An Unsteady Rotor Aerodynamics Analytical Model of Hybrid Compound High-speed Helicopter

被引：0
|
作者：
Yin, Xinfan [1 ,2 ]
Ma, Hongxu [1 ]
An, Honglei [1 ]
Wei, Qing [1 ]
Wang, Liangquan [3 ]
Nie, Bowen [2 ]
机构：
[1] Natl Univ Def Technol, Coll Intelligence Sci & Technol, Changsha, Peoples R China
[2] China Aerodynam Res & Dev Ctr, Low Speed Aerodynam Inst, Mianyang, Sichuan, Peoples R China
[3] China Aerodynam Res & Dev Ctr, Key Lab Rotor Aerodynam, Mianyang, Sichuan, Peoples R China
来源：
2023 5TH INTERNATIONAL CONFERENCE ON CONTROL AND ROBOTICS, ICCR | 2023年
关键词：
hybrid compound high-speed helicopter; rotor aerodynamics; blade element theory; modeling; wind tunnel test;
D O I：
10.1109/ICCR60000.2023.10444885
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
In response to the complex nonlinear aerodynamic characteristics of the hybrid compound high-speed helicopter, the vector method is used to derive the relative airflow velocity of the blade element, and an unsteady rotor aerodynamics analytical model of the hybrid compound high-speed helicopter is established based on the blade element theory. Based on the established unsteady rotor aerodynamics mathematical model, numerical simulation is conducted in SIMULINK. In addition, the wind tunnel test is carried out in the FL-13 wind tunnel of the China Aerodynamics Research and Development Center by using the helicopter wind tunnel test rig. The experimental results show that the numerical simulation results of the unsteady rotor aerodynamics model are in good agreement with the wind tunnel test results, with high confidence and reliability, and can be used to guide the design of control strategies and the verification of control laws.
引用
收藏
页码：11 / 16
页数：6
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