风标式攻角传感器在超声速飞行运载火箭中的应用研究

以运载火箭上的风标式攻角传感器为研究对象,首先运用风洞试验研究其在超声速气流中的静态以及跟随特性。针对箭体常采用的规则旋成体,运用数值仿真分析当地攻角与来流攻角的关系。发现同一位置不同高度(距箭体壁面)当地攻角的变化较小,而同一截面不同周向位置上的影响则较大。在攻角平面内当地攻角不反映来流攻角信息;在垂直于攻角的平面内,受绕流的影响,当地攻角大于来流攻角;在两平面夹角的中心位置,当地攻角大致与来流攻角相当。运用数学分析解算出探测攻角与当地攻角、侧滑角的变换关系,最终获得攻角传感器的探测特性。基于火箭绕流流场的特征以及传感器的探测特性,建议工程应用时在4个象限的中心线上分别布置一个攻角传感器以获得飞行攻角和侧滑角。

Application Research of Wind Vane Sensors of Attack Angle on Rocket with Supersonic Flight

Angle of attack sensor for rockets has been researched in this paper. First, wind tunnel tests have been conducted to observe its dynamic following characteristics. With the consideration of a slender revolution body, simulations have been carried out to analyze the relationship between local attack angle and the incoming infinite flow attack angle. The influence of distance from the wall is small, but that of location is big. In the plane of attack angle, local attack angle doesn''t represent incoming angle. And in the perpendicular plane, the local one is bigger than the incoming one. In the middle plane between them, they are almost the same. Then, transformation of the output of sensor and the local attack angle on rocket has also been conducted mathematically, which finally refers to the probe characteristics. Furthermore, some engineering proposals have been presented for installation position of angle attack sensor on the rocket.