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首页> 外文会议>AHS Specialists Conference on Aeromechanics Design for Transformative Vertical Flight >Vacuum Chamber Testing of 1.5 Foot Diameter Mars Rotor
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Vacuum Chamber Testing of 1.5 Foot Diameter Mars Rotor

机译：真空室测试1.5英尺直径火星转子

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摘要

This paper describes the design of a Mars rotor test stand in a vacuum chamber and presents initial performance results at Martian conditions. The 1.5 foot diamter rotor with a hingeless hub and swashplate pitch control, with tip Reynolds number (Re) 3,000 to 10,000, and Mach number (Ma) 0.1 to 0.25 is considered for initial testing. Initial hover performance testing of the rotor and preliminary Blade Element Momentum Theory (BEMT) analysis are compared. The figure of merit was used as the metric for rotor hover performance and was obtained using a six axis force and moment transducer, which captured all hub forces and moments. Tests from Re = 3,000 to 10,000, with collective sweeps from -10° to 40°, show the trend of decreasing maximum figure of merit with decreasing Reynolds number. The Reynolds number corrected BEMT analysis showed promising correlation to experimental data, but continues to need improvement, through the development of more accurate low Reynolds number airfoil characteristics. The model Mars rotor will be used for continued testing of rotor performance and aeromechanics, in the form of blade pitching moment and hub forces and moments, for a variety of blade designs.
机译：本文介绍了在真空室中的火星转子试验台的设计，并在火星条件下提出初始性能结果。对于尖端雷诺数（RE）3,000至10,000，具有尖端雷诺数（RE）3,000至10,000，以及Mach数（MA）0.1至0.25，有1.5英尺的直径控制器被认为是用于初始测试。比较了转子的初始悬停性能测试和初步叶片元件动量理论（BEMT）分析。优选法用作转子悬停性能的度量，并使用六个轴力和力矩换能器获得，该力换能器捕获了所有轮毂力和时刻。从RE = 3,000到10,000的测试，集体扫描从-10°到40°，显示出减少最大数量的雷诺数目的趋势。雷诺数校正BEMT分析显示出与实验数据相关的相关性，但继续需要改进，通过开发更精确的低雷诺数翼型特性。模型火星转子将用于转子性能和航空力学的持续测试，以刀片抛光矩和枢纽力和时刻，适用于各种刀片设计。

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