基于多体动力学的旋翼模型与气弹稳定性  

Model of rotor aeroelastic stability using dynamics of flexible multbody systems

作　　者：虞志浩[1] 杨卫东[1] 邓景辉[2] 张呈林[1] 

机构地区：[1]南京航空航天大学航空宇航学院直升机旋翼动力学重点实验室,南京210016 [2]中国直升机设计研究所直升机旋翼动力学重点实验室,江西景德镇333001

出　　处：《航空动力学报》2012年第5期1122-1130,共9页Journal of Aerospace Power

基　　金：国家重点基础研究发展计划

摘　　要：针对无轴承等先进旋翼结构特点,建立了基于柔性多体系统动力学方法的旋翼气弹分析模型.旋翼各构件建模相互独立,便于组成不同构型旋翼,适合于新构型旋翼气弹分析.分析模型集成了适合于旋翼气弹分析的隐式大变形桨叶模型,构件动力学方程增加了铰链动力学方程,统一约束方程形式,改进了角运动约束方程,避免连续旋转引起的奇点问题.应用分析模型计算无铰式旋翼和无轴承旋翼的气弹稳定性,分析结构参数对旋翼气弹稳定性的影响.分析结果表明模型能准确计算结构弹性变形的耦合及非线性,提高旋翼气弹稳定性分析精度.Aeroelastic model of rotor was developed using dynamics of flexible multibody systems.The modeling of components of rotor was independent,so different rotor configurations can be modeled and the model was appropriate for new configuration rotor aeroelastic analysis.A large deflection beam model,suitable for aeroelastic analysis of rotor,was incorporated.To simplify the form of constraint equations,dynamic equations of component including a joint were deduced.To avoid singularities for large rotations,the angular constraint equations,expressed by Rodriguez parameters,were modified by introduced a nominal motion.To verify the correctness of the developed method,the aeroelastic analysis of helicopter rotor and influence study of blade structure parameters were implemented.It demonstrates that the method is very useful for improving computation precision of aeroelastic stability.

关 键 词：旋翼 多体系统动力学 气动弹性 稳定性 无轴承旋翼 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]