CAJ | 학술논문

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。
제출료직승궤공간궤동비행급미전동축운동위자적일충묘술방법，건립료상관좌표계。기우확전합밀돈원리，건립료직승궤공간궤동비행하미사축횡향만곡진동적동역학모형，병이용가료금법장편미분방정전화위상미분방정。수평전동축가이당작미사축적일충특례，통과일좌표변환구진즉가장미사축적동역학방정변환위수평전동축적동역학방정。분석료직승궤공간궤동비행대미전동축횡향만곡진동특성적영향。결과표명：직승궤적궤동비행회대미전동축적횡향만곡진동산생부가적강도효응、조니효응화격려효응，사득전동축궤적중심적위치화운동궤도적대소발생개변。
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.