中央翼翻转机构的设计研究
发布时间：2018-08-02 08:08
【摘要】：随着科学技术的不断发展,飞机成为现代生活中重要的交通工具之一。中央翼是飞机整体的重要组成部件,位于飞机中段的内部,无完整的外形。它起着连接飞机左右外翼的重要作用,承受着两翼的升力和机身的重力,是整架飞机的重要受力部件。因此,中央翼的安装及加工精度对整架飞机的平衡和受力有着重要的影响。中央翼完成安装后,需要对其端面进行数控孔加工。但是中央翼在安装型架上和在进行端面孔加工时所处的状态是相互垂直的,即需要将中央翼从安装型架上取下之后翻转90°。原有的翻转机构虽然能使中央翼顺利地完成翻转,但是翻转过程较复杂,效率低下,且存在着一定的安全隐患。飞机中央翼翻转机构设计的目的在于设计一机构,使中央翼方便、快捷地进行翻转,减小机构对生产工人造成的安全隐患,节省翻转过程中的人力和物力,提高生产效率。本文依据项目委托企业的实际要求和翻转机构的发展趋势,结合中央翼翻转时的实际情况,进行方案设计。通过CATIA三维设计软件对其进行建模、利用虚拟样机技术对其进行建模、仿真,验证方案的可行性,最后通过ANSYS有限元软件对翻转机构的重要部件进行分析。本文主要的研究内容为:1.依据翻转机构的设计要求及中央翼的下架路线,进行翻转机构的方案设计,确定翻转原理、吊点的选择、动力源及其控制方式的选择。2.翻转机构中重要部件的设计,包括吊梁、吊挂、支撑架的设计及截面尺寸的确定及强度校核、带传动的摩擦力的计算和该翻转机构是否会出现带传动的打滑现象的研究。3.在Recurdyn中建立翻转机构的简化模型,并通过添加约束、载荷、驱动等,建立虚拟样机的模型,通过运动学仿真分析验证模型的正确性,得出在运转过程中的一系列动态参数。4.在CATIA中建立吊梁的模型,并通过数据接口导入ANSYS Workbench,利用ANSYS Workbench软件对横梁进行静力学分析,得到梁所受的应力变化和梁的变形,并通过梁的应变疲劳分析,得出梁在使用一定次数后,吊梁各个部位的安全系数、寿命及其各个部位的损伤。5.利用ANSYS Workbench软件的响应曲面分析工具分析吊梁横截面的各个尺寸对梁的总体变形和等效应力的影响,并得出在梁的总体变形和等效应力不变的情况下,使其质量最小的横截面尺寸参数。
[Abstract]:With the development of science and technology, aircraft has become one of the most important means of transportation in modern life. The central wing is an important component of the aircraft. It is located in the middle of the aircraft and has no complete shape. It plays an important role in connecting the left and right wings of the aircraft, bearing the lift of the two wings and the gravity of the fuselage. It is an important force component of the whole aircraft. Therefore, the installation and machining accuracy of the central wing have an important effect on the balance and force of the whole aircraft. After the central wing is installed, it is necessary to carry out NC hole machining on its end surface. But the central wing is perpendicular to each other on the mounting frame and in the machining of the end hole, that is to say, it is necessary to remove the central wing from the mounting frame and turn it over 90 掳. Although the original turnover mechanism can make the central wing complete the turnover smoothly, the turnover process is more complex, inefficient and has certain security hidden trouble. The purpose of the design of the aircraft central wing turnover mechanism is to design a mechanism to make the center wing flip conveniently and quickly, to reduce the hidden danger of safety caused by the mechanism to the production workers, to save the manpower and material resources in the turnover process, and to improve the production efficiency. According to the actual requirements of the project entrustment enterprise and the development trend of the turnover mechanism, combined with the actual situation of the central wing turnover, the project design is carried out in this paper. It is modeled by CATIA 3D design software, modeled by virtual prototyping technology, simulated and verified the feasibility of the scheme. Finally, the important parts of the flip mechanism are analyzed by ANSYS finite element software. The main contents of this paper are: 1: 1. According to the design requirements of the turnover mechanism and the dismount route of the central wing, the scheme design of the turnover mechanism is carried out, and the turnover principle, the choice of the lifting point, the choice of the power source and its control mode are determined. The design of the important parts in the reversing mechanism includes the design of the suspension beam, the hanging, the design of the support frame, the determination of the cross section size and the strength check, the calculation of the friction force of the belt transmission and the study on whether the sliding phenomenon of the belt transmission will occur in the flip mechanism. The simplified model of the flip mechanism is established in Recurdyn, and the model of virtual prototype is built by adding constraints, loads, drives, etc. The correctness of the model is verified by kinematics simulation analysis, and a series of dynamic parameters .4in the process of operation are obtained. The model of suspension beam is established in CATIA, and the data interface is imported into ANSYS Workbench. The static analysis of the beam is carried out by using ANSYS Workbench software. The stress changes and the deformation of the beam are obtained, and the strain fatigue analysis of the beam is carried out. After a certain number of times, the safety factor, life span and damage of each part of the beam are obtained. The response surface analysis tool of ANSYS Workbench software is used to analyze the influence of the dimensions of the cross section of the suspension beam on the total deformation and equivalent stress of the beam, and it is obtained that the total deformation and equivalent stress of the beam are invariant. Cross section size parameter that minimizes its mass.
