论文部分内容阅读
曲面锥外形头部整流罩较之现役普遍采用的钝头+单锥/双锥外形头部整流罩,能减小阻尼、消除或减小锥柱交界处较大的脉动压力、大大改善火箭动态气动特性。运用锥壳等效理论和夹层结构计算方法,对整流罩泡沫夹层冯·卡门曲面锥段结构外压计算方法进行了研究,通过理论计算和缩比试验证明:基于锥壳等效理论和夹层结构计算方法及其试验修正系数选取所得出的泡沫夹层冯·卡门锥段外压计算方法能够有效地指导整流罩泡沫夹层冯·卡门曲面锥段结构设计与计算。
Curved cone shape head fairing Compared with the commonly used blunt-ended + single cone / double cone shape head fairing, it can reduce the damping, eliminate or reduce the larger fluctuating pressure at the cone junction and greatly improve the rocket dynamic Pneumatic features. By using the equivalent theory of conical shell and the calculation method of sandwich structure, the calculation method of the external pressure of the conical section structure of von Karman surface of bubble sandwich was studied. Based on the theoretical calculation and the shrinkage ratio test, it was proved that based on the cone shell equivalent theory and the sandwich structure Calculation method and its test correction factor selection of the foam interlayer von Karman cone section external pressure calculation method can effectively guide the cone bubble sandwich von Karman surface cone section structure design and calculation.