航空学报 > 1987, Vol. 8 Issue (2): 39-46

飞机结构的损坏过程承载能力、破坏部位有限元分析

黄敬贤, 黄雅章, 刘夏石   

  1. 中国直升机研究和设计所
  • 收稿日期:1986-03-31 修回日期:1900-01-01 出版日期:1987-02-25 发布日期:1987-02-25

LOADED CAPABILITY OF AIRFRAME IN THE PROCESS OF DAMAGE——FINITE ELEMENT ANALYSIS FOR STRUCTURAL FAILURE AREA

Huang Jingxian, Huang Yazhang, Liu Xiashi   

  1. Chinese Helicopeter Research and Development Institute
  • Received:1986-03-31 Revised:1900-01-01 Online:1987-02-25 Published:1987-02-25

摘要: 本文提出一个适合于飞机结构非线性分析的有限元素组合算法。考虑到元素材料屈服和/或失稳后出现的非线性问题导出了有限元计算格式。本方法已经实际用于描述××型直升机结构静力试验从开始加载到局部损伤或失稳、扩展直至破坏的全过程受力状态;用于确定该机结构的最大承载能力和破坏部位,并取得了非常好的结果。文中介绍了数值算例及其与试验结果的对此。

Abstract: This paper presents a combined finite-element algorthm for non-linear analysis in the process of damage of loaded airframe. On account of the peculiar stressed conditions appeav-ing as yielding and/or buckling in thin sheet, an incremental loading method is used. It is necessary in each loading condition to consider the yielding and/or buckling due to prior stress levels that, decrease airframe loaded capability and lead to geometric changs. The me-thed keforms new stiffness matrix and iterates on the basis of initial stress, then calculates the displacement, strain and stress increments under each incremental load.This method has practically been used in some type of helicopter to describe the whole loading process: initial loading--local damage or crippling and its extension--final damage, and to determine the maximum load and critical failure area of the airframes. The numerical calculation and its comparison with test results are very satisfactary.