直升机地面开车过程旋翼/机体/起落架耦合气弹动力学分析  

Aeroelastic analysis of rotor/fuselage/landing gears coupled system for helicopter during rotor starting process on the ground

作　　者：侯鹏[1] 杨卫东[1] 孙东红[2] 黄斌根[2] 董凌华[1] 

机构地区：[1]南京航空航天大学直升机旋翼动力学国家重点实验室,江苏南京210016 [2]中国直升机设计研究所,江西景德镇333001

出　　处：《振动工程学报》2013年第3期318-327,共10页Journal of Vibration Engineering

摘　　要：基于Hamilton能量原理,考虑直升机地面开车过程旋翼转速变化引起的惯性力及气动力变化的影响,建立旋翼起动过程,旋翼/机体/起落架耦合非线性气弹动力学模型,模拟分析直升机地面开车过程的瞬态响应,用于直升机地面开车过程的工程仿真研究。所建立的分析模型可以模拟旋翼起动过程中,由于旋翼气动力增加导致的机体重心提升及起落架的伸长;可以分析直升机机体姿态及桨叶瞬态响应。以旋翼起动过程中可能出现的桨叶摆振铰失效为例,检验模型模拟旋翼起动过程中各种突发情况的能力。数值分析结果表明:所建立模型可对直升机地面开车过程进行贴近真实的各种动态仿真。Based on Hamilton＇s variation principle, a rotor/ fuselage/landing gears coupled nonlinear aeroelastic dynamic model during rotor starting process on the ground is established so as to simulate the transient responses and use for engineering simu- lation study. The model can be used to simulate both the variations of inertial and aerodynamic forces due to the increase of ro- tor rotation speed and the elongations of landing gears due to the rise of gravity center of helicopter, and calculate the transient responses of the body altitude and the rotor blade. Taking the break of a lag hinge during rotor starting process as an example, the capacities for adapting various sudden situations are examined. Numerical results show that the established model has abili- ty to dynamically simulate the transient responses in various real cases.

关 键 词：直升机 旋翼 气动力弹性 气动力计算 响应分析 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计] V211.47