平面空气静压轴承承载特性研究
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摘要
随着航天技术、微电子技术和精密加工等学科的发展,对于产品精度的要求越来越高。空气静压轴承以其高精度、低摩擦、无污染的特点广泛应用于航空航天、食品医药以及高精密机床和测量仪器等领域中。特别在航天器地面仿真实验系统中,为了完全模拟太空中无摩擦的失重环境,平面空气静压止推轴承作为主要的支承部件承担着整个气浮台及其相关设备的重量。因而,提高空气静压轴承的承载能力,优化轴承节流器的节流作用,就成了气体静压润滑理论研究和空气轴承设计的重要内容。
传统的空气静压止推轴承多采用节流孔供气的方法,这也是研究起步最早、目前理论分析和实验研究较多的一种节流器形式。在已有的研究成果中,国内外学者在设计和选择时多采用经验公式和工程方法,对节流孔的节流类型分为小孔节流方式和环面节流方式两种。随着进口效应和激波假设的提出,在传统的空气静压轴承设计理论中广泛采用的“两块式流动假设”(即:第一部分为供气孔中等熵流动,第二部分为间隙气膜内完全发展的等温层流)已明显不能满足当代研究和应用中对空气静压轴承在精确度和准确性方面的要求。如何准确描述轴承在工作时随着节流孔处结构参数不同轴承节流器表现出来的不同节流类型,在现有条件下从改进节流效果入手,而非单纯依靠提高供气压力或者追求小气膜厚度来提高小孔节流空气静压轴承的承载能力,这不仅从本质上完善和充实了空气轴承设计理论,充分利用了轴承自身所具备的承载力提升空间,也减小了对外界能源的消耗和在追求加工精度方面需要的额外投入。
在广泛调研国内外关于小孔节流空气静压止推轴承研究成果的基础上,本文从流体润滑理论出发,根据供气孔处结构参数之间的相互关系和制约条件,全面考虑各流域可能出现的流动状态和可能造成的节流作用,遵循可压缩雷诺方程的推导结果对空气静压止推轴承的工作气膜进行数学建模,将可压缩雷诺气体润滑方程与边界条件联立求解得到轴承气膜中的压力分布,进而求解轴承的承载力并得出相应的结论。在理论分析的基础上,本文以多孔供气小孔节流空气静压止推轴承为例,研究不同节流类型下具体参数对轴承承载能力的影响规律。分别研究轴承在静态承载、发生倾侧以及受到外界干扰作用时,各典型节流类型轴承在承载性能上表现出来的特点,这样以来就可以根据不同的使用需要选择适当的节流类型,并得到各节流类型下相应的优化参数。本文最后通过搭建实验台,将静态实验、倾侧实验和动态实验三部分的实测值与理论分析和数值计算的结果相比较,证明本文中模型建立和研究结果真实可靠。本文的研究结论使静压润滑理论在空气轴承设计方面得到了丰富和完善,并为实际生产过程中空气静压止推轴承的选择和应用提供了一套完整的选型方法。
Development of space technology, microelectronic technology and precision machining technology demand high accuracy. Attribute to its advantages of high accuracy, anti-friction, clean and health, aerostatic bearing is widely used in spaceflight, pharmaceuticals industry, food service industry, high precision machine tool and measuring instrument areas. In ground-based spaceflight and docking simulation system, it is necessary to simulate a zero-genvironment officeenvironment completely. As an important support unit, aerostatic thrust bearing plays a significant part in air bearing testbed,which is designed for spaceflight and docking simulation system. And the demand for improvement of load-carrying capacity and optimization of throttlling effect of restrictor become one of the most important contents in theoretical research of aerostatic lubrication and design of air bearing.
Traditional aerostatic thrust bearing mostly use orifice inlet method which is the earilest and the most pervasive throttle in theoretical and experimental study. In past researches, domestic and foreign scholars always use experimental formula and engineering calculating method in design and election. And they devide orifice inlet into orifice compensation and inherent compensation according to its throttling effect. Putting forward along with entrance effect and shock wave assumption, simplified model composed by isentropic flow in orifice and isothermal flow in gas film is too rough to meet the need for precise answers to performance characteristics of aerostatic thrust bearings in the serious reaches of contemporary science. At present, making an accurate description of orifice restrictor and improving throttle operating principle instead of requirements of high supply gas pressure and thinner gas film under current conditions is of far reaching importance for further enriching and improving design theories for aerostatic thrust bearing, develop fully orifice compensation's potential and capability, use less energy, and have lower costs on high-precision processing technology.
Given above consideration and current research situation analysis of orifice compensated aerostatic thrust bearing of domestic and foreign scholars, fulfilled mathematical model of the whole flow process from inlet to outlet is established according to gas lubrication theory, relations and limitaion among all structural paprameters around the orifice inlet. For all possibilities of flow condition and throttling tpyes in the whole region, coupling compressible nonsteady Reynolds equation with boundary conditions, pressure distribution of the air film can be obtained. Therefore the load-carrying properties of air bearing can be obtained, as well as the corresponding conclusions. On base of theoretical analysis, we take multi-inlet orifice compensated aerostatic thrust bearing as an example to disclose influence of detailed parameters on load-carrying capacity of air bearing with different throttling modes in possible working conditions. characteristics and differences of air bearings with different throttling modes are Summarized when they are in normal condition, tilt condition and even interfered environment. In this way, you can choose air bearing with proper throttling mode and optimized parameters of as needed. the test investigation on the static characteristics, anti-tilt characteristics and dynamic characteristics is performed.The results show that the models and research results in this dissertation are available and reliable. The results of this paper further enrich the applications of air lubrication theory to aerostatic bearing design. And it also provides a series of comprehensive methods for selection and use of aerostatic thrust bearing in practical production.
