Implementation of a Flapping Wing Micro Air Vehicle Control Technique
Implementation of a Flapping Wing Micro Air Vehicle Control Technique
复制标题
扑翼微型飞行器控制技术的实现
DOI：
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发表时间：
2014
期刊：
影响因子：
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通讯作者：
R. Cobb
中科院分区：
文献类型：
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作者：
M. L. Anderson;R. Cobb
随着对非定常、低雷诺数空气动力学、微加工和流固耦合的研究不断深入，扑翼微型飞行器仍是一个不断发展的领域。然而，对这种微型飞行器的扑翼控制的研究仍然滞后。现有的研究一致地包括建议的控制律，通过准定常叶素公式的计算机模拟验证。这种模拟使用了许多假设，不能完全描述流动物理。相反，这种控制律必须在硬件上验证。在早期的工作中，提出了一种新的控制技术，双谐波振幅和偏置调制，并与这些相同的准稳态叶素公式进行了分析。在这项工作中，双谐波振幅和偏置调制控制技术的扑翼原型（4厘米翼长）和测试上的六分量力/力矩传感器。实验证明，该样机能够产生近似解耦的力和力矩。
Flapping wing micro air vehicles continue to be a growing field, with ongoing research into unsteady, low Reynolds number aerodynamics, microfabrication, and fluid–structure interaction. However, research into flapping wing control of such micro air vehicles continues to lag. Existing research uniformly consists of proposed control laws that are validated by computer simulations of quasi-steady blade-element formulas. Such simulations use numerous assumptions and cannot be trusted to fully describe the flow physics. Instead, such control laws must be validated on hardware. In earlier work, a novel control technique, biharmonic amplitude and bias modulation, was proposed and analyzed with these same quasi-steady blade-element formulas. In this work, the biharmonic amplitude and bias modulation control technique was implemented on a flapping wing prototype (4 cm wing length) and tested on a six-component force/torque sensor. Experiments verified that the prototype can generate nearly uncoupled forces and mo...