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。
Abstract
The description method of spatial motion for helicopter maneuver flight and helicopter tail drive shaft was proposed and the corresponding coordinate systems were established. The 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 Equations by using Galerkin calculation method. The horizontal shaft could be regarded as a special case of the oblique tail shaft, and the dynamical equations of horizontal shaft could derive from the oblique tail 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 by the combination of mathematical model and numerical simulation. The study results reveal that the spatial maneuver flight of helicopter will produce additional stiffness effect, damping effect and external excitation force, which may change the center position and size of the motion orbit of the tail drive shaft, on the bending vibration of helicopter 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
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Key words
maneuver flight /
Helicopter /
tail drive /
shaft /
bending vibration /
modeling /
stiffness /
damping
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倪德;朱如鹏;靳广虎;李发家.
机动飞行时直升机尾传动轴的横向振动建模与特性[J]. 振动与冲击, 2014, 33(7): 215-220
NI De;ZHU Ru-peng;JIN Guang-hu;LI Fa-jia.
Modeling and characteristics of bending vibration for helicopter tail drive shaft during maneuvering flight[J]. Journal of Vibration and Shock, 2014, 33(7): 215-220
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