摘要
为使火箭弹卷弧尾翼在承受特定气动载荷情况下的自身结构质量最小,对其进行了结构优化设计。以包括尾翼弦长、厚度、前缘后掠角等在内的6个几何参数作为设计变量,对应的强度和变形量为约束,以有限元法为分析工具,以非线性规划为搜索算法在整个设计空间里进行优化计算,取得了较好结果,卷弧翼减重效果明显。随后对优化结果进行权重分析,得到了对优化目标和约束影响较大的设计变量,分别是卷弧的圆心角和翼片厚度。最后,讨论了包括气动优化在内的进一步研究方向。
In order to make the structural mass minimum, the structure optimal design of the wrap-around fins subjected to special aerodynamic loads of the rocket was conducted. In the whole design optimization, six geometry parameters of the wrap-around fins were chosen which include fin length, thickness, leading edge sweepback as the design variables, its intensity and distortion were taken as the restrictions, the finite element method as analytical tool and non-linear program as search algorithm. A preferably result of obvious weight reduction was reached. The weight factors analysis results show that the design variables which have the greatest influences on optimal target and restrictions are the central angle of wrap-around fins and the thickness. Finally, the direction of research of wrap-around fins including the aerodynamic optimization was discussed.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2009年第5期478-481,共4页
Journal of Solid Rocket Technology
基金
国防基础科研项目(B222006060)
关键词
卷弧尾翼
有限元
优化设计
权重分析
wrap-around fins
finite element
optimal design
weighting analysis
