机构地区: 中山大学工学院应用力学与工程系
出 处: 《航空动力学报》 2007年第4期614-618,共5页
摘 要: 研究了一类含立方非线性二元机翼颤振系统的分岔现象.应用Hopf分岔定理验证了系统在颤振临界点必发生Hopf分岔.利用中心流形定理将系统降维,然后应用Hopf分叉的复数正规形法判别了极限环的稳定性,所得结果与数值解吻合. The bifurcations of the flutter system of a 2D airfoil with cubic nonlinearity were investigated in this paper. Hopf bifurcation theory was applied to verify Hopf bifurcation at the critical point of flutter. The high-dimensional system was transformed into a lower-dimensional one by center manifold theorem. And, the complex normal form method of Hopf bifurcation was used to analyze the stability of the limit cycle,with the results consistent with numerical solutions.
关 键 词: 航空 航天推进系统 非线性颤振 分叉 中心流形 复数正规形
领 域: [航空宇航科学与技术] [航空宇航科学技术]