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微型飞行器在低Reynolds数条件下飞行,机动能力不足且稳定性差。为了解决上述问题,设计了一种翼型可变机翼,通过高效紧凑的曲柄滑块驱动机构带动机翼蒙皮,最终牵动整个机翼变形;然后对常规机翼和翼型可变机翼进行了仿真和风洞对比试验。结果表明:这种翼型可变机翼具有与很多常规固定机翼不同的特性,可使升力有很大提高,能增强微型飞行器的机动性并改善失速特性;而且,通过变形,翼型可变机翼可以在不同迎角下获得最优气动效率。
Micro-aircraft fly under low Reynolds conditions, lack of maneuverability and poor stability. In order to solve the above problems, an airfoil variable wing was designed. The airfoil skin was driven by a highly efficient and compact crank-slider driving mechanism, which ultimately affected the deformation of the whole wing. Then the conventional wing and airfoil variable wing The simulation and wind tunnel comparative tests were carried out. The results show that this airfoil variable wing has the characteristics of many different conventional fixed wings, which can greatly improve the lift force, enhance the maneuverability of the aircraft and improve the stalling characteristics. Moreover, by the deformation, The variable wing can obtain optimal aerodynamic efficiency at different angles of attack.