This paper investigates the impacts that vibratory-based actuation mechanisms can have on power consumption for a flapping-wing micro air vehicle. The flapping-wing is characterized by a lumped-parameter single degree of freedom system. Equations of motion are developed which are solved to obtain the flapping angle and lift response of the flapping-wing system. Linear and nonlinear vibratory actuation mechanisms are considered to determine their effects on the power consumption of the flapping-wing drone. Actuation mechanism parameters are varied to enhance and optimize the system’s performance. The results show that the resonance phenomenon can be utilized to minimize the power consumption depending on the system’s parameters. Linear damping is found to be a very critical parameter that is necessary to minimize when designing the system. It is demonstrated that higher transmission ratios are effective at reducing the necessary forcing input, which reduces the input power needed for hovering flight. The results also indicate that the nonlinear softening behavior can be beneficial in further reducing the required power by reducing the necessary input force and excitation frequency. An optimal configuration of actuation mechanism parameters is presented.

本文研究了基于振动的驱动机制对扑翼微型飞行器功耗的影响。扑翼的特点是集总参数单自由度系统。开发了运动方程，求解该方程以获得扑翼系统的扑翼角和升力响应。线性和非线性振动驱动机制被认为是确定它们对扑翼无人机功耗的影响。致动机构参数被改变以增强和优化系统的性能。结果表明，根据系统参数，可以利用谐振现象来最小化功耗。发现线性阻尼是一个非常关键的参数，在设计系统时需要将其最小化。结果表明，更高的传动比可有效减少必要的强制输入，从而降低悬停飞行所需的输入功率。结果还表明，非线性软化行为可以通过降低必要的输入力和激励频率来进一步降低所需的功率。提出了致动机构参数的最佳配置。