飞机液压系统泵—管路振动特性研究
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摘要
液压系统在飞机中广泛应用,其主要作用包括驱动舵面操纵与起落架收放等。飞机液压系统采用变量柱塞泵,脉动式流量输出产生的压力脉动常使系统管路遭受严重破坏,影响正常飞行。因此研究飞机液压系统泵-管路振动特性,降低系统流量、压力脉动和噪声,对提高国产大飞机液压系统性能具有重要意义。
现有的对输流管路的理论分析末考虑管道弯曲造成的同一截面内应力不同,影响飞机液压系统中大量弯曲管路振动分析精度,论文建立了考虑管道弯曲和摩擦耦合的管路流固耦合模型,与传统模型相比,该模型在管壁和流体动力学方程中添加弯曲应力项和摩擦力项。针对一段特定的液压系统管段,在时域分析中,传统模型仅能得到截面内平均应力,误差高达73%,该模型得到的弯曲管道截面内应力分布与试验数据误差在10%以内,可以为飞机液压系统管路设计提供参考；在频域分析中,传统模型不能得到管道弯曲对应的共振频率,而该模型分析结果显示管道弯曲对管道应力的频域响应具有决定性的影响,会改变其响应峰值频率,随着弯曲半径的增加,由管道弯曲造成的共振频率逐渐降低。飞机液压系统的泵与管路振动之间存在强烈的振动传递,原有基于泵模型的分析中仅将管路作为简单的液阻与容腔处理,分析误差较大,本论文首次将复杂弯曲管路振动模型与恒压变量柱塞泵模型结合,建立了泵-管路振动系统综合分析模型。应用这一模型对某航空柱塞泵脉动特性进行分析计算,得到不同转速泵出口压力与试验数据误差在0.7%～1.1%之间,精度较未考虑管路影响时最高5.4%的误差有较大提高,可以很好的预测泵在不同工况下的输出特性。为减小航空柱塞泵流量脉动,常在泵出口附近安装缓冲瓶,占用很大空间,本文首次借鉴电学RC滤波器原理设计了压力脉动衰减器,利用泵本身液阻模拟电阻,体积随泵出口压力变化的活塞腔模拟电容,巧妙设计活塞和弹簧参数,满足减振所需的油液容积和频响要求。该衰减器内置安装时质量仅为46g,较常用的重250g的缓冲瓶减小82%。占用空间为31.4cm3,较体积为200cm3的缓冲瓶减小85%。试验测得流量为100L/min时,泵出口的压力脉动由3.9MPa减少到0.8MPa,减小幅度达80%。这种压力脉动衰减器适应飞机液压系统重量轻、体积小的需要,具有重要的应用价值。
本论文主要研究内容如下：
第一章,绪论。概述了飞机液压系统的组成及应用,阐述了飞机液压系统泵-管路振动控制技术国内外研究进展,分析了课题的研究背景及研究意义,并介绍了主要研究内容。
第二章,航空柱塞泵动态特性分析。在分析航空柱塞泵工况、结构与工作原理的基础上,针对机械振动和流量脉动问题,建立其运动与动力学模型。讨论了斜盘、柱塞、缸体、壳体等柱塞泵重要部件的运动状况与受力状态。采用ANSYS进行了航空柱塞泵的模态仿真,得到了各运动组件动力学特性。
第三章,航空柱塞泵流量脉动优化。分析了航空柱塞泵柱塞的排油过程,对主要的两种流量脉动来源：几何脉动与流量倒灌进行了重点讨论。采用FLUENT进行了流场仿真。优化了某航空柱塞泵配流盘预压缩结构参数。
第四章,航空液压管路振动特性分析。在传统一维管道模型的基础上,考虑管道的弯曲和截面上的应力分布等因素,分别在时域和频域对某型飞机液压能源系统管路进行优化,开展仿真与试验研究。经分析与试验验证,飞机液压能源系统振动特性受管路摩擦耦合与联接耦合等复杂因素影响,优化管路布局可有效减小脉动峰值。
第五章,航空柱塞泵-管路综合特性分析。在泵动力学和流场分析的基础上,探讨泵内滑靴副和配流副工作状态。讨论航空柱塞泵压力控制机构的特性,分析了管道和柱塞泵耦合振动特性。以某航空柱塞泵及其出口管路为对象,通过理论分析与试验研究相结合的方法分析压力脉动特性。
第六章,液压能源系统振动控制研究。在航空液压能源系统振动分析的基础上,探讨各种减振设计方法。重点讨论了柱塞泵结构减振设计、脉动衰减器设计与分析及管路优化配置等。
第七章,结论与展望。对本文的研究工作进行了概述,给出了研究结果和主要结论,指出了本文的创新点,并展望了进一步的研究方向和内容。
The hydraulic systems are wildly used in aircrafts as the power source for flight control and landing gear systems. Pressure compensated pumps are mainly used in aircraft hydraulic systems. The pump flow fluctuation is responsible for decreasing the reliability and lifecycle of the aircraft hydraulic systems. Therefore, it is important to study possibilities to reduce the influence of pressure pulsation on vibration and noise of the aircraft hydraulic systems.
