为使火箭弹卷弧尾翼在特定气动载荷下的结构质量最小,对其进行结构优化设计。在优化中以结构质量最小为目标,以包括尾翼弦长、厚度、前缘后掠角等几何参数为设计变量,强度和变形量为约束,通过集成iSIGHT和MSC.PATRAN/NASTRAN对卷弧尾翼结构进行优化设计,取得了较好的结果,减重效果明显。随后对优化结果进行分析,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。

To minimize structural mass of wrap around fins of the rocket under particular aerodynamic load, the structure optimal design of wrap around fins was done. The optimization took minimum structure mass as objective, some geometry parameters of the wrap around fins including fin length, thickness, leading edge sweepback and so on were chosen as the design variables, its intensity and distortion as the restrictions. Through integrating iSIGHT and MSC.PATRAN/NASTRAN, the optimization of the wrap around fins was done and preferable result was achieved, whose weight reduction was obvious. Then the optimization result was analyzed. It's found that the most influential design variables to optimal target and restrictions are central angle of wrap-around fins and the thickness.