摘要
滚转阻尼导数是判断导弹动稳定性的重要气动参数。采用求解定常流场的方法,对超声速阶段平板翼翼身组合体和栅格翼翼身组合体的滚转特性进行数值模拟,并与平板翼翼身组合体的实验数据相比,符合较好。计算结果表明,栅格翼的滚转阻尼导数变化复杂,由于弹体背风面分离流和栅格翼翼面失速的影响,滚转阻尼导数随着攻角增加有两次明显转折;平板翼的滚转阻尼导数随着马赫数增加逐渐减小,而栅格翼的滚转阻尼导数随马赫数同样呈现两次转折,在Ma=3.5达到最大值。
Roll damping derivative is an important aerodynamic coefficient which determines the dynamic stability of missile. Computational fluid dynamic simulations were used to predict roll damping derivative of missile with planar and grid fins at supersonic speeds based on steady flow. Compared with planar fins, roll damping derivative of grid fins has complex variation, the trend curve has two turning points as the angle of attack increases, which are due to the influence of separated flow to grid fins and stall of the fins separately; the derivative of planar fins get smaller as Mach number increases, while the curve of grid fins changes twice and gets a maximum point at Ma = 3.5.
出处
《空气动力学学报》
EI
CSCD
北大核心
2012年第2期151-156,共6页
Acta Aerodynamica Sinica
关键词
航天器结构与设计
栅格翼
滚转阻尼导数
数值模拟
spacecraft structure and design
gird fin
roll damping derivative
numerical simulation
