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作 者:刘伟[1] 张碧妮 Liu Wei;Zhang Bini(Intelligent Mannfacturing College of Shaanxi Institute of Technology,Xi′an 710300,China)
机构地区:[1]陕西国防工业职业技术学院智能制造学院,西安市710300 [2]大连外国语大学软件学院
出 处:《工具技术》2022年第5期45-49,共5页Tool Engineering
基 金:陕西国防工业职业技术学院科研项目(Gfy18-26);陕西省职业技术教育学会2019年度职业教育研究课题(SZJYB19-123);陕西国防工业职业技术学院专项项目(GZY1717)。
摘 要:以某型号飞行器长桁零件为研究对象,围绕装配和加工工艺过程中装夹存在的问题,根据其服役环境,设计了符合飞行器长桁类零件装配的通用可调夹具,旨在提高装夹效率,满足多种截面长桁装夹要求,优化支撑布局。结合国内使用的飞机长桁类工件夹具现状,提出了L形长桁零件装配专用夹具的设计方案。在长桁受重力的情况下,外部施加60kN力时最大挠度为323mm,在长桁的上面打连接铆钉孔,使其承受能力大大降低,在承受同样的力时应力急剧增大,但弹性应力急剧减小,并且装配体中各零件间存在接触应力,其应力小于单个分析的应力,所以装配后长桁、框架及角材可用铆钉连接。将上述装配和仿真研究应用于该飞机装配中,通过仿真说明该装配技术的合理性和可行性。This paper takes a certain type of aircraft long trusses parts as the research object.Around the assembly and the processing technology process,the problems in the assembly clamping are studied.In order to improve the clamping efficiency,meet the requirements of various cross-section of long trusses clamping and optimise the support layout,a fast and universal adjustable clamping fixture is designed according to its service environment.A design of special L-shaped assembly fixture for long trusses is proposed considering the current domestic situation of the use of aircraft long trusses.In the case of a long trusses only subjected to gravity,a force of 60kN is applied and the maximum deflection is 323mm.The bearing capacity of long trusses is greatly reduced due to the rivet holes.Under the same force,the stress increases sharply but the elastic stress decreases sharply,and there is contact stress among each part of the assembly,it is less than that of individual analysis.So the assembly of the long truss,frames and angles with the connection of rivet is perfectly feasible.The assembly and simulation of the above study is applied to the simulation of aircraft assembly to demonstrate the rationality and feasibility of the assembly technique.
关 键 词:机床夹具设计 接触应力 飞行器长桁零件 三维模型
分 类 号:TG75[金属学及工艺—刀具与模具] TH162.1[机械工程—机械制造及自动化]
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