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Design of fixed wing micro air vehicles

Published online by Cambridge University Press:  03 February 2016

P. Cosyn  and
J. Vierendeels
P. Cosyn
Affiliation:
Department of Flow, Heat and Combustion Mechanics, Ghent University, Belgium
J. Vierendeels
Affiliation:
Department of Flow, Heat and Combustion Mechanics, Ghent University, Belgium
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Abstract

The paper describes the methodology and computational design strategies used to develop a series of fixed wing micro air vehicles (MAVs) at the Ghent University. The emphasis of the research is to find an optimal MAV-platform that is bound to geometrical constraints but superior in its performance. This requires a multidisciplinary design optimisation but the challenges are mainly of aerodynamic nature. Key areas are endurance, stability, controllability, manoeuvrability and component integration. The highly three-dimensional low Reynolds number flow, the lack of experimental databases and analytical or empirical models of MAV-aerodynamics required fundamental research of the phenomena. This includes the use of a vortex lattice method, three-dimensional CFD-computations and a numerical propeller optimisation method to derive the forces and their derivatives of the MAV and propeller for performance and stability-related optimisation studies. The design method leads to a simple, stable and robust flying wing MAV-platform that has the agility of a fighter airplane. A prototype, the UGMAV25, was constructed and flight tests were performed. The capabilities of the MAV were tested in a series of successful flight manoeuvres. The UGMAV15, a MAV with a span of 15cm, is also developed to test flight-qualities and endurance at this small scale. With the current battery technology, a flight-time of at least one hour is expected.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1119 , May 2007 , pp. 315 - 326
Copyright
Copyright © Royal Aeronautical Society 2007 

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