首页 | 本学科首页   官方微博 | 高级检索  
     检索      

锥面螺栓联接结构承载能力的实验预测
引用本文:董本涵,高鹏飞.锥面螺栓联接结构承载能力的实验预测[J].航空动力学报,1992,7(1):39-42,97-98.
作者姓名:董本涵  高鹏飞
作者单位:沈阳航空发动机研究所
摘    要:本文用模型试验方法研究了以套齿 (花键)联接的某发动机高压轴的轴向承载能力,分析了双锥面定位联接结构的载荷—变形规律以及它们与传统的螺栓联接结构载荷—变形规律的区别,讨论了影响双锥面联接结构轴向承载能力的因素,同时对某发动机高压轴的承载能力进行了试验确定,并对其装配工艺提出了改进建议。 

关 键 词:联接件    实验预测    双锥面    联接结构    结构承载能力    装配压力    螺栓联接    卸载过程    工作载荷    原型
收稿时间:1990/10/1 0:00:00

PREDICATION OF FASTENNING CAPACITY OF SCREWED JOINT STRUCTURE WITH CONE ASSEMBLY
Dong Benhan and Gao Pengfei.PREDICATION OF FASTENNING CAPACITY OF SCREWED JOINT STRUCTURE WITH CONE ASSEMBLY[J].Journal of Aerospace Power,1992,7(1):39-42,97-98.
Authors:Dong Benhan and Gao Pengfei
Institution:Shenyang Aeroengine Research Institute
Abstract:Assembly and cone assemble are employed between jointed pants for meeting the requirement of self centring.The fastenning capacity of rotator screwed joint with cone assembly can not be calculated according to traditional method,because it is not only related to elastical deformation of jointed parts but also to friction condition and slide condition between contact cone surface under simulation conditions of the geometry and assembly technique.A model test has been conducted to research the mechanical behaviour of the jointed parts in assembling and loading process.The load deformation relation of jointed parts reveals the difference between the plane assembly and the cone assembly.The relation of the former is linear and that of the latter nonlinear.In this research the loose condition of joint structure was defined experimentally as that the strain of cone parts equals to zero and the correlated load is named for loose load(or bearing capacity).Based on the test results the cone assembly jointed structure increases loose load owing to the friction factor.We have been predicted loose load of real jointed structure in an aeroengine by means of the model test and investigated the factors which have influence on bearing capacity.
Keywords:
本文献已被 CNKI 等数据库收录!
点击此处可从《航空动力学报》浏览原始摘要信息
点击此处可从《航空动力学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号