This study introduces a new quasi-flapping wing driving mechanism based on a half-rotating mechanism which is capable of pure rotational flapping rather than the more traditional oscillatory flapping method. Lift models for half-rotating wing (HRW) aircraft in hovering flight are proposed based on the kinematics of a HRW prototype and the flow characteristics near the surface of its wing. Alongside further analytical expressions for lift based on kinematic extractions, computational models and a novel lift validation mechanism are used to reinforce the aerodynamic characteristics of the HRW in hovering flight. The aerodynamics of the HRW are experimentally assessed for different wing layouts and wing materials. Results indicate that the flow field generated by the motion of the wing arranged symmetrically on both sides of the body interfere with each other, causing the average lift coefficient of the paired-wing HRW to be less than that of the single-wing HRW. The average lift coefficient of the flexible wing is larger than that of the rigid wing. In addition, the average lift of the flexible wing increases with increasing flexural compliance within a particular range. Lift forces in different flight conditions are calculated using derived formulas alongside representative computational models, through which the derivation of lift variation for the HRW in hovering flight is validated. The theoretical lift curves show reasonable agreement with numerical simulation results in terms of the time course over one stroke cycle. The mechanisms of the HRW for generation and shedding of vortices in hovering flight are further revealed in computed flow field characteristics results. The velocity vectors of the flow field between the HRW and the symmetrically rotating wing indicate that the HRW with asymmetric rotation can generate lift force effectively. The velocity difference between the wing and the fluid is the key factor influencing the structure of generated vortices. In detailed three-dimensional (3D) vortex flows, our computational fluid dynamics study shows that a horseshoe-shaped vortex is first generated in the early downstroke. The horseshoe-shaped vortex subsequently grows into a doughnut-shaped vortex ring, with a jet stream appearing in its core which forms the downwash. The doughnut-shaped vortex ring eventually elongates into a long arc-shaped wake vortex ring. A large increasing lift force is generated during the upstroke, most likely due to the stable distal attached vortices; and in accordance with this, downwash becomes evident in the vortex ring during the downstroke.

本研究介绍了一种基于半旋转机构的新型准襟翼机翼驱动机构，该机构能够进行纯正的旋转襟翼，而不是传统的振荡襟翼方法。基于HRW原型机的运动学及其机翼表面附近的流动特性，提出了一种用于悬停飞行的半旋翼飞机的升力模型。除了基于运动学提取的升力的进一步分析表达式外，还使用了计算模型和新颖的升力验证机制来增强HRW在悬停飞行中的空气动力学特性。针对不同的机翼布局和机翼材料，对HRW的空气动力学特性进行了实验评估。结果表明，对称分布在机体两侧的机翼运动产生的流场相互干扰，导致成对机翼HRW的平均升力系数小于单机翼HRW的升力系数。柔性机翼的平均升力系数大于刚性机翼的平均升力系数。另外，在特定范围内，挠性机翼的平均升力随着挠性的增加而增加。使用派生的公式以及代表性的计算模型来计算不同飞行条件下的升力，从而验证悬停飞行中HRW的升力变化的推导。理论上的升程曲线在一个冲程周期内的时间过程方面与数值模拟结果显示出合理的一致性。在计算的流场特征结果中进一步揭示了HRW在盘旋飞行中产生和消除涡流的机理。HRW与对称旋转机翼之间流场的速度矢量表明，非对称旋转的HRW可以有效地产生升力。机翼与流体之间的速度差是影响所产生旋涡结构的关键因素。在详细的三维（3D）涡流中，我们的计算流体动力学研究表明，在向下的早期冲程中首先产生了马蹄形的涡流。马蹄形的涡流随后长成甜甜圈形的涡流环，其核心处出现射流，形成下冲。环形的涡流环最终伸长为长弧形的尾流涡流环。在上冲程过程中会产生很大的升力，这很可能是由于远端附着的涡流稳定所致。因此，在向下冲程期间，涡流环中的向下冲洗变得明显。