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| Format: | Artículo científico |
| Language: | en |
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Instituto Politécnico Nacional
2014
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| Online Access: | https://www.redalyc.org/articulo.oa?id=61531305014 |
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Table of Contents:
- Sliding Mode Control Applied to a Mini-Aircraft Pitch Position Model Ricardo Carreño Aguilera Miguel Patiño Ortiz Julián Patiño Ortiz Computación mini Sliding modes aircraft models integral and proportional control Normally , mini - aircraft must be able to perform tasks such as aerial photography, aerial su rveillance, remote fire and pollution sensing, disaster area s , road traffic and security monitoring , among other s, without stability problems in the presence of many bounded perturbations. The dy namical model is affect ed by blast perturbations. B ase d on t his, it i s 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, allow s a linear description without losing its essential prope rties. The Laplace description is a transf er function that works to develop the state sp ace, with unk nown invariant paramet er s using a wind tunnel. Control law is based o n 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. 2014 artículo científico 1405-5546 https://www.redalyc.org/articulo.oa?id=61531305014 en http://www.redalyc.org/revista.oa?id=615 Computación y Sistemas application/pdf Instituto Politécnico Nacional Computación y Sistemas (México) Num.2 Vol.18