Design and Performance Analysis of a Micro Aerial Vehicle Concept

Abstract

The guideline of the present paper is to single out the main problems concerning the Micro Aerial Vehicle design and to discuss the results of a reasonably accurate but time-saving strategy. The aerodynamic analysis, the propulsion system sizing and the performance evaluation have been carried out within the preliminary design phase of a fixed wing MAV, called MicroHawk. A software tool for 3D aerodynamic analysis has been implemented and the reliability of its results, concerning critical flight regimes and non-conventional configurations, has been tested by comparing them with experimental results. The propulsion system sizing has been faced with a numerical tool for DC motor propeller modeling; it is intended for preliminary estimation of the aircraft performances and the propulsive system initial sizing, when detailed and reliable data from experimental testing are not available. The DC motor model is strongly related to the dimensioning of the energy sources, that represents a challenging goal within narrow constraints in terms of weight and power required. Finally, in order to complete the aircraft performance analysis, a simulation model has been set up to provide the evaluation of the aircraft trim states. This preliminary study will be addressed to the analysis of the aircraft dynamics characteristics.