机翼摇晃运动作为现代高机动性飞机在失速迎角附近飞行时出现的一种现象而受到普遍重视.迄今为止,对机翼摇晃的研究工作一般沿两种途径进行。一种为分析产生机翼摇晃的气流流动机理;另一种根据机翼摇晃时飞机运动的特点进行讨论。本文从飞机六自由度方程入手,建立描述大迎角机动飞行的空气动力模型。在此基础上,按照微分方程定性理论和传播矩阵,研究机翼摇晃的产生原因和飞机运动的特点。结果认为,机翼摇晃是一种非线性系统的Hopf分支现象.对具有中等后掠角机翼的飞机,产生机翼摇晃的主要原因是滚转阻尼力矩随迎角和侧滑角的变化. Wing-roll motion is widely regarded as a phenomenon that occurs when modern high-maneuver aircraft fly near a stalled angle of attack. So far, research on wing roll has generally been conducted in two ways. One is to analyze the flow mechanism of the airfoils that generate the wing sway and the other is to discuss the characteristics of the airfoils when the wing is swaying. In this paper, we start with the six degree of freedom equation of the aircraft and establish an aerodynamic model that describes the maneuvering flight at high angles of attack. On this basis, according to the qualitative theory of differential equations and propagation matrix, the causes of wing flapping and the characteristics of aircraft movement are studied. The results show that wing-rocking is a Hopf bifurcation of a nonlinear system. For aircraft with medium-swept-wing wings, the main reason for wing-wing roll is the variation of roll damping torque with angle-of-attack and side slip angle.