摘要
针对直升机大机动实时飞行仿真的需求,提出了一种新的旋翼动态尾迹模型,并开展了初步的验证研究。该模型采用涡环单元来表示旋翼尾迹涡系,每个涡环具有5个刚体运动自由度和1个半径伸展收缩自由度,可描述大机动飞行中旋翼尾迹的拉伸、压缩、倾斜、弯曲等动态畸变行为,并给出桨盘或空间任意区域的旋翼尾迹瞬态诱导速度分布。以悬停状态旋翼拉力和俯仰角速度阶跃突增为算例,通过与尾迹畸变增广的Pitt-Peters动态入流模型的对比分析,验证了本文模型的正确性和实时性,并得到了一些新的结论。
A new rotor dynamic wake model is presented and verified for helicopter real-time large ma- neuvering flight simulation. Vortex ring elements which have five rigid body motion freedoms and one radius extending-compressing freedom are used to represent the rotor wake vortices. The proposed model can describe the stretch, compression, inclination, bending and other dynamic distortion behaviors of rotor wakes during large maneuvering flight, and give transient induced velocity distribution of rotor wake in the rotor disk or any area of the space. The thrust and pitch angular velocity ramping up conditions of a hovering rotor are chosen to verify the correctness and timeliness of the proposed model by comparison with wake distortion augmented Pitt-Peters dynamic inflow model, and some new conclusions are presented.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2016年第2期212-217,共6页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家自然科学基金(51405227)资助项目
航空科学基金(201410241015541)资助项目
中央高校基本科研业务费专项资金(NS2014011)资助项目
关键词
直升机
旋翼
机动飞行
尾迹
诱导速度
动态入流
helicopter
rotor
maneuvering flight
wake
induced velocity
dynamic inflow
