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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
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
关键词
旋翼
多体系统动力学
气动弹性
稳定性
无轴承旋翼
rotor
dynamics of multibody systems
aeroelasticity
stability
bearingless rotor
