机动飞行时直升机尾传动轴的横向振动建模与特性  

Modeling and characteristics of bending vibration for helicopter tail drive shaft during maneuver flight

作　　者：倪德[1] 朱如鹏[1] 靳广虎[1] 李发家[1] 

机构地区：[1]南京航空航天大学江苏省精密与微细制造技术重点实验室,南京210016

出　　处：《振动与冲击》2014年第7期215-220,共6页Journal of Vibration and Shock

基　　金：国家自然科学基金(51375226);高等学校博士学科点专项科研基金资助课题(20113218110017);江苏省高校优势学科建设工程资助;江苏省普通高校研究生科研创新计划资助项目(CXZZ11_0199);中央高校基本科研业务费专项资金资助

摘　　要：提出了直升机空间机动飞行及尾传动轴运动位姿的一种描述方法,建立了相关坐标系。基于扩展哈密顿原理,建立了直升机空间机动飞行下尾斜轴横向弯曲振动的动力学模型,并利用伽辽金法将偏微分方程转化为常微分方程。水平传动轴可以当作尾斜轴的一种特例,通过一坐标变换矩阵即可将尾斜轴的动力学方程变换为水平传动轴的动力学方程。分析了直升机空间机动飞行对尾传动轴横向弯曲振动特性的影响。结果表明:直升机的机动飞行会对尾传动轴的横向弯曲振动产生附加的刚度效应、阻尼效应和激励效应,使得传动轴轨迹中心的位置和运动轨道的大小发生改变。A description method for spatial motions of helicopter maneuver flight and helicopter tail drive shaft was proposed and the corresponding coordinate systems were established.A lateral bending vibration model of the helicopter oblique tail drive shaft during maneuvering flight was established by using the extended Hamilton＇s principle,and the partial differential equations were converted into the ordinary differential ones by using Galerkin method.A horizontal shaft could be regarded as a special case of an oblique tail shaft,and the dynamic equations of the oblique tail drive shaft could be converted into those of a horizontal drive shaft by using a coordinate transformation matrix.The effects of spatial maneuver flight on the vibration characteristics of the tail drive shaft were discussed with the combination of mathematical model and numerical simulation.The study results revealed that the spatial maneuver flight of a helicopter can produce additional stiffness effect,damping effect and external excitation force effect on the bending vibration of the helicopter tail drive shoft,they may change the center position and the size of the motion orbit of the tail drive shaft.

关 键 词：机动飞行 直升机 尾传动 轴 横向振动 建模 刚度 阻尼 

分 类 号：TH113.2[机械工程—机械设计及理论] TH113.1