
其中,x(t)为某时刻的瞬时加速度幅值,T为一个周期时间,XRMS为T周期内加速度的有效值,t为某时刻;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;
加速度信号的最大值计算公式为:The maximum value of the acceleration signal is calculated as follows:
其中,max为求最大值符号。Among them, max is the symbol for finding the maximum value.
本发明的有益效果为:本发明中一种航空高压轴向柱塞泵振动采集系统及使用方法,通过建立地面试验台架、布置不同方向的加速度传感器、采集并分解不同频段下的振动信号,来判断航空高压轴向柱塞泵各部件对振动的贡献程度,可以准确捕捉到不同频段下的加速度瞬时值、有效值及全周期的振动特性,从而对信号中的特征加以提取和分析,最终获得故障形成的机理,可以适用于飞机系统中噪音大的工作环境声音,解决了现有技术中的液压柱塞泵故障诊断装置无法适用于飞机系统的问题。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.
附图说明BRIEF DESCRIPTION OF THE DRAWINGS
图1为一种航空高压轴向柱塞泵振动采集系统的结构示意图。FIG1 is a schematic diagram of the structure of a vibration collection system for an aviation high-pressure axial piston pump.
图2为Z轴加速度传感器采集的Z向加速度值的示意图。FIG. 2 is a schematic diagram of Z-axis acceleration values collected by a Z-axis acceleration sensor.
图3为Z向和X向加速度信号有效值的示意图。FIG. 3 is a schematic diagram of effective values of acceleration signals in the Z direction and the X direction.
图4为在多段不同频率段下Z向加速度信号有效值的示意图。FIG. 4 is a schematic diagram of effective values of Z-axis acceleration signals in multiple frequency bands.
图5为含有缓冲瓶的轴向柱塞泵的Z向加速度信号有效值的示意图。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.
图6为无缓冲瓶的轴向柱塞泵的Z向加速度信号有效值的示意图。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.
其中,1、地面试验台架;2、Z轴加速度传感器;3、Y轴加速度传感器;4、X轴加速度传感器;5、轴向柱塞泵法兰;6、轴向柱塞泵;7、电荷放大器;8、信号分析器。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.
具体实施方式Detailed ways
下面对本发明的具体实施方式进行描述,以便于本技术领域的技术人员理解本发明,但应该清楚,本发明不限于具体实施方式的范围,对本技术领域的普通技术人员来讲,只要各种变化在所附的权利要求限定和确定的本发明的精神和范围内,这些变化是显而易见的,一切利用本发明构思的发明创造均在保护之列。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.
如图1所示,本发明提供了一种航空高压轴向柱塞泵振动采集系统,其特征在于,包括试验台架、多个加速度传感器、电荷放大器7和信号分析器8;试验台架上固定有用于安装轴向柱塞泵6的轴向柱塞泵法兰5;多个加速度传感器包括与电荷放大器7电性连接的X轴加速度传感器4、Y轴加速度传感器3和Z轴加速度传感器2;电荷放大器7与信号分析器8电性连接。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.
具体地,作为X轴加速度传感器4、Y轴加速度传感器3和Z轴加速度传感器2的具体选型,X轴加速度传感器4、Y轴加速度传感器3和Z轴加速度传感器2为电荷型压电式加速度传感器,量程为1000g,响应频率为25KHz,精度为±0.5%。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%.
信号分析器8的采样频率为加速度传感器响应频率的2~5倍。The sampling frequency of the signal analyzer 8 is 2 to 5 times the response frequency of the acceleration sensor.
作为X轴加速度传感器4、Y轴加速度传感器3和Z轴加速度传感器2的具体安装方式,X轴加速度传感器4和Y轴加速度传感器3的安装方向垂直于轴向柱塞泵6旋转轴;Z轴加速度传感器2的安装方向平行于轴向柱塞泵6旋转轴。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.
本发明还提供一种航空高压轴向柱塞泵振动采集系统的使用方法,其包括:The present invention also provides a method for using an aviation high-pressure axial piston pump vibration collection system, which comprises:
步骤S1、将轴向柱塞泵6安装在轴向柱塞泵法兰5上。Step S1, installing the axial piston pump 6 on the axial piston pump flange 5.
步骤S2、启动轴向柱塞泵6,采集轴向柱塞泵6不同工况下全频段的X、Y、Z三个轴向的加速度信号;具体地,每个工况至少采集三个循环。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.
步骤S3、获得多段不同频率段加速度信号的有效值和最大值。具体地,通过带通滤波获取0~1000Hz、1000Hz~3000Hz、3000Hz~6000Hz和6000Hz~10000Hz频率段加速度信号的有效值。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.
加速度信号的有效值计算公式为:The calculation formula of the effective value of the acceleration signal is:
其中,x(t)为某时刻的瞬时加速度幅值,T为一个周期时间,XRMS为T周期内加速度的有效值,t为某时刻;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;
加速度信号的最大值计算公式为:The maximum value of the acceleration signal is calculated as:
其中,max为求最大值符号。Among them, max is the symbol for finding the maximum value.
步骤S4、对比多段不同频率段加速度信号的有效值和最大值,获得影响加速度幅值的轴向柱塞泵6的部件,提出优化规律。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.
一种航空高压轴向柱塞泵振动采集系统及使用方法运用于对某航空高压轴向柱塞泵进行振动采集,该高压轴向柱塞泵具有缓冲瓶和无缓冲瓶两种类型,该高压轴向柱塞泵的出口压力为28MPa,高压轴向柱塞泵的试验工况如表1所示。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.
首先,根据步骤S2,通过Z轴加速度传感器2和X轴加速度传感器4分别采集具有缓冲瓶和无缓冲瓶两种高压轴向柱塞泵的Z向加速度值和X向加速度值;Z轴加速度传感器2采集的Z向加速度值的结果如图2所示;然后根据步骤S3,获取在多段不同频率段下Z向加速度信号有效值和X向加速度信号有效值,其结果如图3和图4所示;对比具有缓冲瓶和无缓冲瓶两种高压轴向柱塞泵的在多段不同频率段下Z向加速度信号的有效值,结果如图5和图6所示。通过图5和图6可知,可以看出在6000Hz~10000Hz高频范围内的无缓冲瓶时加速度幅值非常小,0~10000Hz和6000Hz~10000Hz高频范围内的加速度的有效值大小一样、峰谷特性一样,即缓冲瓶是 造成航空高压轴向柱塞泵加速度的有效值比较大的原因;对于高压轴向柱塞泵中的其他部件,均可以采用上述方式进行分析,即通过提取对不同频率下特征信号来判断航空高压轴向柱塞泵中不同部件对振动的影响,最终获得轴向柱塞泵故障形成的机理,为优化轴向柱塞泵中的各部件提供理论基础。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.
综上所述,本发明中一种航空高压轴向柱塞泵振动采集系统及使用方法,通过建立地面试验台架1、布置不同方向的加速度传感器、采集并分解不同频段下的振动信号,来判断航空高压轴向柱塞泵各部件对振动的贡献程度,可以准确捕捉到不同频段下的加速度瞬时值、有效值及全周期的振动特性,从而对信号中的特征加以提取和分析,最终获得故障形成的机理,可以适用于飞机系统中噪音大的工作环境声音,解决了现有技术中的液压柱塞泵故障诊断装置无法适用于飞机系统的问题。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.
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