摘要
采用有限元分析方法,确定复合材料机翼中刚心轴线的位置。建立一系列的复合材料机翼有限元模型,对影响刚心轴线位置的因素进行具体分析。结果表明,质量分布、展弦比和后掠角的变化对机翼刚心轴线位置有较大的影响,前后梁的位置、铺层形式、铺层比例和铺层顺序的变化对机翼刚心轴线位置的影响相对较小。本研究将为复合材料机翼的设计提供一定的参考。
A method is presented to fix on the location of stiffness-center axis of a composites wing by use of finite element method. A series of finite element models of composites wing are set up to analyze the influencing factors on stiffness-center axis. The result shows it has greater influence on the location of stiffness-center axis with change of mass distribution, aspect ratio and swept-back angle, and relatively smaller influence with change of the location of spar, lay-up form, lay-up ratio and lay-up sequence. It provides some references to design the composites wing.
出处
《航空制造技术》
北大核心
2012年第19期79-82,共4页
Aeronautical Manufacturing Technology
基金
国家高技术研究发展专项863项目(2009AA04Z418)资助
高等学校学科创新引智计划项目(B07050)资助
关键词
有限元方法
刚心轴线
展弦比
后掠角
Finite element method Stiffness-center axis Aspect ratio Swept-back angle
