航空学报2025，Vol.46Issue(12)：132-144,13.DOI:10.7527/S1000-6893.2025.31395
适用于飞行力学分析的旋翼涡环状态入流模型
Rotor vortex ring state inflow model suitable for flight mechanics analysis
摘要
Abstract
To meet the application requirements of helicopter special situation simulation,a rotor vortex ring state in-flow model is established for flight mechanics analysis.Based on the turning relationship of the helicopter vertical mo-tion damping in the rotor vortex ring state,the joint tip vortex motion equation and the modified rotor momentum theory equation are solved to obtain the critical damping boundary of the rotor vortex ring state.The climb rates and induced velocities of the rotor entering and exiting the vortex ring state are given.Cubic spline functions are used to establish a rotor vortex ring state induced velocity model,and the dynamic delay time of the rotor vortex ring state induced velocity is derived from the evolution relationship of the concentrated vorticity in the vortex ring state.Thus,a unified critical damping boundary for the rotor vortex ring state and dynamic inflow model are formed.On this basis,the rotor aerody-namic load model and the flight dynamics model of the helicopter vortex ring state are established,and the wind tunnel and flight test data are used to verify the model.The results show that the proposed model can reasonably and accu-rately predict the critical damping boundary of the rotor vortex ring state and the changes of the rotor induced velocity with the helicopter descent rate and forward flight speed.Combined with the rotor aerodynamic load model,the pro-posed model can accurately predict the changes of the rotor tension and increment of torque coefficient with the heli-copter descent rate trend.Comparison with flight test data shows that the proposed model accurately simulates the dy-namic characteristics of helicopter vertical damping in the rotor vortex ring state,and is suitable for flight mechanics analysis applications.关键词
直升机/旋翼/涡环状态/诱导速度/飞行力学Key words
helicopter/rotor/vortex ring state/induced velocity/flight dynamics分类
航空航天引用本文复制引用
文镜涵,吉洪蕾,邓皓轩,王畅..适用于飞行力学分析的旋翼涡环状态入流模型[J].航空学报,2025,46(12):132-144,13.基金项目
国家级项目(FKFB20231108015) （FKFB20231108015）
重庆市自然科学基金(CSTB2022NSCQ-MSX1592) （CSTB2022NSCQ-MSX1592）
中国空气动力研究与发展中心旋翼空气动力学重点实验室研究开放课题(RAL202302-3) （RAL202302-3）
国家自然科学基金(11902052) National Level Project(FKFB20231108015) （11902052）
Natural Science Foundation of Chongqing(CSTB2022NSCQ-MSX1592) （CSTB2022NSCQ-MSX1592）
Open Research Program of Key Laboratory of Rotor Aerodynamics,China Aerodynamics Re-search and Development Center(RAL202302-3) （RAL202302-3）
National Natural Science Foundation of China(11902052) （11902052）
