飞机部件轴孔柔顺装配系统设计研究

发布时间：2018-02-01 07:00

本文关键词： 轴孔装配飞机部件被动柔顺调姿　出处：《浙江大学》2016年硕士论文　论文类型：学位论文

【摘要】：某型飞机鸭翼和垂尾等部件采用轴孔形式装配,配合间隙单边小于0.04mm,装配时易产生较大惯性力和接触力,无法沿用课题组激光跟踪仪辅助下的对接装配方法。为解决飞机部件高精度轴孔装配问题,结合浙江大学飞机数字化装配技术团队在飞机部件并联调姿平台系统的研究成果,本课题研发被动柔顺机构,满足飞机轴孔装配类部件自动化装配要求。本文以某型飞机鸭翼和垂尾高精度轴孔自动装配为研究对象,重点研究柔顺装配系统的设计与实现方案,并通过实验验证。主要内容包括:首先阐述飞机数字化装配技术的发展,针对鸭翼和垂尾等飞机部件轴孔.自动装配技术,分析轴孔柔顺装配技术的研究现状。接着以轴孔柔顺装配基本理论为基础,通过典型的柔顺手腕为例分析被动柔顺装置基本建模方法;对轴孔接触状态进行准静态分析和仿真研究,结合卡阻和楔紧状态分析远程柔顺中心位置对柔顺性能的影响。之后针对某型飞机鸭翼和垂尾装配需求,提出基于并联调姿系统和五自由度被动柔顺装置的鸭翼和垂尾柔顺装配系统设计方案,详细分析系统结构特点和参数设计过程。建立某型飞机鸭翼柔顺装配系统模拟实验平台,设计该柔顺装配系统力监测控制算法并完成Mechaware实现。结合实验过程,分析柔顺装配各阶段进给轴扭矩值的变化特点。实验表明在1mm位置误差和0.1°姿态误差范围内,柔顺装配平台能够有效完成实验样件的装配。最后总结全文的研究工作,对有待进一步研究的内容进行展望。
[Abstract]:The parts such as duck wing and vertical tail of a certain aircraft are assembled in the form of shaft holes, and the side clearance of the joint clearance is less than 0.04mm, so it is easy to produce larger inertial force and contact force during assembly. The method of docking assembly assisted by laser tracker can not be used. In order to solve the problem of high-precision shaft hole assembly of aircraft components. Combined with the research results of the aircraft digital assembly technology team of Zhejiang University in the aircraft components parallel attitude adjustment platform system, this paper develops passive compliance mechanism. To meet the requirements of automatic assembly of aircraft shaft hole assembly parts, this paper takes the automatic assembly of duck wing and vertical tail shaft holes as the research object, and focuses on the design and implementation of the compliant assembly system. The main contents are as follows: firstly, the development of aircraft digital assembly technology is introduced, and the automatic assembly technology for the shaft holes of aircraft components such as duck wing and vertical tail is introduced. Based on the basic theory of axial-hole compliance assembly, the basic modeling method of passive compliance device is analyzed by taking typical compliant wrist as an example. The quasi-static analysis and simulation of the contact state of the shaft hole are carried out, and the influence of the center position of the remote compliance on the compliance performance is analyzed in combination with the blocking and wedge-tight state. Then, the assembly requirements of the duck wing and vertical tail of a certain type of aircraft are addressed. The design scheme of duck wing and vertical tail compliant assembly system based on parallel attitude adjusting system and five degree of freedom passive compliance device is presented. The structural characteristics and parameter design process of the system are analyzed in detail. The simulation experimental platform of a certain aircraft duck wing compliant assembly system is established. The force monitoring control algorithm of the compliant assembly system is designed and implemented by Mechaware. The variation characteristics of feed shaft torque in various stages of compliant assembly are analyzed. The experimental results show that in the range of 1 mm position error and 0.1 掳attitude error. The compliant assembly platform can effectively complete the assembly of experimental samples. Finally, the research work of this paper is summarized, and the future research contents are prospected.
【学位授予单位】：浙江大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V262.4

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