【作者】 艾平贵；

【导师】 朱如鹏；

【作者基本信息】 南京航空航天大学 ， 机械设计及理论， 2009， 硕士

【摘要】 传动系统是直升机的重要组成部分,其振动特性直接影响着整个直升机的性能。尾传动系统是一个多级数、带分支、含非平行轴的齿轮耦合复杂转子系统。由于锥齿轮啮合的作用,每段传动轴的振动已不再是独立的,而是彼此耦合的。直升机尾传动系统日益向高效率、高速度、高精度、高承载能力方向发展,这就有可能使系统进入共振区而发生共振现象。在传动系统设计时,需要掌握结构参数对系统固有特性的影响规律,从而调整参数,使系统在工作中避免共振,保证直升机的稳定性与可靠性。一般来讲,传动系统发生两类振动即横向振动和扭转振动。本文首先根据振动学理论和有限元基本原理,分析了直升机尾传动系统的结构特点;建立了直升机尾传动系统的三维实体模型;结合机械动力学等效原理,等效出直升机尾传动系统的动力学模型,包括直升机尾传动系统的弯曲动力学模型、扭转动力学模型,运用ANSYS软件平台建立了直升机尾传动系统的参数化模型。其次,分析了直升机尾传动系统的横向振动,包括单段轴、水平轴段以及尾传动系统的固有频率和振型;并在此基础上分析了支承刚度对尾传动系统横向振动的影响以及支承数量对水平轴段的影响,进一步分析了尾传动系统横向振动的谐响应分析。最后,分析了尾传动系统的扭转振动,包括扭转动力学模型的建立以及有限元模型的建立;通过等效质量-弹簧系统和ANSYS有限元分别分析了尾传动系统的扭转振动的固有频率和振型。对比两种分析结果,进一步分析了尾传动系统扭转振动的谐响应分析。更多还原

【Abstract】 Drive system is an important part of helicopter, the vibration characteristics directly impact on the helicopter’s performance. Tail drive system is a multi-series, with branches and including non-parallel to the axis of the rotor gear coupled complex system. Due to the role of the bevel gear engaging, each of the shaft vibration is no longer independent, but coupled with each other. The direction of helicopter tail drive is high-efficiency, high-speed, high precision and high load capacity, which may caused the system entering the resonance zone, and may caused of resonance phenomenon. In the design of drive system, which needs to master the influence law of structural parameters of the system inherent characteristics, thus adjust the parameters to avoid the system resonance and to ensure the helicopter stability and reliability. In general, drive system occurrence lateral vibration and torsion vibration.This paper based on vibration theory and the basic principles of finite element, analysis of the structure of the helicopter drive characteristics. Build the three-dimensional solid model of the helicopter tail drive system, and combine mechanical dynamics equivalence principle. Equivalent the helicopter tail drive system dynamics model, including the helicopter’s tail drive system bending dynamics model, torsion dynamics model. The use of ANSYS software platform for the establishment of a helicopter tail drive system parameterized model.Secondly, analysis of lateral vibration of the helicopter tail drive, including the natural frequency and vibration mode of the single shaft, horizontal continuous shaft, the drive system. On the basis of analysis of the supporting stiffness influence of the drive system lateral vibration, as well as the number of supports influence of horizontal continuous shaft. Further analysis the helicopter tail drive system lateral vibration harmonic response.Finally, analysis of torsion vibration of the helicopter tail drive system, including build torsion dynamics model and finite element model. Through equivalent mass-spring system and ANSYS finite element, respectively analysis of the helicopter tail drive system’s natural frequency and vibration modes of torsion vibration. Contrast two kinds of analysis results. Further analysis of the helicopter tail drive system of torsion vibration harmonic response.更多还原