为降低某实心导弹尾翼结构重量,参照飞机机翼梁、肋结构对其进行优化。在保持外形的基础上对其进行中空处理,在中空内部添加加强筋结构进行补强。通过初步设计确定了加强筋的数目,再利用标准二次多项式的方法拟合出加强筋位置和宽度参数对最大应力、最大变形和质量的响应面函数,根据响应面对参数进行优化。优化结果显示:在最大变形和最大应力基本保持不变的前提下,质量降低了25.67%,达到了较好的轻量化效果,对实心导弹尾翼轻量化设计具有一定的参考作用。

In order to reduce the weight of a solid missile tail, simulate the beam rib structure in the wing of plane to optimize it. Remove the internal area on the basis of maintaining the appearance, reinforce the hollow area by adding stiffeners. Determine the number of stiffeners through preliminary design, and then use the method of standard quadratic polynomial to fit response surface function of stiffener position and width to maximum stress, maximum deformation and mass, further optimize the parameters according to the response surface. The optimization results show that on the premise that the maximum deformation and maximum stress remain basically unchanged, the mass is reduced by 25.67%, and have a good lightweight effect, it can be used as a reference for the lightweight design of solid missile tail.