摘要
介绍了一种运用有限元分析软件确定大展弦比复合材料机翼刚心位置的方法,并将该有限元分析方法得到的计算结果与理论方法进行比较,两者最多相差7.5%。将该方法运用到工程中,以大展弦比复合材料机翼刚心轴线的位置作为目标函数,静强度和稳定性作为约束,蒙皮、梁腹板各个铺层角的厚度和桁条、梁缘条的横截面积作为设计变量进行优化设计。经过多岛遗传算法和序列二次规划算法的迭代计算,最终得到机翼模型刚心轴线的最佳位置,与优化前相比刚心轴线位置更靠近于机翼前缘。
A simple method was presented by means of FE software to fix on the location of stiffness-center axis of a high-ratio-aspect composite wing model.The most difference was 7.5%,comparing the results of FE method with that of theoretical method.It was applied to an example of engineering.The optimal design was carried out with the location of stiffness-center axis of a composite wing as objective function and static strength and stability as constraints.The design variables were the lay-up thickness of panel and spar web,and the cross-section area of stringer and spar edge.Through the iterative calculation by multi-island genetic algorithm and sequential quadratic programming,the optimized location of stiffness-center axis of composite wing model was obtained finally.Compared with that optimized before,the location of stiffness-center axis is closer to leading edge of the wing.
出处
《中国机械工程》
EI
CAS
CSCD
北大核心
2013年第1期52-55,共4页
China Mechanical Engineering
基金
国家自然科学基金资助项目(51175424)
高等学校学科创新引智计划资助项目(B07050)
关键词
有限元方法
刚心轴线
优化设计
多岛遗传算法
序列二次规划算法
finite element（FE） method
stiffness center axis
optimization design
multi-island genetic algorithm
sequential quadratic programming
