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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Bibliographic Details
Main Authors: Kandath, Harikumar, Bera, Titas, Dhall, Sidhant, Pushpangathan, Jinraj V., Bhat, M. Seetharama
Other Authors: School of Electrical and Electronic Engineering
Format: Article
Language:English
Published: 2018
Subjects:
Online Access:https://hdl.handle.net/10356/85034
http://hdl.handle.net/10220/45126
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Institution: Nanyang Technological University
Language: English