【学位授予单位】：陕西理工学院
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V261
本文编号：2158763
[Abstract]:With the development of science and technology, aircraft has become one of the most important means of transportation in modern life. The central wing is an important component of the aircraft. It is located in the middle of the aircraft and has no complete shape. It plays an important role in connecting the left and right wings of the aircraft, bearing the lift of the two wings and the gravity of the fuselage. It is an important force component of the whole aircraft. Therefore, the installation and machining accuracy of the central wing have an important effect on the balance and force of the whole aircraft. After the central wing is installed, it is necessary to carry out NC hole machining on its end surface. But the central wing is perpendicular to each other on the mounting frame and in the machining of the end hole, that is to say, it is necessary to remove the central wing from the mounting frame and turn it over 90 掳. Although the original turnover mechanism can make the central wing complete the turnover smoothly, the turnover process is more complex, inefficient and has certain security hidden trouble. The purpose of the design of the aircraft central wing turnover mechanism is to design a mechanism to make the center wing flip conveniently and quickly, to reduce the hidden danger of safety caused by the mechanism to the production workers, to save the manpower and material resources in the turnover process, and to improve the production efficiency. According to the actual requirements of the project entrustment enterprise and the development trend of the turnover mechanism, combined with the actual situation of the central wing turnover, the project design is carried out in this paper. It is modeled by CATIA 3D design software, modeled by virtual prototyping technology, simulated and verified the feasibility of the scheme. Finally, the important parts of the flip mechanism are analyzed by ANSYS finite element software. The main contents of this paper are: 1: 1. According to the design requirements of the turnover mechanism and the dismount route of the central wing, the scheme design of the turnover mechanism is carried out, and the turnover principle, the choice of the lifting point, the choice of the power source and its control mode are determined. The design of the important parts in the reversing mechanism includes the design of the suspension beam, the hanging, the design of the support frame, the determination of the cross section size and the strength check, the calculation of the friction force of the belt transmission and the study on whether the sliding phenomenon of the belt transmission will occur in the flip mechanism. The simplified model of the flip mechanism is established in Recurdyn, and the model of virtual prototype is built by adding constraints, loads, drives, etc. The correctness of the model is verified by kinematics simulation analysis, and a series of dynamic parameters .4in the process of operation are obtained. The model of suspension beam is established in CATIA, and the data interface is imported into ANSYS Workbench. The static analysis of the beam is carried out by using ANSYS Workbench software. The stress changes and the deformation of the beam are obtained, and the strain fatigue analysis of the beam is carried out. After a certain number of times, the safety factor, life span and damage of each part of the beam are obtained. The response surface analysis tool of ANSYS Workbench software is used to analyze the influence of the dimensions of the cross section of the suspension beam on the total deformation and equivalent stress of the beam, and it is obtained that the total deformation and equivalent stress of the beam are invariant. Cross section size parameter that minimizes its mass.
【学位授予单位】：陕西理工学院
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V261
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