分布式推进旋翼飞行器回转颤振特性研究  

Research on Whirl-Flutter Characteristics of Distributed Propulsive Rotorcraft

作　　者：程毅 余智豪 王司文 赵金瑞 CHENG Yi;YU Zhihao;WANG Siwen;ZHAO Jinrui(China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所,景德镇333001

出　　处：《南京航空航天大学学报(自然科学版)》2025年第2期243-251,共9页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：直升机动力学全国重点实验室基金(2023-HA-LB-067-08)。

摘　　要：针对高速前飞状态分布式推进旋翼飞行器存在的回转颤振动力学问题,提出了一种通用性强且快速高效分布式多旋翼/倾转机翼耦合气弹动力学分析方法。该方法基于中等变形梁理论,考虑旋翼和机翼间弹性、惯性耦合,采用基于CFD修正的片条理论,建立分布式多旋翼/倾转机翼气弹动力学分析模型,研究其前飞状态下的回转颤振特性。在证明了分析方法的准确性后,同时研究了耦合系统动力学参数(机翼、短舱和旋翼等)对飞行器回转颤振临界速度的影响。结果表明:系统先发生扭转失稳,后发生面内弯曲失稳,机翼扭矩刚度对系统临界颤振速度影响程度最大;其次是面外和面内弯曲刚度,其颤振运动的三维效应十分明显,呈现为机翼扭转和面内外弯曲模态耦合。在低速状态下将升力桨张开并提高旋翼数量能有效增加系统气弹稳定性,无铰式桨叶挥舞刚度对系统临界颤振影响不大,增大旋翼拉力和降低旋翼转速有利于提高系统临界颤振速度,而增加旋翼和短舱高度则会降低系统临界颤振速度。Aiming at the problem of whirl-flutter dynamics of distributed propulsion rotorcraft in high-speed forward flight state,this paper proposes a highly versatile,fast and efficient distributed multi-rotor/tilt-wing coupled aeroelastic dynamics analysis method.Based on the theory of moderately deformed beams,this method takes into account the elastic and inertial coupling between the rotors and the wings.By using the strip theory corrected by CFD,a distributed multi-rotor/tilt-wing aeroelastic dynamics analysis model is established to study its whirl-flutter characteristics in the forward flight state.After proving the accuracy of the analysis method,this paper also studies the influence of the dynamic parameters of the coupled system(such as the wings,nacelles and rotors,etc.)on the critical whirl-flutter speed of the aircraft.The results show that the system first experiences torsional instability and then in-plane bending instability.The torsional stiffness of the wings has the greatest influence on the critical flutter speed of the system,followed by the out-of-plane and inplane bending stiffness.The three-dimensional effect of the flutter motion is obvious,presenting as the coupling of the torsional and in-plane and out-of-plane bending modes of the wings.Opening the lift rotors and increasing the number of rotors at low speeds can effectively increase the aeroelastic stability of the system.The flapping stiffness of the hinge-less blades has little influence on the critical flutter of the system.Increasing the rotor thrust and reducing the rotor speed are beneficial to increasing the critical flutter speed of the system,while increasing the height of the rotors and nacelles will reduce the critical flutter speed of the system.

关 键 词：分布式推进 倾转机翼 气弹动特性 大展弦比 回转颤振 

分 类 号：V214.11[航空宇航科学与技术—航空宇航推进理论与工程]