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首页> 外文期刊>Proceedings of the Institution of Mechanical Engineers >Effects of tilting rate variations on the aerodynamics of the tilting ducted fans mounted at the wing tips of a vertical take-off and landing unmanned aerial vehicle
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Effects of tilting rate variations on the aerodynamics of the tilting ducted fans mounted at the wing tips of a vertical take-off and landing unmanned aerial vehicle

机译：倾斜速率变化对安装在垂直起降无人飞行器机翼尖端的倾斜式管道风扇空气动力学的影响

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摘要

Tilting ducted fans mounted at the wing tips of vertical take-off and landing unmanned aerial vehicles define new applications for these types of aerial vehicles. This new configuration gives vertical take-off and landing unmanned aerial vehicles the ability to hover like helicopters and fly forward like airplanes, which results in using any arbitrary location for take-off and landing combined with increasing range and speed. Furthermore, generating additional lift by using asymmetrical shape for the external body of the ducted fans can lead to reducing the wing area and related overall drag, which results in saving more energy. The transition between cruise mode and hovering can be done by choosing different tilting rates, which can produce instabilities in the aerodynamics of the tilting ducted fans mounted at the wing tips of the vertical take-off and landing unmanned aerial vehicles. This research provides the computational fluid dynamics simulations to investigate these instabilities and compare them for two different ducted fans. Actuator disk model combined with the assumption of constant delivered power to the propeller were used successfully to calculate the induced velocity to the rotor plane of the ducted fan in the computational fluid dynamics simulations. The effects of the flow separation on the aerodynamic coefficients were discussed and compared for both symmetrical and asymmetrical ducted fans in different tilting rates.
机译：安装在垂直起降机翼的机翼尖端的倾斜式管道风扇为这些类型的飞行器定义了新的应用。这种新的配置使垂直起降无人驾驶飞机能够像直升机一样盘旋并像飞机一样向前飞行，从而可以在任意位置进行起降，并增加了航程和速度。此外，通过对风管风扇的外部使用非对称形状来产生额外的升力，可导致机翼面积减小和相关的总阻力，从而节省更多的能量。巡航模式和悬停之间的过渡可以通过选择不同的倾斜率来完成，这可能会导致安装在垂直起降无人机机翼末端的倾斜式管道风扇的空气动力学不稳定。这项研究提供了计算流体动力学仿真，以研究这些不稳定性并针对两个不同的管道风扇进行比较。在计算流体动力学模拟中，成功地使用了致动器盘模型并结合了向螺旋桨恒定传递功率的假设，来计算到风管风机转子平面的感应速度。讨论了流分离对空气动力学系数的影响，并比较了不同倾斜率下对称和不对称导管风机的流动系数。

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