直升机旋翼/机身耦合系统的气弹响应分析(二)方程的求解  

Aeroelastic Response Analysis of a Coupled Rotor/Fuselage System (Ⅱ) Solution of the Equations

作　　者：程永明[1,2] 任革学[1,2] 郑兆昌 余洵[1,2] 

机构地区：[1]清华大学 [2]航空工业总公司六0二所

出　　处：《应用力学学报》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

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.

关 键 词：直升机动力学 旋翼/机身耦合 气弹响应 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]