不同高度小型直升机主旋翼自适应研究

2019 International Conference on Military Technologies (ICMT) Pub Date : 2019-05-01 DOI:10.1109/MILTECHS.2019.8870110

T. Bulín, D. Rozehnal, J. Hnidka

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引用次数: 0

摘要

本文对直升机悬停时气动特性的一些计算和测量结果进行了讨论。提出了一种简单的叶片单元模型(BEM)，并对日本天皇LOGO 600 3D直升机在不同高度的悬停飞行性能进行了计算。计算结果与风洞测量结果进行了比较。

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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Adaptation of Main Rotor of Small Helicopter at Different Altitudes

This paper presents a discussion to some results of the calculation and measurement of aerodynamic characteristics of helicopter in the hover. A simple blade element model (BEM) is presented and a calculation of flight performance in a hover of helicopter Mikado LOGO 600 3D in various altitudes was performed as well. Results of the calculation are compared to the measurement conducted in the wind tunnel.

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来源期刊

2019 International Conference on Military Technologies (ICMT)

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