悬停状态下跷跷板式无轴承尾桨气弹稳定性研究  

Aeroelastic Stability Analysis for Bearingless- Teeter Tail Rotor

作　　者：赵文梅[1] 李建伟[1] 赵军[1] 冯拯桥[1] 

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《直升机技术》2016年第1期7-10,17,共5页Helicopter Technique

摘　　要：以某跷跷板式无轴承尾桨为研究对象,开展具有跷跷板与无轴承双重结构特性的尾桨的气弹稳定性分析研究。在考虑了集合型振型与周期型振型两种尾桨振型的基础上,建立跷跷板式无轴承尾桨动力学模型,研究了尾桨转速、尾桨总距及阻尼器阻尼刚度对尾桨摆振阻尼和阻尼比的影响。数值分析研究表明尾桨阻尼器阻尼刚度对尾桨气弹稳定性具有显著影响,通过控制阻尼器刚度可以有效提高该型尾桨气弹稳定性。In the background of bearingless- teeter tail rotor,considering the structure characters of both teeter rotor and bearingless rotor,a numerical method for aeroelastic stability analysis was developed. With considering collective mode and cycle mode of tail rotor,also with establishing the dynamical model of bearlingness- teeter rotor,the effects on the lag damping and damping ratio of tail rotor were researched by considering three aspects,including the rotate speed,collective and the damper stiffness of tail rotor. Numerical analysis showed that the stiffness of tail rotor damper had a significant effect on the aeroelastic stability of tail rotor; through controlling the stiffness of damper could effectively improve the aeroelastic stability of tail rotor.

关 键 词：跷跷板 无轴承 尾桨 阻尼器 气弹稳定性 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]