大攻角动导数支撑系统的设计与研究

Bracing System for Dynamic Derivative of Large Attack Angle

在对飞行器进行动态稳定性分析时,需要有关的动态气动参数,这些参数值不能用理论方法计算,必须用风洞实验方法确定,为此,设计了在风洞实验中用于测量动态导数的支撑系统及研究了影响动态导数变化的因素.此系统采用强迫振动法,利用正弦发生器,使模型产生单自由度的滚转、偏航、俯仰、升沉或平移振动,进而求得模型在各种姿态下的动导数,此数据可为研究飞行器在大攻角状态下的动态特性提供可靠的依据.本装置角度变化范围大,精度高、风洞的堵塞度小、支架干扰量小,提高了实验的测量精度.

Some aerodynamic parameters are needed when we design aircraft navigation or commanding systems and analyse dynamic stability . These values of dynamic derivatives can not be obtained from theoretical calculations , it must be obtained from wind tunnel tests . The paper has introduced design of the bracing system and some influence factors . The model can oscillate in spinning , yawing , pitching or so with constrained oscillation of the system , and the derivative of a kind of attitudes is gained . Studying dynamic characteristics of aircraft at large attack angle can rely on the data .