摘要
某型直升机的响应计算通过建立该机全机有限元模型,采用标准软件 MSC.nastran 提供的求解序列SOL111,即频率响应的模态求解法完成全机传递函数计算。然后根据该型机旋翼桨毂载荷,计算了频率等于旋翼一阶通过频率的旋翼桨毂载荷作用下的机身的加速度振动响应,计算结果为该型机全机振动水平预估提供原始数据。
In this paper,the vibration acceleration responses on a helicopter fuselage under rotor hub loads of the first passage fre- quency are calculated through building up finite element model of whole fuselage structure,using solution series SOL111 of MSC. nastran.The calculated results provide data for predicting the helicopter vibration level.
出处
《直升机技术》
2003年第4期11-14,共4页
Helicopter Technique
关键词
直升机
机身振动响应
有限元
模态求解
helicopter
vibration acceleration responses
finite element analysis
