Blade Element Momentum Modeling of Low-Re Small UAS Electric Propulsion Systems
Blade Element Momentum Modeling of Low-Re Small UAS Electric Propulsion Systems
复制标题
低分辨率小型无人机电力推进系统的叶片元件动量建模
DOI：
10.2514/6.2015-3296
复制
发表时间：
2015
期刊：
影响因子：
--
通讯作者：
J. Gregory
中科院分区：
文献类型：
--
作者：
M. McCrink;J. Gregory
建立了小型电动无人机推进系统的模型。该模型基于桨叶单元动量（BEM）模型，并对叶尖损失、马赫效应、三维流分量和雷诺标度进行了修正。特别的重点放在尺度效应的估计，而不是通常遇到的规模应用边界元建模方法。对几种具有代表性的商用螺旋桨的几何形状进行了性能预测。然后将这些预测结果与螺旋桨性能的实验风洞测量结果进行比较。实验数据支持所提出的边界元模型的预测，并指出尺度效应对预测系统整体性能的重要性。
A model for the propulsion system of a small-scale electric Unmanned Aircraft System (UAS) is presented. This model is based on a Blade Element Momentum (BEM) model of the propeller, with corrections for tip losses, Mach effects, three-dimensional flow components, and Reynolds scaling. Particular focus is placed on the estimation of scale effects not commonly encountered in the full-scale application of the BEM modeling method. Performance predictions are presented for geometries representative of several commercially available propellers. These predictions are then compared to experimental wind tunnel measurements of the propellers’ performance. The experimental data supports the predictions of the proposed BEM model and points to the importance of scale effects on prediction of the overall system performance.