一种改进的前飞时倾转旋翼机非定常气弹动力学模型  

An improved unsteady aeroelastic model for tiltrotor aircraft in forward flight

作　　者：李治权[1] 夏品奇[1] LI ZhiQuan;XIA PinQi(College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学航空宇航学院,南京210016

出　　处：《中国科学：技术科学》2018年第8期901-907,共7页Scientia Sinica(Technologica)

基　　金：国家自然科学基金(批准号:11572150)资助项目

摘　　要：倾转旋翼机前飞时,旋翼会处于复杂的非定常气动力环境中,但现有的倾转旋翼机前飞气弹稳定性分析模型主要采用准定常片条理论对旋翼的空气动力载荷进行气弹动力学建模,气弹稳定性分析结果与实验值存在明显误差.本文采用ONERA非定常气动力模型进行旋翼气动力建模,并考虑翼型压缩性和失速的影响,建立了倾转旋翼机前飞时的非定常气弹动力学模型.根据NASA试验模型参数,本文计算了系统各模态频率和阻尼比随前飞速度的变化,计算结果相对于现有理论模型更接近试验数据,表明本文建立的非定常气弹动力学模型可以比现有模型更准确地描述倾转旋翼机的前飞气弹稳定性.When the tiltrotor aircraft is in forward flight, the rotor is in complex and unsteady aerodynamic environment. However, the existing aeroelastic stability models for tiltrotor aircraft mainly adopt quasi steady strip theory to calculate the aerodynamic airloads of rotor,which leads a significant error between the calculated and experimental data of aeroelastic stability. In this paper, the unsteady aeroelastic model for tiltrotor aircraft in forward flight has been presented by using the ONERA unsteady aerodynamic model and considering the influence of compressibility and stall effects of airfoil. According to the system parameters of NASA experimental data, the variations of modal frequencies and damping ratios with flight speed were calculated. The calculated results are closer to the experimental data compared with the existing theoretical model, indicating that the unsteady aeroelastic model established in this paper can more accurately describe the aeroelastic stability for tiltrotor aircraft in forward flight than the existing models.

关 键 词：倾转旋翼机 前飞 气弹稳定性 非定常气动力 

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]