This paper presents a new method for controlling tri rotor-type unmanned aerial vehicles (UAV) adapted from the SE (3) nonlinear geometric method for quadrotor-type UAV. Like its predecessor, the control strategy for single tri rotors is realized in a hierarchical architecture, containing both attitude controller and position controller. As a basis, the mathematical dynamics of the tri rotor is given in form of rotation matrix that ensures the algorithm is independent from any specific representation, such as Euler angle or quaternion. Assumption about primary thrust component is made to decouple the equations of the controllers to find an appropriate reference target for the attitude controller. An integral action is proposed to alleviate the steady-state error that arises from incorrect modelling due to simplification. This is justified by a Lyapunov function that also yields additional conditions for parameter gains setup. Output of the controller includes desired torque components, as well as total thrust magnitude. It is from this point that divergence from the original method for quadrotors becomes prominent. A numerical solver is introduced to yield the desired motors’ angular speed and tail servo angle. Some numerical examples implemented on MATLAB/Simulink illustrate that the controller is able to correct steady-state error and gives quick response, just like its quadrotor-type counterpart.
| Published in | American Journal of Aerospace Engineering (Volume 5, Issue 2) |
| DOI | 10.11648/j.ajae.20180502.14 |
| Page(s) | 96-105 |
| Creative Commons |
This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited. |
| Copyright |
Copyright © The Author(s), 2018. Published by Science Publishing Group |
Tri Rotor, Geometric, Nonlinear, Control, SE (3), SO (3).
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APA Style
Dinh-Thinh Hoang, Thi-Hong-Hieu Le, Ngoc-Hien Nguyen. (2018). Adapting SE (3) Nonlinear Geometric Method to Control Single-Tri Rotors with Integrator. American Journal of Aerospace Engineering, 5(2), 96-105. https://doi.org/10.11648/j.ajae.20180502.14
ACS Style
Dinh-Thinh Hoang; Thi-Hong-Hieu Le; Ngoc-Hien Nguyen. Adapting SE (3) Nonlinear Geometric Method to Control Single-Tri Rotors with Integrator. Am. J. Aerosp. Eng. 2018, 5(2), 96-105. doi: 10.11648/j.ajae.20180502.14
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Download@article{10.11648/j.ajae.20180502.14,
author = {Dinh-Thinh Hoang and Thi-Hong-Hieu Le and Ngoc-Hien Nguyen},
title = {Adapting SE (3) Nonlinear Geometric Method to Control Single-Tri Rotors with Integrator},
journal = {American Journal of Aerospace Engineering},
volume = {5},
number = {2},
pages = {96-105},
doi = {10.11648/j.ajae.20180502.14},
url = {https://doi.org/10.11648/j.ajae.20180502.14},
eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajae.20180502.14},
abstract = {This paper presents a new method for controlling tri rotor-type unmanned aerial vehicles (UAV) adapted from the SE (3) nonlinear geometric method for quadrotor-type UAV. Like its predecessor, the control strategy for single tri rotors is realized in a hierarchical architecture, containing both attitude controller and position controller. As a basis, the mathematical dynamics of the tri rotor is given in form of rotation matrix that ensures the algorithm is independent from any specific representation, such as Euler angle or quaternion. Assumption about primary thrust component is made to decouple the equations of the controllers to find an appropriate reference target for the attitude controller. An integral action is proposed to alleviate the steady-state error that arises from incorrect modelling due to simplification. This is justified by a Lyapunov function that also yields additional conditions for parameter gains setup. Output of the controller includes desired torque components, as well as total thrust magnitude. It is from this point that divergence from the original method for quadrotors becomes prominent. A numerical solver is introduced to yield the desired motors’ angular speed and tail servo angle. Some numerical examples implemented on MATLAB/Simulink illustrate that the controller is able to correct steady-state error and gives quick response, just like its quadrotor-type counterpart.},
year = {2018}
}
TY - JOUR T1 - Adapting SE (3) Nonlinear Geometric Method to Control Single-Tri Rotors with Integrator AU - Dinh-Thinh Hoang AU - Thi-Hong-Hieu Le AU - Ngoc-Hien Nguyen Y1 - 2018/11/21 PY - 2018 N1 - https://doi.org/10.11648/j.ajae.20180502.14 DO - 10.11648/j.ajae.20180502.14 T2 - American Journal of Aerospace Engineering JF - American Journal of Aerospace Engineering JO - American Journal of Aerospace Engineering SP - 96 EP - 105 PB - Science Publishing Group SN - 2376-4821 UR - https://doi.org/10.11648/j.ajae.20180502.14 AB - This paper presents a new method for controlling tri rotor-type unmanned aerial vehicles (UAV) adapted from the SE (3) nonlinear geometric method for quadrotor-type UAV. Like its predecessor, the control strategy for single tri rotors is realized in a hierarchical architecture, containing both attitude controller and position controller. As a basis, the mathematical dynamics of the tri rotor is given in form of rotation matrix that ensures the algorithm is independent from any specific representation, such as Euler angle or quaternion. Assumption about primary thrust component is made to decouple the equations of the controllers to find an appropriate reference target for the attitude controller. An integral action is proposed to alleviate the steady-state error that arises from incorrect modelling due to simplification. This is justified by a Lyapunov function that also yields additional conditions for parameter gains setup. Output of the controller includes desired torque components, as well as total thrust magnitude. It is from this point that divergence from the original method for quadrotors becomes prominent. A numerical solver is introduced to yield the desired motors’ angular speed and tail servo angle. Some numerical examples implemented on MATLAB/Simulink illustrate that the controller is able to correct steady-state error and gives quick response, just like its quadrotor-type counterpart. VL - 5 IS - 2 ER -
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