Analysis of rotor interference effects on quadrotor lift in hover

Home > Archive>Volume 5, Issue 2, 2014 >148-153

Analysis of rotor interference effects on quadrotor lift in hover
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                        Liu XuesongLiu Xuesong
Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle,Nanjing University of Aeronautics and Astronautics
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Ang HaisongAng Haisong
Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle,Nanjing University of Aeronautics and Astronautics
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Xiao TianhangXiao Tianhang
Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle,Nanjing University of Aeronautics and Astronautics
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Affiliation:Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle,Nanjing University of Aeronautics and Astronautics,Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle,Nanjing University of Aeronautics and Astronautics,Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle,Nanjing University of Aeronautics and Astronautics
Clc Number:V211.3
Fund Project:A Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions

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Abstract:

The aerodynamic interference among rotors has strong affect on the lift force of the quadrotor UAV, it is necessary to study on the interference to provide a reference for the aerodynamic layout design. An equivalent actuator disk model of airplane propeller is presented, which takes into consideration such factors as such as diameter, chord,pitch and rotating speed of rotor, etc. The effectiveness of the equivalent actuator disk is established thorough increasing momentum source,calculating the different lift force of a single rotor in hover on Fluent and comparing with the experimental data. Thorough the above method, the effects of interference among rotors on lift force of quadrotor in hover is calculated that have different rotor distances. The resulted of the calculation indicates that the smaller rotor distance causes the stronger interference as well as the more loss of lift force.

Key words:aerodynamic interference;quadrotor;CFD;equivalent actuator disk model;momentum source

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Liu Xuesong, Ang Haisong, Xiao Tianhang. Analysis of rotor interference effects on quadrotor lift in hover[J]. Advances in Aeronautical Science and Engineering,2014,5(2):148-153

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Received:October 31,2013
Revised:December 26,2013
Adopted:January 23,2014
Online: November 06,2015
Published:

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