摘要
在文（一）得到的直升机旋翼系统运动方程的基础上，运用动态子结构的方法对旋翼系统和机身作为相对独立的部分进行分析，通过界面上的力平衡和几何协调将子系统耦合成整体系统。用分割——迭代法求解直至旋翼系统和机身的响应同时收敛到精度要求。并研制相应的计算程序。
On the basis of the equation of the rotary wing system established by previous paper , dynamic substructure method is used to analyze the response of the rotary wing system and the fuselage separately, the whole response of the coupled system is obtained through the interface force equilibrium and geometrical compatibility between the substructures. The iteration process is stopped until both the rotary wing system and the fuselage's responses converge simultaneously. The computer program is developed and the engineering example is given.
出处
《应用力学学报》
CAS
CSCD
北大核心
1999年第2期32-36,共5页
Chinese Journal of Applied Mechanics
基金
国家自然科学基金
关键词
直升机动力学
旋翼/机身耦合
气弹响应
helicopter dynamics, nonlinearity, time varying system, rotor/fuselage couplings, aeroelasticity.
