|
Designing of Auto-landing system of fixed wing unmanned aerial vehicles using the backstepping and disturbance observer-based sliding mode control
|
Marzieh Kakavand   , Ali MoarefianPour * , Mahdi Siahi |
| , moarefian@srbiau.ac.ir |
|
|
Abstract: (1599 Views) |
| The control of unmanned aerial vehicles is a challenging problem due to their lightweight and intense coupling between longitudinal and lateral motion. Considering this issue, in this article, an automatic landing system for a fixed-wing unmanned aircraft exposed to wind disturbances and parametric uncertainties is designed using the backstepping algorithm and the disturbance observer-based sliding mode control. Two controllers are designed based on the backstepping algorithm and sliding mode control to stabilize the attitude angles. The longitudinal speed controller uses the sliding mode technique to maintain the total speed relative to the ground at a constant desired value in all landing phases. A nonlinear disturbance-observer is considered in the sliding mode controller structure to estimate wind disturbance and parametric uncertainty. The new robust automatic landing system is software implemented, and its performance is investigated by several numerical simulations; Lateral deviation relative to the runway is eliminated while the unmanned aerial vehicle maintains its desired trajectory slope angle in all phases of the landing at the desired value. Therefore, the results of numerical simulations prove that the new control structure is stable and robust against different initial conditions, different types of wind disturbances (wind shear and discrete gust), and parametric uncertainty. |
Article number: 3 |
| Keywords: Unmanned Aerial Vehicles, Automatic Landing, Backstepping Control, Sliding Mode control, Disturbance observer |
|
|
Full-Text [PDF 9568 kb]
(593 Downloads)
|
Type of Study: Research |
Subject:
Nonlinear Control
Received: 2022/06/9 | Accepted: 2023/05/11 | Published: 2023/07/22
|
|
|
|
|
|
|
| Send email to the article author |
|
|
|
| Add your comments about this article |
|
|
|
