摘要
通过风洞实验对无尾飞翼布局飞机的本体气动特性和全动翼尖的操纵效能进行了研究。结果表明,此布局飞机是纵向静稳定的,但零升俯仰力矩系数为负值,这对飞机的起降不利。全动翼尖作动时将增加飞机的阻力,降低全机的最大升阻比,产生抬头力矩。全动翼尖单侧作动可在升力基本保持不变的条件下提供偏航力矩,但同时也伴随着较大的滚转力矩和俯仰力矩。此外,全动翼尖的单侧作动和侧力是弱耦合的。全动翼尖同步作动的纵向特性和单侧作动规律相似,但幅度相对要大。
The inherent aerodynamic characteristics and control effectiveness of AMT （All-Moving Tip） of a tailless flying-wing configuration aircraft were investigated in wind tunnel. The results showed that the tested configuration is static stable in longitudinal axis, however, the zero lift pitching moment coefficient is around zero, which is adverse to takeoff and landing. When AMT deflects, the drag coefficient of the aircraft increases, and the nose-up moment increases too, but the maximum lift to drag ratio decreases. The deflection of single AMT could provide considerable yaw control moment almost without variation of lift coefficient, and cause relative large rolling and pitching moments. Furthermore, it is obtained that the coupling between deflection of single AMT and side force is weak. The effects of both AMTs simultaneous deflection and single AMT deflection on longitudinal aerodynamic characteristics are similar, but the impact of AMTs simultaneous deflection is stronger.
出处
《空气动力学学报》
EI
CSCD
北大核心
2010年第2期132-137,共6页
Acta Aerodynamica Sinica
关键词
飞翼布局
全动翼尖
操稳
偏航
flying-wing configuration
AMT
handling and stability
yaw
