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Modeling and Closed Loop Flight Testing of a Fixed Wing Micro Air Vehicle

This paper presents the nonlinear six degrees of freedom dynamic modeling of a fixed wing micro air vehicle. The static derivatives of the micro air vehicle are obtained through the wind tunnel testing. The propeller effects on the lift, drag, pitching moment and side force are quantified through wi...

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Detalles Bibliográficos
Autores principales:	Kandath, Harikumar, Pushpangathan, Jinraj V., Bera, Titas, Dhall, Sidhant, Bhat, M. Seetharama
Formato:	Online Artículo Texto
Lenguaje:	English
Publicado:	MDPI 2018
Materias:	Article
Acceso en línea:	https://www.ncbi.nlm.nih.gov/pmc/articles/PMC6187696/ https://www.ncbi.nlm.nih.gov/pubmed/30424045 http://dx.doi.org/10.3390/mi9030111

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