Preliminary design and wind tunnel tests of a micro air vehicle for surveillance and sensor-bearing applications

Abstract

This work presents the preliminary design of a micro air vehicle (MAV) and the wind tunnel tests of some wing configurations identified, in the design phase, as potentially suitable for the MAV realization. After some considerations about the airfoil adoption and its performance estimation, five possible plan shapes for the wing are defined and the three-dimensional model realization is described. These wings are experimentally tested in a wind tunnel as simple wings and as complete MAV dummies, equipped with vertical fins. The results from the tests allow the selection of the most promising configurations among those tested for the achievement of the desired MAV performance. A final evaluation on the better performing wing is carried out with regard to the placement of the components in its interior and to the calculation of its stability parameters.

Keywords

micro air vehicle low Reynolds flight wind tunnel

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References

Parra

Bordeneuve Guibe

Briere

Development of a MAV — from theory to implementation. EURO-AUVSI Conference, Bruxelles, December 2002.

Waszak

M. R.

Jenkins

L. N.

Ifju

(AIAA) Stability and control properties of an aeroelastic fixed wing. Micro Aerial Vehicle Atmospheric Flight Mechanics Conference, Montreal, August 2001.

AeroVironment's ‘Black Widow’ micro air vehicle wins two awards. Aerovironment press release, June 1999.

Lausetti

Filippi

Elementi di meccanica del volo, 1956 (Levrotto & Bella, Turin).

Di Lecce

Fondamenti di aerotecnica, 1997 (IBN Editore, Rome).

Talay

T. A.

Introduction to the Aerodynamics of Flight, 1975 (Langley Research Centre, National Aeronautics and Space Administration).

Drela

XFOIL v.6.9 User Guide, 2001 (MIT Aero & Astro Harold Youngren, Aerocraft, Inc., Cambridge).

Didacta Italia.

Pn62D — Subsonic Wind Tunnel Operating Manual, 1998 (Didacta Italia, Turin).

Van Dorn

N. H.

De Young

A comparision of three theoretical methods of calculating span load distribution on swept wings. Technical note no. 1476, 1947. Ames Aeronautical Laboratory, National Advisory Committee for Aeronautics, Washington.

10.

Stevens

V. I.

Theoretical basic span loading characteristics of wings with arbitrary sweep, aspect ratio and taper ratio. Technical note no. 1772, 1948. Ames Aeronautical Laboratory, National Advisory Committee for Aeronautics, Washington.

11.

De Young

Theoretical additional span loading characteristics of wings with arbitrary sweep, aspect ratio and taper ratio. Technical note no. 1491, 1947. Ames Aeronautical Laboratory, National Advisory Committee for Aeronautics, Washington.

12.

Weissinger

The lift distribution of swept-back wings. Technical memorandum no. 1120, 1947. National Advisory Committee for Aeronautics, Washington.