Services on Demand
Journal
Article
Indicators
- Cited by SciELO
- Access statistics
Related links
- Similars in SciELO
Share
Computación y Sistemas
On-line version ISSN 2007-9737Print version ISSN 1405-5546
Abstract
CARRENO AGUILERA, Ricardo; PATINO ORTIZ, Miguel and PATINO ORTIZ, Julián. Sliding Mode Control Applied to a Mini-Aircraft Pitch Position Model. Comp. y Sist. [online]. 2014, vol.18, n.2, pp.409-416. ISSN 2007-9737. https://doi.org/10.13073/CyS-18-2-2014-041.
Normally, mini-aircraft must be able to perform tasks such as aerial photography, aerial surveillance, remote fire and pollution sensing, disaster areas, road traffic and security monitoring, among others, without stability problems in the presence of many bounded perturbations. The dynamical model is affected by blast perturbations. Based on this, it is possible to design, evaluate and compare the real result with respect to pitch control law based on reference trajectory in the presence of external disturbances (blasts) or changes in the aircraft controller model. The model has non-linear properties but, with soft perturbations through the aircraft trajectory, allows a linear description without losing its essential properties. The Laplace description is a transfer function that works to develop the state space, with unknown invariant parameters using a wind tunnel. Control law is based on a feedback sliding mode with decoupled disturbances, and the output result is compared with the real pitch position measured in the real system. The control law applied to the system has a high convergence performance.
Keywords : Sliding modes; integral and proportional control; mini-aircraft models.