机翼刚心位置对回转颤振稳定性边界的影响分析  

The effect of the stiffness position of wing on the stability boundary of whirl flutter

作　　者：查建平[1] 张树桢[1] 董凌华[2] ZHA Jianping;ZHANG Shuzhen;DONG Linghua(China Helicopter Research and Development Institute,333000 Jingdezhen,China;Nanjing University of Aeronautics and Astronautics,210016 Nanjing,China)

机构地区：[1]中国直升机设计研究所,景德镇333000 [2]南京航空航天大学,南京210016

出　　处：《应用力学学报》2023年第5期987-993,共7页Chinese Journal of Applied Mechanics

基　　金：新一代民机技术研究专题资助项目(No.MJZ5-2N2X)。

摘　　要：基于哈密顿原理,建立了适合快速开展回转稳定性设计参数评估的倾转旋翼/短舱/机翼多体气弹耦合动力学分析模型,并通过参数影响分析,获得机翼刚心位置前移有利于提高倾转旋翼机回转颤振稳定性边界的重要结论。所建立的分析方法和获得的结论,对工程设计具有重要的指导意义,可以在机翼气动外形约束条件下,通过调整机翼内部结构特性,合理将机翼的刚心位置向机翼前缘移动,达到提高该构型飞行器回转颤振稳定性裕度的目的。Basing on the Hamilton s principle,a dynamic model of rotor/nacelle/wing coupling system was established with the purpose of engineering design assessment of whirl flutter instability characteristics for tilt-rotor aircraft.The influence analysis of the wing stiffness center on the stability boundary of whirl flutter indicated that putting the wing stiffness center forward to the leading edge will contribute to increasing the boundary of whirl flutter.The analysis results show that the stability boundary can be effectively improved by adjusting the wing stiffness center through structural design,which can be used to guide the engineering design.

关 键 词：气动弹性 稳定性 倾转旋翼 回转颤振 刚心 

分 类 号：V261.2[航空宇航科学与技术—航空宇航制造工程]