摘要
复合材料加筋筒段是航空航天领域广泛采用的结构构形,其结构形式决定了重量及承压能力。为了研究加筋筒壁的承载能力,分析筋条间距、筒段长度和四种典型工程筋条截面的影响;以结构轻重量为目标函数,结构临界屈曲载荷、筋条局部屈曲载荷为约束,采用梁轴惯性矩平移模型,对复合材料筒壁0°、±45°、90°各铺层总厚度和筋条截面尺寸进行优化。结果表明结构轻重量设计中τ型桁条最有利,并得到其设计曲线,为工程设计应用提供参考。
The structural forms of cylindrical stiffened composite panels are widely used in the aerospace field . The weight and pressure bearing capacity are determined by the structure layout .In order to study the load car-rying capacity of cylindrical stiffened composite panel ,the influence of stringers’ distance ,panel’s length and typical sections ,the ply thickness of 0＆#176; ,＆#177; 45＆#176; ,90＆#176; and section sizing of stringer are optimized .The structural weight is chosen as objective function and the critical buckling load and local buckling load of stringer are con-straints .The results show thatτ-section stringer is most favorable in structural lightweight design ,and the de-sign curves are obtained as well .The results could provide valuable reference for project design .
出处
《航空工程进展》
2014年第3期377-382,共6页
Advances in Aeronautical Science and Engineering
关键词
复合材料
加筋筒段
承载能力
优化
惯性平移
composite
cylindrical stiffened panels
carrying capacity
optimization
inertial translation
