DESIGN AND TESTING OF COAXIAL ROTOR DUCTED FAN VTOL UAV
Abstract: In general aircraft
are classified into two major categories: fixed wing and rotary wing aircraft
which are commonly known as helicopters. The vertical take-off and landing
(VTOL) aircraft is designed to be capable of both flying horizontally like a
fixedwing airplane and also ascending and descending vertically and thus
eliminates the needof a runway [1],[2],[3],[4]. At recently years, Ducted fan
VTOL is most popular. Thereason behind that fact is the efficiency of power on
the maneuver. This paper presents theresults of design and testing of coaxial
rotor ducted fan VTOL UAV. Pitch and rollmoment of this vehicle will controlled
with 2 independence control surface that’s attachedon the bottom of duct. The
Ducted profile is applied to the system in order to improve theefficiency
thrust at hovering state [3]. The goal of this design is to find optimized
rotationspeed rotor and distance between rotors. The value of rotation speed
and distance betweenrotors could be simulated in Computational Fluid Dynamics
(CFD) Analysis. The targetof this simulation is to find some combination
minimum yawing moment and maximum thrust at specifics distance between each
rotor. In order to validate this simulation andanalysis, we used dedicated
platform that’s could sense thrust and roll, pitch, yawmoment.
Penulis: M. Kartidjo, S.A.
Nugroho2 & R.G. Jiniwangun
Journal Code: jptmesindd090203
