Investigation On The Propulsive Efficiency Of The Small Uav Conceptual Design
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Date
2012-03
Authors
Yahaya, Khairul Ikhsan
Journal Title
Journal ISSN
Volume Title
Publisher
Universiti Sains Malaysia
Abstract
A parametric study of low altitude small Unmanned Autonomous Vehicle (UAV) conceptual
design was performed. The purpose was to estimate constraint diagram propulsive efficiency
of propeller-Brushless Direct Current (BLDC) motor propulsion system at two different
flight conditions with the consideration of Atmospheric Boundary Layer (ABL) turbulent
effect. The lift slope and drag polar of the small UAV was obtained by simulating the
airframe in FluentTM 6.3 using SST k-ω turbulence model at stall, cruise and maximum
speeds. Constraint diagram was constructed and power loading at different flight conditions
was resolved as required thrust at different airspeed. Goldstein vortex theory of propellers
was used to model propeller; the propeller blade geometry and size was varied to see the
effect of propeller torque and rotational speed at required thrust and airspeed with BLDC
motor matching. CFD simulation results show a logarithmic trend increase in minimum drag
with the decrease of airspeed. Without considering the propulsive efficiency of the
propulsion system, the power loading at design point, determined by maximum speed
requirement was about 0.23N/W. Himax HA2825-2700 with second highest rated power of
400W was found to be the most suitable BLDC motor. It was concluded that for constructing
constraint diagram, the propulsive efficiency value of the best BLDC motor-propeller
combination was 58 percent for maximum speed requirement and 42 percent for time to
climb requirement.
Description
Keywords
Investigation on the propulsive efficiency of , the small UAV conceptual design