Helicopter rotor blade multiple-section optimization with performance

Luke D. Allen, Joon W. Lim, R. Haehnel, I. Dettwiller
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引用次数: 1

Abstract

This paper presents advancements in a surrogate-based, rotor blade design optimization framework for improved helicopter performance. The framework builds on previous successes by allowing multiple airfoil sections to designed simultaneously to minimize required rotor power in multiple flight conditions. Rotor power in hover and forward flight, at advance ratio 𝜇 = 0.3, are used as objective functions in a multi-objective genetic algorithm. The framework is constructed using Galaxy Simulation Builder with optimization provided through integration with Dakota. Three independent airfoil sections are morphed using ParFoil and aerodynamic coefficients for the updated airfoil shapes (i.e., lift, drag, moment) are calculated using linear interpolation from a database generated using C81Gen/ARC2D. Final rotor performance is then calculated using RCAS. Several demonstrative optimization case studies were conducted using the UH-60A main rotor. The degrees of freedom for this case are limited to the airfoil camber, camber crest position, thickness, and thickness crest position for each of the sections. The results of the three-segment case study show improvements in rotor power of 4.3% and 0.8% in forward flight and hover, respectively. This configuration also yields greater reductions in rotor power for high advance ratios, e.g., 6.0% reduction at 𝜇 = 0.35, and 8.8% reduction at 𝜇 = 0.4.
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直升机旋翼叶片多截面性能优化
本文介绍了一种基于代理的旋翼叶片设计优化框架的进展,以提高直升机的性能。该框架建立在以前的成功,允许多个翼型部分同时设计,以尽量减少在多种飞行条件下所需的旋翼功率。在多目标遗传算法中,以前进比为≥0.3的悬停和前飞旋翼功率为目标函数。该框架使用Galaxy Simulation Builder构建,并通过与Dakota集成提供优化。三个独立的翼型部分变形使用ParFoil和空气动力学系数更新的翼型形状(即升力,阻力,力矩)是使用线性插值从使用C81Gen/ARC2D生成的数据库计算。然后使用RCAS计算最终转子性能。使用UH-60A主旋翼进行了几个示范性优化案例研究。这种情况下的自由度是有限的翼型弧度,弧度波峰位置,厚度,厚度波峰位置为每一节。三段式案例研究结果表明,前飞和悬停时,旋翼功率分别提高4.3%和0.8%。这种配置也产生更大的减少转子功率为高超前比,例如,在 = 0.35时减少6.0%,在 = 0.4时减少8.8%。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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