机翼失速颤振抑制的合成射流相位控制方法  

Phase control for stall flutter suppression with synthetic jet

作　　者：张海成[1,2] 刘春嵘[1,2] 徐道临[1,2] 胡振[1,2] 

机构地区：[1]湖南大学机械与运载工程学院,湖南长沙410082 [2]湖南大学汽车车身先进设计制造国家重点实验室,湖南长沙410082

出　　处：《振动工程学报》2014年第5期661-667,共7页Journal of Vibration Engineering

基　　金：国家自然科学基金资助项目(11272116)

摘　　要：提出合成射流抑制机翼失速颤振的相位控制方法。基于复合材料闭口截面薄壁梁理论建立了三元机翼两自由度的动力学模型,并采用CFD软件模拟了合成射流作用下翼型周围的流场,发现在一定条件下,合成射流可控制脱落涡的相位。在此基础上,提出采用合成射流控制翼展涡脱相位,降低脉动气动载荷在各阶振型上的投影幅值来抑制失速颤振。以NACA0012复合材料三元机翼为例,对其进行数值验证。结果表明:当翼展上合成射流激励器之间的相位差较大时,一阶弯曲和一阶扭转的共振幅值可降至约6%,而二阶弯曲和二阶扭转的共振幅值可降至10%。A phase control method of stall flutter suppression with synthetic jet（SJ）is presented in this paper.Based on the theory of thin-walled composite beams with closed sections,a dynamical model of three-dimensional wings is developed and the flow field around the wing under SJ action is also investigated with CFD software.The results show that the phase of vortex shedding could be controlled with SJ action under certain conditions.Based on this discovery,it is proposed to suppress the stall flutter by lowering the amplitude of the projective fluctuating aerodynamic loads on each of the modes.The effectiveness of our method is numerically verified by taking the NACA0012 airfoil as a case study.If the phase difference of SJ action on the wingspan is large enough,the resonant amplitude of the first bending mode and the first torsion mode will be reduced to about 6%,and those of the second modes will be decreased to about 10%.

关 键 词：失速颤振 合成射流 相位控制 涡激振动 

分 类 号：V215.34[航空宇航科学与技术—航空宇航推进理论与工程] O358[理学—流体力学]