• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>Congress of the International Council of the Aeronautical Sciences >FATIGUE DESIGN PROCEDURE OF LONGITUDINAL AND TRANSVERSE FUSELAGE JOINTS
【24h】

FATIGUE DESIGN PROCEDURE OF LONGITUDINAL AND TRANSVERSE FUSELAGE JOINTS

机译：纵向和横向机身关节的疲劳设计程序

获取原文
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

A new fatigue design procedure of longitudinal and transverse medium-range civil aircraft skin joints was verified while taking into account the geometrical non-linearity (bending stress) based on results of the experimental study of specimens that simulate different variants of fuselage skin joints.Following the tests results a number of main joints failure types were determined and each of them is provided with a particular algorithm to calculate the reduced stresses given.The state of stress (SS) calculation of all joints variants tested is given. The calculation vs. experiment shows that the developed procedures are capable to provide a precision that is enough to be used practically to predict the fuselage joints fatigue stregnth taking into account the bending stress.
机译：验证了一种新的纵向和横向中范围内飞机皮肤关节的疲劳设计程序，同时考虑了几何非线性（弯曲应力）基于模拟机身皮肤关节的不同变体的试样的实验研究的结果。假设测试结果确定了许多主要关节故障类型，并且它们中的每一个都提供特定的算法来计算给出的应力减小。给出了所有接头变体的应力（SS）计算。计算与实验表明，开发的程序能够提供足够的精确性，这几乎足以预测化身关节疲劳患者的疲劳患者考虑到弯曲应力。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号