连续变弯度后缘飞机的滚转机动载荷减缓

Rolling maneuver load alleviation of aircraft with continuously variable-camber trailing edge

变弯度后缘机翼具有变形连续、阻力较小、气动噪声较低等优势,越来越多地应用于新概念飞行器的设计之中。基于此,提出一种基于变弯度后缘的飞行器刚弹耦合动力学建模方法,并针对变弯度后缘飞机缩比模型开展了滚转机动仿真分析与风洞试验。结果表明:变弯度后缘可以操纵飞机在2 s内进行180°滚转机动。相较于外侧后缘单独变形,通过内外后缘协同变形可以降低30%以上的滚转机动附加载荷。另外,对比表明滚转角仿真结果与风洞试验数据误差小于6%,验证了所提方法的准确性。

The variable-camber trailing edge is frequently used in new concept aircraft design because of its advantages of continuous deformation,less resistance,and low aerodynamic noise.A rigid-elastic coupling dynamics modeling method based on the variable-camber trailing edge was proposed,and rolling maneuver simulation analysis and wind tunnel test were carried out using a scale model of aircraft with the variable-camber trailing edge.The results show that the variable-camber trailing edge can maneuver the aircraft to roll 180°within 2 s.Additional rolling maneuver load can be reduced by more than 30%through cooperative inner and outer trailing edge deformation compared to outer trailing edge deformation alone.In addition,a comparative study shows that the error between rolling maneuver simulation results and wind tunnel test data is less than 6%,which confirms the accuracy of the established theoretical model.