Comprehensive study on yaw control characteristic of combined control surfaces of flying wing configuration

被引：0
|
作者：
Zhou Z. [1 ]
Yu Y. [1 ]
Liu G. [1 ]
Chen Z. [1 ]
He K. [1 ]
机构：
[1] China Aerodynamics Research and Development Center, Mianyang
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2020年 / 41卷 / 06期
关键词：
Aileron; CFD method; Flying wing; Model flight test; Spoiler drag rudder; Subsonic velocity; Wind tunnel test; Yaw control;
D O I：
10.7527/S1000-6893.2019.23422
中图分类号：
学科分类号：
摘要：
Searching for effective and practical yaw control measures has always been a difficult point in the design of flying-wing aircraft. This paper presents a yaw control method of combined rudder consisting of a spoiler drag rudder on the upper surface of the outer wing and its corresponding trailing aileron. The yaw control characteristics of single component and combined rudder at low and subsonic speeds are studied comprehensively by three means of CFD, wind tunnel test, and model flight test. Research results show that the yaw control ability of the single drag rudder is relatively strong, but its coupling with the longitudinal and lateral moments is severe, and needs to be combined with other rudders. It is suggested that the aileron should not be used alone as a yaw control measure because of its weak yaw control capability and serious coupling with longitudinal and lateral moments. The combined rudder has strong yaw control ability. Selecting the scheme of combined rudder with the difference of rudder deviation between drag rudder and aileron in the range of 0°-5° can greatly reduce the coupling degree of longitudinal and lateral moments and realize the decoupling design of control rudder. Whether single component or combined rudder, the moment regularity of the rudder deviation angle in the range of 0°-6° is poor, and it is suggested to avoid this angle area by presetting the rudder deviation angle. © 2020, Press of Chinese Journal of Aeronautics. All right reserved.
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