直升机旋翼前飞状态下的气动弹性分析  

Aeroelastic Analysis of Helicopter Main Rotor in Forward Flight

作　　者：余智豪 虞志浩[1] 李赟 杨卫东[1] YU Zhi-hao;YU Zhi-hao;LI Yun;YANG Wei-dong(National Key Laboratory of Rotorcraft Aeromechanics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学直升机旋翼动力学国防科技重点实验室,南京210016

出　　处：《科学技术与工程》2018年第11期332-336,共5页Science Technology and Engineering

基　　金：航空科学基金(20155752054);青年科技创新基金(NS2016013);南京航空航天大学开放基金(kfjj20160109)资助

摘　　要：建立一种旋翼前飞状态下的旋翼气动弹性分析模型,模型中采用松耦合方法集成高精度计算流体力学(CFD)气动模型。采用Green应变以及几何精确的弹性运动及变形的几何关系式;并通过Hamilton建立旋翼动力学方程。采用基于N-S控制方程的CFD气动模型,采用滑移网格技术实现桨叶运动。通过计算SA349/2直升机前飞状态下的挥舞、摆振振动载荷,对比试验数据,验证建立的气动弹性分析模型。结果表明,集成CFD的气弹模型能有效提高振动载荷预估精度,对于高阶谐波载荷的计算有很大的提高。A rotor aeroelastic analysis model for rotor forward flight was established,the high-accuracy computational fluid dynamics(CFD)model was integrated by using the loose coupling method.The rotor dynamic model was built by the geometrically exact beam model and the Hamilton principle.The CFD model was based on N-S equation and the rotor model in CFD was built with multiple mesh motion.The flight test data of SA349/2 helicopter were used to validate this method by comparison calculation with the flap bending moment and the edge bending moment,the improvement of the prediction accuracy of the rotor vibration loads was effectively demonstrated and the effectiveness of prediction analysis of the rotor higher order harmonic vibratory loads are validated.

关 键 词：旋翼 气动弹性 几何精确 N-S方程 耦合 

分 类 号：V221.47[航空宇航科学与技术—飞行器设计]