南京航空航天大学学报2013，Vol.45Issue(3)：353-359,7.
复合材料加筋板长桁终止端设计与分析
Design and Analysis of Laminated Stiffened Composite Panels with Stringer Terminations
刘婷 1周凯华 2阴悦 3陈普会4
作者信息
- 1. 上海飞机设计研究院结构设计部,上海,200232
- 2. 上海飞机设计研究院适航中心,上海,200232
- 3. 南京航空航天大学金城学院,南京,211156
- 4. 南京航空航天大学航空宇航学院,南京,210016
- 折叠
摘要
Abstract
In an aircraft structure,it is often necessary to runout some of the stiffeners to satisfy detailed design requirements.Depending on the structural design,stiffeners for a wing structure may terminate at a chord-wise splice,at the forward or rear spar,at a rib,or at a structural discontinuity such as an access hole.Under in-plane loads,skin/stringer interfaces at run-out tips are vulnerable areas due to stiffness discontinuities and load-path centricities.In order to postpone the interface crack initiation and increase the failure load,stiffener webs are tapered near the termination,and then the portions of the skins lying below the run-out tip are thickened locally.The results of a parametric study examining these two types of design of laminated stiffened composite panels with stringer terminations are presented.The results indicate that local reinforcement on the skin can significantly increase the initial disbond load.关键词
复合材料/加筋板/长桁终止端/斜削设计/增厚设计Key words
composite/ stiffened panels/ stringer terminations/ tapered design/ thickened design分类
航空航天引用本文复制引用
刘婷,周凯华,阴悦,陈普会..复合材料加筋板长桁终止端设计与分析[J].南京航空航天大学学报,2013,45(3):353-359,7.
