飞翼布局组合舵面航向控制特性综合研究  

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

作　　者：周铸[1] 余永刚[1] 刘刚[1] 陈作斌[1] 何开锋[1] ZHOU Zhu;YU Yonggang;LIU Gang;CHEN Zuobin;HE Kaifeng(China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心,绵阳621000

出　　处：《航空学报》2020年第6期164-178,共15页Acta Aeronautica et Astronautica Sinica

摘　　要：寻求高效实用的航向控制措施一直是飞翼布局飞行器设计的难点。提出了一种由外翼上翼面嵌入式阻力舵和其相对应的后缘副翼组成的组合舵航向控制措施,通过CFD方法、风洞试验和模型飞行试验3种研究手段,综合研究了单独部件和组合舵在低速、亚声速时的航向控制特性。结果表明:单独阻力舵的航向控制能力比较强,但与纵横向力矩耦合严重,需与其他舵组合使用;单独副翼的航向控制能力很弱,且与纵横向力矩耦合非常严重,建议不单独作为航向控制措施使用;组合舵的航向控制能力强,选取阻力舵与副翼的舵偏角角度差在0°~5°范围的组合舵方案,可以大幅度削弱与纵横向的力矩耦合程度,实现操纵舵面解耦设计;无论单独部件,还是组合舵,舵偏角为0°~6°范围的力矩变化规律较差,建议通过预置舵偏角等方式避开此角度区域。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.

关 键 词：飞翼 嵌入式阻力舵 副翼 航向控制 亚声速 CFD方法 风洞试验 模型飞行试验 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]