摘要
针对面对称布局飞行器整体模态具有对称和反对称的特征,应用分枝模态法建模时采取以对称和反对称模态划分分枝,避免了按部件划分分枝产生的约束模态问题,且分枝间实现惯性和气动力解耦,有助于减缩自由度和计算规模。数值算例表明:其建模精度满足工程要求。
According to the characteristics of the symmetry and antisymmetry of mode shape about vertical meridian plane,symmetry and antisymmetry modal branches were divided by the branch mode method in this paper,in which the restraint modal from parts＇ interface by traditional divided method was not leaded in,and the decoupling of inertia and aerodynamic force about these two partial braches was derived.The method was helpful to reduce modeling DOF and computing scale.The numerical example showed that the accuracy was satisfied in engineering manufacture and development（EMD）.
出处
《上海航天》
2011年第2期27-31,共5页
Aerospace Shanghai
基金
国家自然科学基金(90716001)
"十一五"航天支撑技术项目(617010602)
关键词
飞行器结构
子结构
动力学
分枝模态法
面对称
解耦
有限元
Vehicle structure
Substructure
Dynamics
Branch mode method
Plane symmetry
Decoupling
Finite element method