In this thesis, the pipeline model with consideration of the bending and friction coupling has been developed by employing the curved stress and friction in the kinetic equations in the traditional model based on the analysis of the one-dimensional long pipeline. In time domain analysis, the differences of the pipewall stress between the calculated and experiment results were within10%compared with73%in the traditional model for the pipe section. In frequency domain analysis, the effect of the pipe curvature on the resonant frequency was ignored in the traditional approach. It was shown from the calculated results using the model developed that the curvature was a determining factor of the pipe frequency response, and it could obviously change both the frequency and peak value. In fact, with the increase of the pipe curvature radius, the corresponding resonant frequency decreased. The interactions of flow rate, pressure and mechanical vibration between the pump and the connected pipeline were very complex, which had not been discussed in previous study. The vibration of the piston pump and connected pipeline in aircraft hydraulic system was also included in the model. The difference of the pipe wall stress between the calculated and experimental results were within0.7%～1.1%, as a comparison to5.4%of the model without connected pipeline. A new pulsation attenuator for aircraft piston pump based upon the RC (fluid resistance and fluid volume) principles was developed and tested. The piston and spring in the attenuator were designed to reduce the noise level with optimal volume and natural frequency. Hence, the mass of the pulsation attenuator was cut down to46g,82%less compared with the mass of the existing buffer bottle. The needed volume of the pulsation attenuator was reduced to31.4cm3, which was85%less than the volume of the buffer bottle. Remarkable reduction on the pressure fluctuation was obtained in the experiments. At the output flow rate of100L/min, the pressure fluctuation without the attenuator was3.9MPa and0.8MPa with the attenuator, reduction was more than79.5%.
The main contents of the thesis are as follows:
In chapter1, the application of the aircraft hydraulic power system was outlined. The development of the aircraft hydraulic power system vibration control both at home and abroad was summarized. The research background and the main contents of the degree project were introduced.
In chapter2, the kinetic model of the aviation piston pump for vibration analysis was developed based on its working condition, principle and structure. The dynamic characteristic of swash plate, pistons, cylinder and the housing was analyzed in detail. The pump model was developed using the software AN SYS. The dynamic performance of the main components of piston pump was discussed.
In chapter3, the flow model of the aviation piston pump was proposed, and two main parts of flow fluctuation in piston pump with the kinematic flow fluctuation and the compressible flow fluctuation were analyzed. Flow simulation of the aviation piston pump was carried using the software FLUENT. Pre-compression structure parameter of the aviation piston pump was optimized.
In chapter4, the pipeline model composed of curved pipe section and tees was developed. The flow and pressure fluctuations were analyzed both in time and frequency domain. The vibration characteristics of two pipe sections in aircraft were discussed. It was shown in the simulation results that the vibration of the hydraulic power system was affected by the pipe friction coupling and the junction coupling, and the ripple peaks could be reduced by pipeline layout optimization.
In chapter5, the oil film model between the slipper shoes, the swash plate and the oil film between the cylinder and the valve plate was developed. The pressure and velocity distributions were obtained. The relationship between the pump vibration and the oil film thickness was analyzed. The interaction between the pump and the pipeline was discussed. Theoretical analysis and experimental test were carried on the vibration characteristics of an aviation piston pump with the connected pipeline. Some suggestions were given on development of the aircraft hydraulic power system with low vibration.
In chapter6, the optimizations of pump structure and pipeline arrangement were discussed. A new pulsation attenuator for aircraft piston pump based upon the RC (fluid resistance and fluid volume) principles was developed and tested. Remarkable reduction on the pressure fluctuation was obtained in the experiments.
