Nonlinear Modeling the Quadcopter Considering the Aerodynamic Interaction
This paper presents a nonlinear model of the quadcopter to simulate the actual motion. An aerodynamic model of the rotor is obtained through wind-tunnel tests, which consider the variations in the rotor’s angular velocity, incoming flow speed, and angle of attack of the rotor (<inline-...
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2021-01-01
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doaj-ac001e700937415cbddbfa70c5c720e22021-10-06T23:00:34ZengIEEEIEEE Access2169-35362021-01-01913471613473210.1109/ACCESS.2021.31166769552918Nonlinear Modeling the Quadcopter Considering the Aerodynamic InteractionJianchuan Ye0https://orcid.org/0000-0002-2625-4872Jiang Wang1Tao Song2Zeliang Wu3Pan Tang4School of Aerospace Engineering, Beijing Institute of Technology, Beijing, ChinaSchool of Aerospace Engineering, Beijing Institute of Technology, Beijing, ChinaSchool of Aerospace Engineering, Beijing Institute of Technology, Beijing, ChinaSchool of Aerospace Engineering, Beijing Institute of Technology, Beijing, ChinaSchool of Aerospace Engineering, Beijing Institute of Technology, Beijing, ChinaThis paper presents a nonlinear model of the quadcopter to simulate the actual motion. An aerodynamic model of the rotor is obtained through wind-tunnel tests, which consider the variations in the rotor’s angular velocity, incoming flow speed, and angle of attack of the rotor (<inline-formula> <tex-math notation="LaTeX">$\alpha _{p}$ </tex-math></inline-formula>). The quadcopter’s fuselage aerodynamics and mutual interference are simulated using the computational fluid dynamic (CFD) method. The mesh motion method is used to simulate the rotation of the rotor. It can be found that the interference has a significant impact on the aerodynamic load of the fuselage and the thrust and pitch moment of the rear rotor. The mathematical expression of the interference model is given by adopting the idea of the small disturbance hypothesis. The yaw dynamics model is also improved by considering the motor’s dynamics. The quadcopter’s nonlinear model can be obtained by combining the rotor model, fuselage model, motor model, and interference model. Then, flight experiments are done at hovering and forward flight states to verify the established model, and the experiment results are in good agreement with the nonlinear model. Finally, the quadcopter’s characteristic descriptive abilities of different accurate models are discussed to help designers to build a suitable quadcopter model according to the requirements.https://ieeexplore.ieee.org/document/9552918/Quadcopteraerodynamic interactionrotor modelwind-tunnel tests |
collection |
DOAJ |
language |
English |
format |
Article |
sources |
DOAJ |
author |
Jianchuan Ye Jiang Wang Tao Song Zeliang Wu Pan Tang |
spellingShingle |
Jianchuan Ye Jiang Wang Tao Song Zeliang Wu Pan Tang Nonlinear Modeling the Quadcopter Considering the Aerodynamic Interaction IEEE Access Quadcopter aerodynamic interaction rotor model wind-tunnel tests |
author_facet |
Jianchuan Ye Jiang Wang Tao Song Zeliang Wu Pan Tang |
author_sort |
Jianchuan Ye |
title |
Nonlinear Modeling the Quadcopter Considering the Aerodynamic Interaction |
title_short |
Nonlinear Modeling the Quadcopter Considering the Aerodynamic Interaction |
title_full |
Nonlinear Modeling the Quadcopter Considering the Aerodynamic Interaction |
title_fullStr |
Nonlinear Modeling the Quadcopter Considering the Aerodynamic Interaction |
title_full_unstemmed |
Nonlinear Modeling the Quadcopter Considering the Aerodynamic Interaction |
title_sort |
nonlinear modeling the quadcopter considering the aerodynamic interaction |
publisher |
IEEE |
series |
IEEE Access |
issn |
2169-3536 |
publishDate |
2021-01-01 |
description |
This paper presents a nonlinear model of the quadcopter to simulate the actual motion. An aerodynamic model of the rotor is obtained through wind-tunnel tests, which consider the variations in the rotor’s angular velocity, incoming flow speed, and angle of attack of the rotor (<inline-formula> <tex-math notation="LaTeX">$\alpha _{p}$ </tex-math></inline-formula>). The quadcopter’s fuselage aerodynamics and mutual interference are simulated using the computational fluid dynamic (CFD) method. The mesh motion method is used to simulate the rotation of the rotor. It can be found that the interference has a significant impact on the aerodynamic load of the fuselage and the thrust and pitch moment of the rear rotor. The mathematical expression of the interference model is given by adopting the idea of the small disturbance hypothesis. The yaw dynamics model is also improved by considering the motor’s dynamics. The quadcopter’s nonlinear model can be obtained by combining the rotor model, fuselage model, motor model, and interference model. Then, flight experiments are done at hovering and forward flight states to verify the established model, and the experiment results are in good agreement with the nonlinear model. Finally, the quadcopter’s characteristic descriptive abilities of different accurate models are discussed to help designers to build a suitable quadcopter model according to the requirements. |
topic |
Quadcopter aerodynamic interaction rotor model wind-tunnel tests |
url |
https://ieeexplore.ieee.org/document/9552918/ |
work_keys_str_mv |
AT jianchuanye nonlinearmodelingthequadcopterconsideringtheaerodynamicinteraction AT jiangwang nonlinearmodelingthequadcopterconsideringtheaerodynamicinteraction AT taosong nonlinearmodelingthequadcopterconsideringtheaerodynamicinteraction AT zeliangwu nonlinearmodelingthequadcopterconsideringtheaerodynamicinteraction AT pantang nonlinearmodelingthequadcopterconsideringtheaerodynamicinteraction |
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