Sliding mode control applied to a mini-aircraft pitch position model

Ricardo Carreño Aguilera, Miguel Patiño Ortiz, Julián Patiño Ortiz

Research output: Contribution to journalArticle

Abstract

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.
Original languageAmerican English
Pages (from-to)409-416
Number of pages367
JournalComputacion y Sistemas
DOIs
StatePublished - 1 Jan 2014

Fingerprint

Sliding mode control
sliding
aircraft
Aircraft
perturbation
trajectory
Trajectories
Aerial photography
disturbance
aerial photography
transfer function
wind tunnel
Disasters
Wind tunnels
Transfer functions
disaster
Fires
Pollution
Antennas
Feedback

Cite this

Aguilera, Ricardo Carreño ; Ortiz, Miguel Patiño ; Ortiz, Julián Patiño. / Sliding mode control applied to a mini-aircraft pitch position model. In: Computacion y Sistemas. 2014 ; pp. 409-416.
@article{32b59b9f8fcf4bccabb4ecabfa46e438,
title = "Sliding mode control applied to a mini-aircraft pitch position model",
abstract = "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.",
author = "Aguilera, {Ricardo Carre{\~n}o} and Ortiz, {Miguel Pati{\~n}o} and Ortiz, {Juli{\'a}n Pati{\~n}o}",
year = "2014",
month = "1",
day = "1",
doi = "10.13053/CyS-18-2-2014-041",
language = "American English",
pages = "409--416",
journal = "Computacion y Sistemas",
issn = "1405-5546",
publisher = "Centro de Investigacion en Computacion (CIC) del Instituto Politecnico Nacional (IPN)",

}

Sliding mode control applied to a mini-aircraft pitch position model. / Aguilera, Ricardo Carreño; Ortiz, Miguel Patiño; Ortiz, Julián Patiño.

In: Computacion y Sistemas, 01.01.2014, p. 409-416.

Research output: Contribution to journalArticle

TY - JOUR

T1 - Sliding mode control applied to a mini-aircraft pitch position model

AU - Aguilera, Ricardo Carreño

AU - Ortiz, Miguel Patiño

AU - Ortiz, Julián Patiño

PY - 2014/1/1

Y1 - 2014/1/1

N2 - 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.

AB - 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.

UR - https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=84904011272&origin=inward

UR - https://www.scopus.com/inward/citedby.uri?partnerID=HzOxMe3b&scp=84904011272&origin=inward

U2 - 10.13053/CyS-18-2-2014-041

DO - 10.13053/CyS-18-2-2014-041

M3 - Article

SP - 409

EP - 416

JO - Computacion y Sistemas

JF - Computacion y Sistemas

SN - 1405-5546

ER -