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中文摘要：
气泡致动器是一种通过改变翼型局部轮廓引起流场改变，从而提高飞行器机动性能的微器件。同时，经致动器扰动后的流场也会对翼型的结构产生影响。采用ANSYS对NACA0012翼型周围流场进行仿真分析，得到了翼面压力分布曲线以及速度矢量场，与风洞实验所测压力值的最大误差为0．3％。仿真时比说明当攻角为15°时，气泡致动器安装于弦长的40％处时能够有效抑制分离涡的分布面积，对流场的控制作用最为明显。将安装有气泡致动器的翼型流场分析结果直接作用于翼型结构，进行流固耦舍分析，结果表明：气泡致动器在控制流场的同时增大了结构的变形。
英文摘要：
The balloon actuator is a micro device, which can improve the aerodynamic characteristics of aircraft by changing part of contour of the aerofoil. Meanwhile, the disturbed flow field also affects the original structure of the aerofoil. The flow field around the NACA0012 was simulated by ANSYS and the distribution of pressure and velocity field were obtained. Compared with wind tunnel test, the maximum deviation of pressure is 0.3%. When the angle of attack is set to 15 degree and the balloon actua- tor is located at the 40% of the chore length, the actuator can restrain the separation vortex area, which indicates that the flow field control is most effective. After applying the changed flow field results on the structure of the aerofoil, the coupling analysis indicates that the balloon actuator not only changes the flow field of the aerofoil but also augments the structure deformation.
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