应用CFD方法的舰载直升机舰面气弹响应计算与分析  

Calculation and Analysis of Shipboard Helicopter Aero-elastic Response Using CFD Method on Ship-deck

作　　者：张冉 徐国华[1] 史勇杰[1] 王清 ZHANG Ran;XU Guohua;SHI Yongjie;WANG Qing(National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;College of Energy and Power Engineering,Lanzhou University of Technology,Lanzhou 730050,China)

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,南京210016 [2]兰州理工大学能源与动力工程学院,兰州730050

出　　处：《航空工程进展》2022年第4期48-56,64,共10页Advances in Aeronautical Science and Engineering

基　　金：国防科技重点实验室基金(JZX7Y201911SY004001)。

摘　　要：舰载直升机所处的环境恶劣,易出现旋翼桨尖过度挥舞及机身碰撞等事故,研究直升机舰面气弹响应可预防此类事故的出现。应用CFD方法获得舰船流场数据,结合桨叶动力学模型,综合提出旋翼气弹响应计算分析方法,研究不同来流速度、悬停位置与风向角下旋翼的气弹响应。结果表明:本文提出的气弹响应计算分析方法正确可行;舰船来流速度的增加会引起桨尖响应最大值的增大,速度从20 m/s变为40 m/s时,响应幅值增加了8.35%;悬停位置主要影响桨尖位移响应沿桨盘方位角的分布;来流风向角的改变会显著影响旋翼气弹响应,桨尖挥舞位移最大值与舰船尾流场的垂向速度分布有关,变化梯度越大桨尖挥舞最大值亦越大。The shipboard helicopter is in a harsh environment,which can cause the accidents of rotor tip over-swing and body collision.The research on the aero-elastic response on the ship surface of the helicopter can prevent such accidents.The computational fluid dynamics(CFD)method is used to obtain the data of ship flow field.Combining with blade dynamic model,a comprehensive calculation and analysis method of rotor aero-elastic response is pro⁃posed,and the aero-elastic response of the rotor under different inflow speed,hovering position and wind direction is studied.The results show that the proposed aero-elastic response calculation and analysis method is correct.The maximum response of rotor tip is increased with the increase of ship inflow speed.When the speed is changed from 20 m/s to 40 m/s,the response amplitude is increased by 8.35%.The hovering position mainly can affect the distri⁃bution of tip displacement response along the azimuth angle of the rotor disc.The change of inflow wind direction angle significantly affects the aeroelastic response of the rotor.The maximum flapping displacement of the blade tip is related to the vertical velocity distribution of the ship's wake flow field.The greater the change gradient is,the greater the maximum flapping of the blade tip is.

关 键 词：舰载直升机 舰船流场 气弹响应 CFD 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程] V271.492