具有瓦片翼的旋转子弹气动特性数值研究

The Aerodynamic Performance Simulation of a Spinning Projectile with Tile Wings

为了预估具有瓦片翼的旋转子弹气动特性,文中采用求解准定常流场的方法,对其进行数值模拟,结果表明:不旋转状态下数值模拟的结果与实验值一致性较好,高阻力、低升力的特点与常规弹箭正好相反,但是法向力特性与常规弹箭一致;旋转状态下低转速时法向力和静态参数类似,但高转速时法向力出现了反号,转速对俯仰力矩的影响也不同;提出旋转状态的气动参数m_z^(C_N)不能判定静稳定性,并采用火箭外弹道学对导弹稳定性的判定准则对旋转子弹动稳定性进行了分析。

To predict aerodynamic performance of a spinning projectile, quasi-stable flow simulations were used in the paper. The results show the calculation data are in good agreement with the experimental data in no-rolling frame. Its larger drag and lower lift are contrary to counterparts of traditional missiles, but the normal force acts consistently with traditional missiles. In the rolling frame, the normal force vector at lower rotating speed is opposite to that at the higher rotating speed. Rotational motion has different effect on pitch moment. It is not proved that the dynamic stability of the spinning projectile could be judged by rotational aerodynamic data （ mz^CN ）. According to stability conditions on rocket external ballistics, dynamic stability of the spinning projectile was analyzed.