Hovering ability forms the basis for space operations of Micro Aerial Vehicles (MAVs). The problem of uneven load puts high demands on the wing design. In this paper, a new hovering-mode for MAVs, inspired by flapping flight in bees and hummingbirds but using high-aspect-ratio and low-stress wings, is proposed. Different from the flapping actuations that occur at the wing roots, the two wings are driven back and forth in a straight line. To simplify the design and control the angle of attack, passive wing rotation is employed. The numerical results and analysis show that the maximum stress of the oscillating wing is approximately 1/6 of that of the flapping wing when the lift of the oscillating wing is twice that of the flapping wing. A theoretical aerodynamic model of the kinematics of the vehicle’s driving mechanism was developed to fulfill its design. Force measurements indicate that the vehicle generates a sufficiently high cycle-averaged vertical thrust (71 g) for liftoff at a maximum frequency of 5.56 Hz, thereby validating the proposed aerodynamic model. Moreover, liftoff performance is presented to visually demonstrate the vertical take-off capabilities and hovering potential of the aeromechanical solution.

悬停能力构成了微型飞行器（MAV）空间操作的基础。载荷不均的问题对机翼设计提出了很高的要求。在本文中，受蜜蜂和蜂鸟扑翼飞行的启发，提出了一种新的微型飞行器悬停模式，但使用了高纵横比和低应力的翅膀。与发生在机翼根部的扑动驱动不同，两个机翼在一条直线上来回驱动。为了简化设计和控制攻角，采用被动翼旋转。数值结果和分析表明，当摆翼升力为扑翼升力的2倍时，摆翼的最大应力约为扑翼升力的1/6。开发了车辆驱动机构运动学的理论空气动力学模型以实现其设计。力测量表明，该飞行器在最大频率为 5.56 Hz 时产生足够高的循环平均垂直推力 (71 g) 以进行升空，从而验证了所提出的空气动力学模型。此外，还提供了起飞性能，以直观地展示航空机械解决方案的垂直起飞能力和悬停潜力。