旋转导弹风洞六自由度自由飞动导数实验研究

风洞六自由度自由飞实验,是国内首次开展的一项新的风洞实验研究。实验设备为0.2米×0.2米的超声速风洞,求流马赫数为2和2.5。当超声速流场建立后,将以每分钟一万多转的高速旋转导弹模型,向实验段上游发射。模型在风洞观察窗区飞行时,用高速立体摄影拍摄模型飞行姿态随时间的变化。然后根据飞行姿态记录,通过数据辨识,求得俯仰力矩系数斜率,俯仰阻尼力矩系数和马格努斯力矩系数。实验精度优于国外弹道靶自由飞实验结果,尤其是动导数数据取得了满意的结果。

Experimental Investigation of a Spinning Missile Model for Dynamic Stability Coefficients in the Six- Freedom-Degree Free-Flight in Wind Tunnel

This paper reports experiment results of six-freedom-degree free-flight. The experiments are performed in a 0.2m by 0.2m supersonic wind tunnel with free-stream Mach numbers of 2 and 2.5 respectively. When the supersonic flow field is built up, the highly spinning model is launched to the upstream, and the altitute angles of the flying model are recorded by a high speed picture system. Through the processing of the altitute angle data, the static pitching moment stability coefficient, the damping moment stability coefficent and the Magnus moment stability coefficient can be obtained. The accuracy of the present results is better, especially for the dynamic derivatives, than those of the aeroballistic range.