高速箭弹滚转气动特性

为提高尾翼弹射击精度，对高速箭弹滚转气动特性进行研究。建立火箭弹简化模型，对不同翼片斜置角 的火箭弹进行数值模拟，采用有限体积法对空间进行离散，通过多参考系模型模拟火箭弹的定常旋转，得出火箭弹 的滚转阻尼力矩导数和平衡转速，并分别对有、无旋转条件下的气动特性进行分析。计算结果表明：火箭弹升力系 数随攻角的增大而增大，随翼片斜置角的增大变化不大；滚转阻尼力矩导数在高空时会骤减，平衡转速随着马赫数 的增大而增大。

Rolling Aerodynamic Characteristics of High Speed Projectile

In order to improve the firing accuracy of tail-wing projectiles, the rolling aerodynamic characteristics of high speed projectiles were studied. A simplified model of rocket projectile is established to simulate the rocket with different oblique blade angle of the rocket''s wing. The finite volume method is used to discretize the space. The steady rotation of rocket projectile is simulated by multi-reference system model. The derivative of rolling damping moment and the balanced rotational speed of rocket projectile are obtained, and the aerodynamic characteristics of rocket with and without rotation are analyzed respectively. The calculation results show that the lift coefficient of rocket increases with the increase of angle of attack, but does not change with the increase of oblique angle of wing; the rolling damping moment derivative decreases sharply at high altitude, and the balance speed of projectile increases with increase of Mach number.