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Research Papers

Stability and Performance Analysis of Six-Rotor Unmanned Aerial Vehicles in Wind Disturbance

[+] Author and Article Information
Xianying Li

College of Mechanical and
Electrical Engineering,
Nanjing University of
Aeronautics and Astronautics,
Nanjing 210016, Jiangsu, China
e-mail: lixy@nuaa.edu.cn

Biao Zhao

College of Mechanical and
Electrical Engineering,
Nanjing University of
Aeronautics and Astronautics,
Nanjing 210016, Jiangsu, China
e-mail: zhaobiao@nuaa.edu.cn

Yu Yao

College of Aerospace Engineering,
Nanjing University of
Aeronautics and Astronautics,
Nanjing 210016, Jiangsu, China
e-mail: yy503@126.com

Hongtao Wu

College of Mechanical and
Electrical Engineering,
Nanjing University of
Aeronautics and Astronautics,
Nanjing 210016, Jiangsu, China
e-mail: eehtwu@nuaa.edu.cn

Yunping Liu

College of information and control,
Nanjing University of
Information Science and Technology,
Nanjing 210044, Jiangsu, China
e-mail: liuyunping@nuist.edu.cn

1Corresponding author.

Contributed by the Design Engineering Division of ASME for publication in the JOURNAL OF COMPUTATIONAL AND NONLINEAR DYNAMICS. Manuscript received March 8, 2017; final manuscript received December 2, 2017; published online January 10, 2018. Assoc. Editor: Katrin Ellermann.

J. Comput. Nonlinear Dynam 13(3), 031005 (Jan 10, 2018) (11 pages) Paper No: CND-17-1107; doi: 10.1115/1.4038776 History: Received March 08, 2017; Revised December 02, 2017

The effect of wind disturbances on the stability of six-rotor unmanned aerial vehicles (UAVs) was investigated, exploring the various disturbances in different directions. The simulation model-based Euler–Poincare equation was established to investigate the spectra of Lyapunov exponents. Next, the value of the Lyapunov exponents was used to evaluate the stability of the systems. The results obtained show that the various speeds of rotors are optimized to keep up the stability after disturbances. In addition, the flight experiment with the hitting gust has been carried out to verify the validity and accuracy of the simulation results.

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Figures

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Fig. 1

Schematic evolution of an initially infinitesimal two-dimensional sphere

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Fig. 2

Schematic diagram of the six-rotor UAV

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Fig. 3

Calculation process of Lyapunov exponents

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Fig. 5

Attitude curves with resultant disturbance force at the hovering stage revealing the remarkable range of variation of the roll curve and the position curve of z axis

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Fig. 4

Attitude curves at the hovering stage without disturbances

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Fig. 10

Location curves of different axis revealing the large fluctuation position between 82 to 88 s under gust disturbances: (a) x axis, (b) y axis, and (c) z axis

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Fig. 9

Variation curves of rotors speed of six-rotor UAVs encountered with the unexpected gusts between 82 to 88 s

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Fig. 8

Physical map of six-rotor UAVs at the hovering stage

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Fig. 7

Energy consumption with the disturbed system and standard state of systems revealing the consumption value of disturbed systems is higher than that of standard state of systems with delay of time

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Fig. 6

Optimized attitude curves at the hovering stage revealing a stable system with convergent curves compared to the initial attitude curve with disturbances

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