摘要
根据工字梁腹板及缘条受力特点,计算了某型无人机机翼大梁在均布升力作用下腹板和缘条的内力。基于经典层合板理论和最大应力强度准则,采用Matlab软件编程,运用迭代法设计了机翼工字形层合结构大梁的铺层结构。建立了复合材料层合结构大梁的有限元模型,基于最大应力强度准则对大梁结构进行有限元强度校核,给出了各层的安全裕度。分析结果表明,基于经典层合板理论的迭代设计方法能够在有限次迭代后设计出符合要求的复合材料层合结构翼梁,层合结构翼梁各铺层安全裕度均大于0.5,该工字梁结构强度符合设计要求。
The inner forces of web and caps of an unmanned aircraft composite wing beam under uniformly distributed air lift is calculated based on the loading characteristics of the beam.The layer structure of the composite wing beam is designed using iterative method through Matlab programming.The design procedure is based on the classical laminate theory and maximum stress strength criterion.The finite element model of the composite wing beam is built,based on which the strength check is done using maximum stress criterion.The safety margin coefficient of each layer is given.It shows that the layer structure of composite wing beam can be properly designed by iteration method based on classical laminate theory.The iteration procedure is convergent.The least margin of safety of each layer is 0.981,which is greater than 0.5.Therefore,the design of the composite wing beam is a success which gives enough strength and light weight.
出处
《玻璃钢／复合材料》
CAS
CSCD
北大核心
2014年第1期72-75,共4页
Fiber Reinforced Plastics/Composites
基金
国家自然科学基金(NSFC)民航联合基金重点项目"民机复合材料结构维修基础理论与实验验证"(U1233202)
民航局科技项目重大专项(MHRD201240)
国家级大学生创新创业训练项目"多用途先进复合材料航模飞机研制"(20120624060)
中国民航飞行学院研究生创新基金"复合材料层合板制件湿法成型工艺研究"(X2011-12)
关键词
复合材料
机翼大梁
迭代法
有限元法
强度
composite material
wing beam
iteration method
finite element method
strength
