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ANALISIS KINERJA PESAWAT TERBANG TANPA AWAK TIPE VERTICAL TAKE-OFF LANDING (VTOL) QUADPLANE DENGAN SISTEM PROPULSI TAMBAHAN YANG BERSIFAT FOLDABLE
A fixed wing VTOL vehicle is a combination of a rotary wing and a fixed wing vehicle.
It can fly with good efficiency and the ability to take off and land vertically. The ability
to fake off and land vertically is due to the additional propulsion system. However, the
use of this propulsion system results in increased air dragfrom the auxiliary propulsion system. To
overcome this problem, this research offers a solution of a fixed wing VTOL liJ.itV with a foldable
auxiliary propulsion system. The design of this vehicle involves a
'fanufacturing process that refers to a predetermined design. The VTOL vehicle with n additional
propulsion system was successfully made with the % e"or of the anufacturing results compared to
the design dimensions below 5%. Analysis of the peiformance of the vehicle based on the theory has
a maximum speed of31.23 m Is at
100% throttle while based on the test results shows the maximum speed of 24.93 m Is, for the
theoretical stall speed test results of 12 m Is then the actual stall speed of the vehicle of 13.88
m Is there is a difference between theoretical and actual calculations of 1.88 m Is. As for the
rate of climb based on the theory of the vehicle, there is a difference between theoretical and
actual calculations. As for the theoretical rate of climb o/7.51 m/s and experimentally o/3.54
m/s.While for the theoretical flight time at 50% throttle the flight time reaches 21.03 minutes, in
actual testing the vehicle has
9;JRtal flight time of 6 minutes with a energi consumption of 10.8 wh. In addition, the fo!Jable
propulsion mechanism proved to function properly during the test. In the cruise phase, the folded
VTOL arm requires 60-80% throttle, while the open arm only requires 40-50% throttle for the same
speed.
Kl!yWorda: UAV, VTOL, Foldable
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