低雷诺数下超微型复合材料旋翼流固耦合分析研究  

Fluid-structure interaction investigation on composite nano rotor at low Reynolds number

作　　者：刘振[1] 杨东[1] 卜宸 LIU Zhen;YANG Dong;BU Chen(State Key Laboratory for Strength and Vibration of Mechanical Structures,Shaanxi Key Laboratory of Environment and Control for Flight Vehicle,School of Aerospace,Xi′an Jiaotong University,Xi′an 710049,China)

机构地区：[1]西安交通大学航天航空学院机械结构强度与振动国家重点实验室,陕西省先进飞行器服役环境与控制重点实验室,陕西西安710049

出　　处：《振动工程学报》2018年第2期283-290,共8页Journal of Vibration Engineering

基　　金：国家自然科学基金资助项目(11302164);高等学校博士学科点专项科研基金资助项目(20130201120031)

摘　　要：复合材料轻薄旋翼在气动力的作用下发生结构变形和振动是造成旋翼推进性能改变和破坏的重要原因之一。针对超微型复合材料旋翼,搭建了基于非接触式超微型旋翼模态试验测量平台,研究了旋翼结构固有特性,建立了旋翼铺层复合材料的有限元模型,并用实验模态数据验证了有限元模型的准确性。搭建了可测量微小力和扭矩的超微型旋翼推进性能试验平台,获得了超微型旋翼的推进特性。结合基于多块结构化网格、多参考坐标系运动域方法以及两方程湍流模型的流体求解器和基于有限元方法结构动响应求解器,开展了超微型旋翼流固耦合研究,分析了柔性旋翼的响应和推进特性,并同实验数据进行了对比,结果发现耦合计算中旋翼结构呈现以2阶模态振型为主的上拍现象,耦合计算得到的旋翼推力和扭矩相比实验值误差仅为7%,而非耦合状态计算误差可达11%,且耦合计算时旋翼结构系统稳定,未发生颤振现象。研究表明了采用流固耦合方法研究旋翼气动和结构性能的必要性。The composite light-weight nano rotor suffers aerodynamic forces,which induces deformation and vibration resulting in the change of rotor performance and structure failure.A non-contact modal experimental platform is established and the finite element model of the nano rotor based on laminated composite is generated.The dynamic characteristics of the nano rotor are studied experimentally and numerically.The first five modes and natural frequencies are obtained and the finite element model is validated.A static performance test bench is established with small-capacity force and torque sensor for the nano rotor and the propulsive performance of nano rotor is measured.A fluid solver is established based on multi-block structured grids,multi-reference frame method and two-equation turbulence model.With a finite-element structure solver,a fluid-structure solver is established based on radial basis function method for data transfer at the interface.The fluid-structure interaction analysis is then carried out and the dynamic response and propulsive performance of the nano rotor are obtained and compared with experiment results.It can be found that the fluid-structure interaction solver predicts a more accurate result(relatively 7%error)than the only fluid solver(relatively 11%error).In addition,no flutter is observed which shows that the structure system is stable.It is evidenced that the fluid-structure interaction method is necessary to study the aerodynamic performance and structural dynamic characteristics of the composite nano rotor.

关 键 词：超微型旋翼 气动力特性 流固耦合 复合材料 

分 类 号：V224[航空宇航科学与技术—飞行器设计] V258[一般工业技术—材料科学与工程]