某直升机主桨叶翼型改进后经典颤振分析  

CLASSICAL FLUTTER ANALYSIS OF A HELICOPTER MAIN ROTOR BLADE AIRFOIL DEVELOPED

作　　者：杨福根[1] 马兵林[1] 

机构地区：[1]中国直升机设计研究所,景德镇333001

出　　处：《直升机技术》2001年第3期16-21,共6页Helicopter Technique

摘　　要：直升机经典颤振分析是研究刚性桨叶的最低阶挥舞模态与最低阶扭转模态的耦合不稳定性。经过直升机的理论研究与实验研究,已经形成了一套工程上实用的计算方法。这套方法是建立在金属铰接式旋翼之上。本文计算分析了某型机旋翼主桨叶翼型由NACA0012改进为TSAGI 12.XX翼型后旋翼的经典颤振。Classical flutter analysis of helicopter researched the instability of the rigid balde in the coupling of the lowest flap and torsion mode. A practical calculation method in engineering field has been established by the theory researching and test researching of helicopter. The method is based on the metallic articulate rotor. In this paper, the classical flutter of a helicopter main rotor is analyzed after its main rotor blade airfoil type be changed from NACA0012 to TSAGI 12.XX.

关 键 词：直升机 旋翼 经典颤振 主浆 叶型 气动弹性力学 计算模型 

分 类 号：V215.34[航空宇航科学与技术—航空宇航推进理论与工程]