CD Skripsi
Perancangan Pesawat Terbang Tanpa Awak Tipe Fixed Wing Untuk Misi Multirole
ABSTRACT
Fixed wing UAV is a type of unmanned aircraft that has fixed wings to its body.
The fixed wing UAV designed by the Riau University Flying Robot Team
previously had weaknesses and was inefficient in various situations. To improve
efficiency and high responsiveness in complex situations, this study will design a
fixed wing UAV that is capable of carrying out multirole missions with a higher
flight time value than before. This design begins with determining the design
requirement objective and estimating the MTOW. Next, calculate the wing and tail
geometry. Then the airfoil can be selected based on the value of the decisionmaking
matrix table. The next step is to create a fixed wing UAV design and
design a payload dropping mechanism. The fixed wing UAV was successfully
designed with an MTOW of 5 kg, a wingspan of 1,9 m using the EPPLER 66
airfoil. After that, the cg position of the fixed wing UAV component on the
longitudinal axis was calculated before simulating the aerodynamic
characteristics and strength of the fixed wing UAV structure. From the
aerodynamic characteristic simulation, the lift coefficient (CL) and drag
coefficient (CD) values of the fixed wing UAV during take-off mode were 0,8312
and 0,1595. While during cruise mode, the lift coefficient (CL) and drag
coefficient (CD) of the fixed wing UAV were 0,4554 and 0,0507. In the structural
strength simulation, it is known that the fuselage design has a maximum deflection
of 2,887 mm, a maximum stress of 0,209 MPa, and a safety factor of 15. While the
fixed wing UAV design is known to have a maximum deflection of 26,21 mm, a
maximum stress of 0,209 MPa and a safety factor of 15. With these safety factor
values, the fixed wing UAV has eligibility in terms of safety.
Keywords: UAV, fixed wing, multirole, aerodynamics, structure
Tidak tersedia versi lain