传统的空气静压止推轴承多采用节流孔供气的方法,这也是研究起步最早、目前理论分析和实验研究较多的一种节流器形式。在已有的研究成果中,国内外学者在设计和选择时多采用经验公式和工程方法,对节流孔的节流类型分为小孔节流方式和环面节流方式两种。随着进口效应和激波假设的提出,在传统的空气静压轴承设计理论中广泛采用的“两块式流动假设”(即:第一部分为供气孔中等熵流动,第二部分为间隙气膜内完全发展的等温层流)已明显不能满足当代研究和应用中对空气静压轴承在精确度和准确性方面的要求。如何准确描述轴承在工作时随着节流孔处结构参数不同轴承节流器表现出来的不同节流类型,在现有条件下从改进节流效果入手,而非单纯依靠提高供气压力或者追求小气膜厚度来提高小孔节流空气静压轴承的承载能力,这不仅从本质上完善和充实了空气轴承设计理论,充分利用了轴承自身所具备的承载力提升空间,也减小了对外界能源的消耗和在追求加工精度方面需要的额外投入。
在广泛调研国内外关于小孔节流空气静压止推轴承研究成果的基础上,本文从流体润滑理论出发,根据供气孔处结构参数之间的相互关系和制约条件,全面考虑各流域可能出现的流动状态和可能造成的节流作用,遵循可压缩雷诺方程的推导结果对空气静压止推轴承的工作气膜进行数学建模,将可压缩雷诺气体润滑方程与边界条件联立求解得到轴承气膜中的压力分布,进而求解轴承的承载力并得出相应的结论。在理论分析的基础上,本文以多孔供气小孔节流空气静压止推轴承为例,研究不同节流类型下具体参数对轴承承载能力的影响规律。分别研究轴承在静态承载、发生倾侧以及受到外界干扰作用时,各典型节流类型轴承在承载性能上表现出来的特点,这样以来就可以根据不同的使用需要选择适当的节流类型,并得到各节流类型下相应的优化参数。本文最后通过搭建实验台,将静态实验、倾侧实验和动态实验三部分的实测值与理论分析和数值计算的结果相比较,证明本文中模型建立和研究结果真实可靠。本文的研究结论使静压润滑理论在空气轴承设计方面得到了丰富和完善,并为实际生产过程中空气静压止推轴承的选择和应用提供了一套完整的选型方法。
Development of space technology, microelectronic technology and precision machining technology demand high accuracy. Attribute to its advantages of high accuracy, anti-friction, clean and health, aerostatic bearing is widely used in spaceflight, pharmaceuticals industry, food service industry, high precision machine tool and measuring instrument areas. In ground-based spaceflight and docking simulation system, it is necessary to simulate a zero-genvironment officeenvironment completely. As an important support unit, aerostatic thrust bearing plays a significant part in air bearing testbed,which is designed for spaceflight and docking simulation system. And the demand for improvement of load-carrying capacity and optimization of throttlling effect of restrictor become one of the most important contents in theoretical research of aerostatic lubrication and design of air bearing.
Traditional aerostatic thrust bearing mostly use orifice inlet method which is the earilest and the most pervasive throttle in theoretical and experimental study. In past researches, domestic and foreign scholars always use experimental formula and engineering calculating method in design and election. And they devide orifice inlet into orifice compensation and inherent compensation according to its throttling effect. Putting forward along with entrance effect and shock wave assumption, simplified model composed by isentropic flow in orifice and isothermal flow in gas film is too rough to meet the need for precise answers to performance characteristics of aerostatic thrust bearings in the serious reaches of contemporary science. At present, making an accurate description of orifice restrictor and improving throttle operating principle instead of requirements of high supply gas pressure and thinner gas film under current conditions is of far reaching importance for further enriching and improving design theories for aerostatic thrust bearing, develop fully orifice compensation's potential and capability, use less energy, and have lower costs on high-precision processing technology.
Given above consideration and current research situation analysis of orifice compensated aerostatic thrust bearing of domestic and foreign scholars, fulfilled mathematical model of the whole flow process from inlet to outlet is established according to gas lubrication theory, relations and limitaion among all structural paprameters around the orifice inlet. For all possibilities of flow condition and throttling tpyes in the whole region, coupling compressible nonsteady Reynolds equation with boundary conditions, pressure distribution of the air film can be obtained. Therefore the load-carrying properties of air bearing can be obtained, as well as the corresponding conclusions. On base of theoretical analysis, we take multi-inlet orifice compensated aerostatic thrust bearing as an example to disclose influence of detailed parameters on load-carrying capacity of air bearing with different throttling modes in possible working conditions. characteristics and differences of air bearings with different throttling modes are Summarized when they are in normal condition, tilt condition and even interfered environment. In this way, you can choose air bearing with proper throttling mode and optimized parameters of as needed. the test investigation on the static characteristics, anti-tilt characteristics and dynamic characteristics is performed.The results show that the models and research results in this dissertation are available and reliable. The results of this paper further enrich the applications of air lubrication theory to aerostatic bearing design. And it also provides a series of comprehensive methods for selection and use of aerostatic thrust bearing in practical production.
引文
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