旋转控制固定鸭舵二维弹道修正弹气动特性

Aerodynamic Characteristics for Two-dimension Trajectory Correction Projectile With Spin-control Fixed-canard

为研究旋转控制固定鸭舵二维弹道修正弹的气动特性,采用风洞实验方法,对该弹气动特性随马赫数、攻角以及舵偏角的变化规律进行了研究。结果显示:在实验研究马赫数、攻角和舵偏角范围内,舵偏角增大对模型有一定增阻作用;模型升力系数随舵偏角增大而增大、随攻角呈线性变化关系;在相同马赫数和攻角下,俯仰力矩系数和滚转力矩系数随舵偏角的增大而增大。该研究结果为旋转控制固定鸭舵二维弹道修正弹的弹道设计和研究提供了参考依据。

To investigate the aerodynamic characteristics of two-dimension trajectory correction projectiles（TCP） with spin-control fixed-canard,wind tunnel tests were carried out to study the aerodynamic characteristics varying with Mach numbers, attack angles and rudder angles. The results show that,in the experiment rang of the Mach number, attack angle and rudder angle, drag coefficient and lift coefficient of model increases with the increase of rudder angle; its lift coefficient has linear relationship with attack angle; under the same Mach number and attack angle, the pitching moment coefficient and rolling moment coefficient increase with the increase of the rudder angle. The study result offers reference for trajectory design and research of the twodimension TCP with spin-control fixed-canard.