超声速流中二元机翼的颤振与极限环  

AERODYNAMIC FLUTTER AND LIMITED CYCLE OF A 2-D WING IN THE HYPERSONIC FLOW FIELD

作　　者：陈科文[1] 赵海[1] 周立杰 赵娜[1] 曹登庆[1] 

机构地区：[1]哈尔滨工业大学航天学院,137信箱哈尔滨150001 [2]哈尔滨综合开发有限公司,哈尔滨150090

出　　处：《动力学与控制学报》2012年第1期62-66,共5页Journal of Dynamics and Control

基　　金：国家自然科学基金资助项目(90816002;10772056);航天技术支撑基金资助项目(2009-HIT-HGD-07)~~

摘　　要：以沉浮和俯仰自由度上具有间隙立方结构非线性的二元机翼模型为例,考虑系统的结构阻尼,建立了系统的非线性动力学方程.通过修正的三阶活塞理论模拟了超声速流中机翼的非定常气动力和气动力矩.引入无量纲参数将系统动力学方程无量纲化,通过数值模拟得到了二元机翼的时域响应和系统的相轨迹变化规律.通过系统的分岔图得到了无量纲参数和系统周期运动振幅幅值的关系.研究结果表明,当无量纲流速增大至临界颤振速度时出现极限环振动,系统由稳定运动过渡到周期振动,继续增大无量纲流速会有更加复杂的动力学行为.A dynamical model of the airfoil with cubic and freeplay nonlinearity in both pitch and plunge was established. The nonlinear aerodynamic force and moment on the wing were evaluated by the third order piston theory. A bifurcation diagram,which presents the relevance between bifurcation parameter and amplitude of the periodic motion,was given numerically. When the dimensionless flight speed increases to the flutter critical speed, limited cycle can be observed in both pitch and plunge,and Hopf bifurcation appears,which means the stable point bifurcates to a periodic motion. And when further increasing the dimensionless flight speed,a more complex dynamic phenomenon will turn up .

关 键 词：极限环颤振 活塞理论 间隙非线性 分岔 

分 类 号：O322[理学—一般力学与力学基础]