In chapter7, the main results and conclusions were summarized, the progress was concluded, and proposals were given for the future work.
现有的对输流管路的理论分析末考虑管道弯曲造成的同一截面内应力不同,影响飞机液压系统中大量弯曲管路振动分析精度,论文建立了考虑管道弯曲和摩擦耦合的管路流固耦合模型,与传统模型相比,该模型在管壁和流体动力学方程中添加弯曲应力项和摩擦力项。针对一段特定的液压系统管段,在时域分析中,传统模型仅能得到截面内平均应力,误差高达73%,该模型得到的弯曲管道截面内应力分布与试验数据误差在10%以内,可以为飞机液压系统管路设计提供参考；在频域分析中,传统模型不能得到管道弯曲对应的共振频率,而该模型分析结果显示管道弯曲对管道应力的频域响应具有决定性的影响,会改变其响应峰值频率,随着弯曲半径的增加,由管道弯曲造成的共振频率逐渐降低。飞机液压系统的泵与管路振动之间存在强烈的振动传递,原有基于泵模型的分析中仅将管路作为简单的液阻与容腔处理,分析误差较大,本论文首次将复杂弯曲管路振动模型与恒压变量柱塞泵模型结合,建立了泵-管路振动系统综合分析模型。应用这一模型对某航空柱塞泵脉动特性进行分析计算,得到不同转速泵出口压力与试验数据误差在0.7%～1.1%之间,精度较未考虑管路影响时最高5.4%的误差有较大提高,可以很好的预测泵在不同工况下的输出特性。为减小航空柱塞泵流量脉动,常在泵出口附近安装缓冲瓶,占用很大空间,本文首次借鉴电学RC滤波器原理设计了压力脉动衰减器,利用泵本身液阻模拟电阻,体积随泵出口压力变化的活塞腔模拟电容,巧妙设计活塞和弹簧参数,满足减振所需的油液容积和频响要求。该衰减器内置安装时质量仅为46g,较常用的重250g的缓冲瓶减小82%。占用空间为31.4cm3,较体积为200cm3的缓冲瓶减小85%。试验测得流量为100L/min时,泵出口的压力脉动由3.9MPa减少到0.8MPa,减小幅度达80%。这种压力脉动衰减器适应飞机液压系统重量轻、体积小的需要,具有重要的应用价值。
本论文主要研究内容如下：
第一章,绪论。概述了飞机液压系统的组成及应用,阐述了飞机液压系统泵-管路振动控制技术国内外研究进展,分析了课题的研究背景及研究意义,并介绍了主要研究内容。
第二章,航空柱塞泵动态特性分析。在分析航空柱塞泵工况、结构与工作原理的基础上,针对机械振动和流量脉动问题,建立其运动与动力学模型。讨论了斜盘、柱塞、缸体、壳体等柱塞泵重要部件的运动状况与受力状态。采用ANSYS进行了航空柱塞泵的模态仿真,得到了各运动组件动力学特性。
第三章,航空柱塞泵流量脉动优化。分析了航空柱塞泵柱塞的排油过程,对主要的两种流量脉动来源：几何脉动与流量倒灌进行了重点讨论。采用FLUENT进行了流场仿真。优化了某航空柱塞泵配流盘预压缩结构参数。
第四章,航空液压管路振动特性分析。在传统一维管道模型的基础上,考虑管道的弯曲和截面上的应力分布等因素,分别在时域和频域对某型飞机液压能源系统管路进行优化,开展仿真与试验研究。经分析与试验验证,飞机液压能源系统振动特性受管路摩擦耦合与联接耦合等复杂因素影响,优化管路布局可有效减小脉动峰值。
第五章,航空柱塞泵-管路综合特性分析。在泵动力学和流场分析的基础上,探讨泵内滑靴副和配流副工作状态。讨论航空柱塞泵压力控制机构的特性,分析了管道和柱塞泵耦合振动特性。以某航空柱塞泵及其出口管路为对象,通过理论分析与试验研究相结合的方法分析压力脉动特性。
第六章,液压能源系统振动控制研究。在航空液压能源系统振动分析的基础上,探讨各种减振设计方法。重点讨论了柱塞泵结构减振设计、脉动衰减器设计与分析及管路优化配置等。
第七章,结论与展望。对本文的研究工作进行了概述,给出了研究结果和主要结论,指出了本文的创新点,并展望了进一步的研究方向和内容。
The hydraulic systems are wildly used in aircrafts as the power source for flight control and landing gear systems. Pressure compensated pumps are mainly used in aircraft hydraulic systems. The pump flow fluctuation is responsible for decreasing the reliability and lifecycle of the aircraft hydraulic systems. Therefore, it is important to study possibilities to reduce the influence of pressure pulsation on vibration and noise of the aircraft hydraulic systems.
