22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-4.7.R1
ULTRA LIGHT WING STRUCTURE FOR HIGH ALTITUDE LONG ENDURANCE UAV
Z. Goraj (1), T. Ueda (2)
(1) Warsaw University of Technology, Warsaw, Poland;
(2) Tetsuhiko Ueda, National Aeronautical Laboratory, Tokyo, Japan
Keywords: airplane design, flutter
This paper presents a conceptual design of
main wing, body and empennage for high
altitude long endurance unmanned aerial
vehicle. An arrangement of main spar, ribs,
shell and strut for high aspect ratio main wing
and tailplane has been proposed. A number of
characteristics (stiffnesses, mass distributions,
moments of inertia etc), necessary for flutter
calculations, is included in this paper. The
structural characteristics are computed using
NASTRAN programme. The critical flutter
speed for empennage has been found by means
of the conventional U-G method. The Doublet-
Point-Method (DPM) for non-coplanar
configuration was used to compute the unsteady
aerodynamic forces. Aerodynamic model of
empennage includes 168 aerodynamic panels.
This analysis can be treated as a starting point
for further wing optimisation. The main goal is
to obtain the structure lighter and
aerodynamically more efficient - the feature -
being very important in long endurance
missions.
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