An initial design concept for a micro-coaxial rotorcraft using custom manufacturing techniques and commercial off-the-shelf components is discussed. Issues associated with the feasibility of achieving hover and fully functional flight control at small scale for a coaxial rotor configuration are addressed. Results from this initial feasibility study suggest that it is possible to develop a small scale coaxial rotorcraft weighing approximately 100 gm, and that moment control is sufficient for roll, yaw and lateral trim. A prototype vehicle was built and its rotors were tested in a custom hover stand used to measure thrust and power. The best measured rotor Figure of Merit, 0.42, was obtained for a single rotor configuration. A blade element momentum theory (BEMT) model of the rotor was implemented, and airfoil characteristics were estimated from the rotor tests. The model showed that profile drag accounts for 45% of the losses as opposed to 30% in full-scale helicopters. The radio controlled vehicle was flown untethered with its own onboard power source and exhibited good flight stability and control dynamics.
Design, analysis and hover performance of a rotary wing micro air vehicle
Entwurf, Leistungsanalyse und Schwebflugverhalten eines ferngesteuerten Miniatur-Drehflügelflugzeugs
Journal of the American Helicopter Society ; 48 , 2 ; 80-90
2003
11 Seiten, 13 Bilder, 4 Tabellen, 17 Quellen
Article (Journal)
English
Design, Analysis and Hover Performance of a Rotary Wing Micro Air Vehicle
Online Contents | 2003
|Hover Performance and Swashplate Design of a Coaxial Rotary Wing Micro Air Vehicle
British Library Conference Proceedings | 2004
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