氦氖激光陀螺铟封接系统设计优化与封接应力的研究

发布时间：2018-05-23 15:11

本文选题：氦氖激光陀螺仪 + 铟封接　；参考：《合肥工业大学》2017年硕士论文

【摘要】：氦氖激光陀螺仪电极铟封接技术是维持微晶谐振腔真空环境的关键技术之一。本文以氦氖激光陀螺仪电极铟封接结构为研究对象,分析其残余应力和温度对封接疲劳失效的影响,设计了氦氖激光陀螺仪电极铟封接系统。主要内容如下:基于弹塑性力学理论,分析了封接界面残余应力与挠度的关系,依据高等传热学理论,研究了封接过程中热量传递方式,得出了温度变化规律;构建激光陀螺仪电极-腔体铟封接结构的数学和物理模型,并依据封接过程确定求解边界条件,对铟封接结构残余应力进行理论计算和数值分析,获得了铟封接结构轴向、周向以及切向残余应力的变化规律;分析了铟丝环直径、铟合金化学计量比对铟封接残余应力的影响,优化了封接工艺参数,提高了谐振腔真空铟封接性能及封接强度,为激光陀螺仪电极热压铟封接系统后续设计提供了工艺参数与理论基础。依据黏塑性流体方程与损伤演化理论,选用Anand黏塑性模型进行疲劳分析;根据几何对称性与载荷对称性简化铟封接结构,构建了二维有限元模型并给出边界条件及黏塑性参数;基于构建的有限元模型,分析循环温度工况下铟封接结构的疲劳失效问题,获得其失效趋势,依据塑性应变累积效应确定了危险节点,并对应力滞回环与温度棘轮出现的根本原因进行了分析。基于前述铟封接模型的工艺参数、尺寸特征及封接技术难点,以提高加工效率为目的,确定了铟封接系统总体架构,研究了以下几方面内容:从封装夹具出发,确定了最优定位点分布,实现了封接状态中腔体的力闭合装夹,并对装夹可靠性进行了分析;从机身结构出发,对比了开式、闭式、半开式机身性能,选用了轻量化的半开式机身,设计了流水线嵌入式机身结构,并分析其最大角变形验证了机身可靠性;从热压机构出发,针对阴阳极特征差异分析了压力与热量传递方式,比对了不同原理的作业平台,并根据型面特征设计了真空夹紧系统;从力热测量出发,设计了带有温度补偿单元的压力传感器系统,构建了温度传感器控制系统,确定了位移传感器的位置分布并采用机器视觉建立准直检测系统。综合上述设计,搭建了氦氖激光陀螺仪电极铟封接系统的总体结构。
[Abstract]:The indium sealing technology of He-Ne laser gyroscope electrode is one of the key technologies to maintain the vacuum environment of microcrystal resonator. In this paper, the indium sealing structure of He-Ne laser gyroscope electrode is studied, the influence of residual stress and temperature on sealing fatigue failure is analyzed, and the indium sealing system of He-Ne laser gyroscope electrode is designed. The main contents are as follows: based on the theory of elastoplastic mechanics, the relationship between residual stress and deflection of sealing interface is analyzed. According to the theory of higher heat transfer, the heat transfer mode in sealing process is studied, and the law of temperature change is obtained. The mathematical and physical model of indium sealing structure of laser gyroscope electrode cavity was constructed. The residual stress of indium sealing structure was calculated and numerically analyzed according to the boundary conditions determined by the sealing process, and the axial direction of indium sealing structure was obtained. The influence of the diameter of indium wire ring and the stoichiometric ratio of indium alloy on the residual stress of indium sealing is analyzed, the sealing process parameters are optimized, and the vacuum indium sealing performance and sealing strength of the resonator are improved. It provides the technological parameters and theoretical basis for the subsequent design of the hot pressing indium sealing system of laser gyroscope electrode. According to the viscoplastic fluid equation and damage evolution theory, the Anand viscoplastic model is selected for fatigue analysis, the Indium sealing structure is simplified according to geometric symmetry and load symmetry, the two-dimensional finite element model is constructed and the boundary conditions and viscoplastic parameters are given. Based on the established finite element model, the fatigue failure problem of indium sealing structure under cyclic temperature is analyzed, and the failure trend is obtained. The dangerous joints are determined according to the cumulative plastic strain effect. The fundamental causes of stress hysteresis loop and temperature ratchet are analyzed. Based on the process parameters, dimension characteristics and sealing technology difficulties of the indium sealing model, the overall structure of indium sealing system is determined in order to improve the processing efficiency. The following aspects are studied: starting from the packaging fixture, The optimal location point distribution is determined, the force closed clamping of the cavity in the sealing state is realized, and the reliability of the clamping is analyzed, and the performance of the open, closed and semi-open fuselage is compared from the fuselage structure. The structure of pipeline embedded fuselage is designed, and the reliability of the fuselage is verified by analyzing the maximum angular deformation of the fuselage, and the pressure and heat transfer mode are analyzed according to the difference of the characteristics of cathode and anode from the hot pressing mechanism, and the reliability of the fuselage is verified by analyzing the maximum angular deformation of the fuselage. The vacuum clamping system is designed according to the characteristics of the profile, the pressure sensor system with temperature compensation unit is designed from the point of view of force and heat measurement, and the temperature sensor control system is constructed. The position distribution of displacement sensor is determined and the collimation detection system is established by machine vision. The overall structure of indium sealing system for He-Ne laser gyroscope electrode is built.
【学位授予单位】：合肥工业大学
【学位级别】：硕士
【学位授予年份】：2017
【分类号】：TN96

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