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首页> 外文期刊>Journal of the American Helicopter Society >Trailing-Edge Flaps for Rotor Performance Enhancement and Vibration Reduction
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Trailing-Edge Flaps for Rotor Performance Enhancement and Vibration Reduction

机译：后缘襟翼可增强转子性能并减少振动

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摘要

The comprehensive analysis University of Maryland Advanced Rotor Code (UMARC) was used to quantify the capabilities of trailing-edge flaps (TEFs) for helicopter vibration reduction and performance improvement. The rotor performance in hover was improved with a combination of torsionally softer blades and positive TEF deflections. Suitable combinations of lower harmonic TEF inputs were shown capable of reducing the rotor power requirement by about 4-5% at an advance ratio of μ = 0.4. The TEF was shown to be capable of suppressing vibratory loads at a range of forward speeds, using half peak-to-peak deflections of about 5°-10°. Softening the blades in torsion resulted in larger flap actuation requirements for vibration reduction. A combination of 1, 2, 3, 4, and 5/rev TEF inputs resulted in a power reduction of 1.5%, while also reducing certain vibratory loads by more than 50% in high-speed forward flight.
机译：经过全面分析的马里兰大学高级旋翼代码（UMARC）用于量化后缘襟翼（TEF）的能力，以减少直升机的振动并提高性能。结合使用更软的叶片和正的TEF挠度，可以提高悬停时的转子性能。示出了低谐波TEF输入的合适组合，该组合能够以μ= 0.4的提前比将转子功率需求降低约4-5％。事实证明，TEF使用大约5°-10°的半峰至峰挠度，可以在一定范围的前进速度下抑制振动载荷。扭转软化叶片导致更大的襟翼驱动要求以减少振动。 1、2、3、4和5 / rev TEF输入的组合导致功率降低1.5％，同时在高速向前飞行中还将某些振动负载降低50％以上。

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