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

Kandath, Harikumar and Pushpangathan, Jinraj V and Bera, Titas and Dhall, Sidhant and Bhat, M Seetharama (2018) Modeling and Closed Loop Flight Testing of a Fixed Wing Micro Air Vehicle. In: MICROMACHINES, 9 (3).

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Official URL: https://dx.doi.org/10.3390/mi9030111


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 wind tunnel testing. The dynamic derivatives are obtained through empirical relations available in the literature. The trim conditions are computed for a straight and constant altitude flight condition. The linearized longitudinal and lateral state space models are obtained about trim conditions. The variations in short period mode, phugoid mode, Dutch roll mode, roll subsidence mode and spiral mode with respect to different trim operating conditions is presented. A stabilizing static output feedback controller is designed using the obtained model. Successful closed loop flight trials are conducted with the static output feedback controller.

Item Type: Journal Article
Additional Information: Copy right of this article belong to MDPI, ST ALBAN-ANLAGE 66, CH-4052 BASEL, SWITZERLAND
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 28 Jun 2018 14:32
Last Modified: 28 Jun 2018 14:32
URI: http://eprints.iisc.ac.in/id/eprint/60100

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