Experimental Study on the Aerodynamic Arrangement of Small Multi-rotor Aircraft with High Capacity Payload

doi:10.3969/j.issn.1000-1093.2019.06.025

Abstract

Abstract: The hover efficiency of multi-rotor aircraft is mainly determined by the configuration of rotor system. In order to obtain the hover efficiency of multi-rotor system with different aerodynamic parameters, the thrust and power consumption of multi-rotor system with different rotor position, the number of rotor blades, the shape and size of rotor arm, the spacing of coaxial rotors and the overlap area of non-coaxial rotors are measured experimentally. The variation of hover efficiency with the disk loading for rotor different configurations is also analyzed. The experimental results show that the 2-blade rotor with pusher configuration is characterized with better hovering efficiency; the size of rotor arm has a greater influence on the hovering efficiency compared with its shape; the hovering efficiency of coaxial rotor is close to that of interference-free single rotor under a higher rotor disk loading， and achieves better performance when the spacing ratio is 30.4%; and the energy loss can be effectively reduced by adjusting the vertical and horizontal spacing ratios of the non-coaxial overlap region, and the hovering efficiency is significantly improved when the horizontal spacing ratio is ranged from 10% to 15% with a smaller vertical spacing ratio. Key

Key words: multi-rotoraircraft, propeller, rotorarm, coaxialspacing, overlapregion, hoveringefficiency

CLC Number:

V211.3

LEI Yao， LIN Rongzhao， WU Zhiquan. Experimental Study on the Aerodynamic Arrangement of Small Multi-rotor Aircraft with High Capacity Payload[J]. Acta Armamentarii, 2019, 40(6): 1323-1328.

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第40卷第6期
2019 年6月兵工学报ACTA
ARMAMENTARIIVol.40No.6Jun.2019

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