为提升无尾飞翼布局飞机航向控制能力，以典型飞翼布局飞机模型为研究对象设计了翼尖可绕弦线方向偏转结构。基于FL-14风洞单自由度动态试验系统开展了静态和动导数试验，研究了飞翼布局飞机基本气动特性及翼尖偏转对全机气动特性的影响。结果表明：无尾飞翼布局飞机航向呈静不稳定，航向动稳定性极弱，航向增稳设计及控制很有必要；翼尖偏转有助于增强飞机的航向静、动稳定性，并很好地解决了传统阻力类舵面航向增稳时导致全机升阻比下降气动效率降低的问题；翼尖偏转能够有效改善飞翼布局飞机恶化的荷兰滚模态使之趋近于常规布局飞机模态，这有利于简化飞机横航向控制律设计方法。弯折翼尖结构具有舵面少、效率高的特点，是航向增稳的有效手段，具有应用价值。
To improve the directional control ability of the flying-wing configuration aircraft, we design a wing tip structure which can be deflected around the direction of the wing chord based on a typical flying-wing configuration model. The static force measurement and a dynamic derivative test are conducted on the dynamic test system of the FL-14 wind tunnel. The basic aerodynamic characteristics of the flying-wing configuration aircraft and the effect of wing tip deflection on the whole aircraft are studied. The results show the static instability and extremely weak dynamic stability of the tailless flying-wing configuration aircraft in the flying direction, thereby necessitating the improvement of directional stability in both design and control of the flying-wing aircraft. The wing tip deflection is helpful to enhance the directional static and dynamic stability, and can well solve the problem of aerodynamic efficiency reduction when the traditional drag rudder is used to increase the directional stability. In addition, the wing tip deflection can also improve the deteriorated Dutch roll mode of the flying-wing configuration aircraft, bringing it closer to the conventional configuration aircraft mode that will simplify the design method of directional control law. Highly efficient with fewer rudders, the bendable wing tip is an efficient method for directional stability enhancement with high application value.
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