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大展弦比复合材料机翼刚心分析与剪裁设计
引用本文:董永朋,霍世慧,华林,王富生,岳珠峰. 大展弦比复合材料机翼刚心分析与剪裁设计[J]. 中国机械工程, 2013, 24(1): 52-55
作者姓名:董永朋  霍世慧  华林  王富生  岳珠峰
作者单位:1.西北工业大学,西安,710129
2.中国运载火箭技术研究院,北京,100076
基金项目: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)
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75%。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。

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

Analysis and Tailoring Design of Stiffness-center of a High-ratio-aspect Composite Wing
Dong Yongpeng,Huo Shihui,Hua Lin,Wang Fusheng,Yue Zhufeng. Analysis and Tailoring Design of Stiffness-center of a High-ratio-aspect Composite Wing[J]. China Mechanical Engineering, 2013, 24(1): 52-55
Authors:Dong Yongpeng  Huo Shihui  Hua Lin  Wang Fusheng  Yue Zhufeng
Affiliation:1.Northwestern Polytechnical University,Xi’an,710129 2.China Academy of Launch Vehicle Technology,Beijing,100076
Abstract: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 75%, 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.
Keywords:finite element(FE) method  stiffness center axis  optimization design  multi-island genetic algorithm  sequential quadratic programming
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