In this thesis, the pipeline model with consideration of the bending and friction coupling has been developed by employing the curved stress and friction in the kinetic equations in the traditional model based on the analysis of the one-dimensional long pipeline. In time domain analysis, the differences of the pipewall stress between the calculated and experiment results were within10%compared with73%in the traditional model for the pipe section. In frequency domain analysis, the effect of the pipe curvature on the resonant frequency was ignored in the traditional approach. It was shown from the calculated results using the model developed that the curvature was a determining factor of the pipe frequency response, and it could obviously change both the frequency and peak value. In fact, with the increase of the pipe curvature radius, the corresponding resonant frequency decreased. The interactions of flow rate, pressure and mechanical vibration between the pump and the connected pipeline were very complex, which had not been discussed in previous study. The vibration of the piston pump and connected pipeline in aircraft hydraulic system was also included in the model. The difference of the pipe wall stress between the calculated and experimental results were within0.7%～1.1%, as a comparison to5.4%of the model without connected pipeline. A new pulsation attenuator for aircraft piston pump based upon the RC (fluid resistance and fluid volume) principles was developed and tested. The piston and spring in the attenuator were designed to reduce the noise level with optimal volume and natural frequency. Hence, the mass of the pulsation attenuator was cut down to46g,82%less compared with the mass of the existing buffer bottle. The needed volume of the pulsation attenuator was reduced to31.4cm3, which was85%less than the volume of the buffer bottle. Remarkable reduction on the pressure fluctuation was obtained in the experiments. At the output flow rate of100L/min, the pressure fluctuation without the attenuator was3.9MPa and0.8MPa with the attenuator, reduction was more than79.5%.
The main contents of the thesis are as follows:
In chapter1, the application of the aircraft hydraulic power system was outlined. The development of the aircraft hydraulic power system vibration control both at home and abroad was summarized. The research background and the main contents of the degree project were introduced.
In chapter2, the kinetic model of the aviation piston pump for vibration analysis was developed based on its working condition, principle and structure. The dynamic characteristic of swash plate, pistons, cylinder and the housing was analyzed in detail. The pump model was developed using the software AN SYS. The dynamic performance of the main components of piston pump was discussed.
In chapter3, the flow model of the aviation piston pump was proposed, and two main parts of flow fluctuation in piston pump with the kinematic flow fluctuation and the compressible flow fluctuation were analyzed. Flow simulation of the aviation piston pump was carried using the software FLUENT. Pre-compression structure parameter of the aviation piston pump was optimized.
In chapter4, the pipeline model composed of curved pipe section and tees was developed. The flow and pressure fluctuations were analyzed both in time and frequency domain. The vibration characteristics of two pipe sections in aircraft were discussed. It was shown in the simulation results that the vibration of the hydraulic power system was affected by the pipe friction coupling and the junction coupling, and the ripple peaks could be reduced by pipeline layout optimization.
In chapter5, the oil film model between the slipper shoes, the swash plate and the oil film between the cylinder and the valve plate was developed. The pressure and velocity distributions were obtained. The relationship between the pump vibration and the oil film thickness was analyzed. The interaction between the pump and the pipeline was discussed. Theoretical analysis and experimental test were carried on the vibration characteristics of an aviation piston pump with the connected pipeline. Some suggestions were given on development of the aircraft hydraulic power system with low vibration.
In chapter6, the optimizations of pump structure and pipeline arrangement were discussed. A new pulsation attenuator for aircraft piston pump based upon the RC (fluid resistance and fluid volume) principles was developed and tested. Remarkable reduction on the pressure fluctuation was obtained in the experiments.
In chapter7, the main results and conclusions were summarized, the progress was concluded, and proposals were given for the future work.
引文
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