CD Skripsi
Analisis Kinerja Sistem Pendorong (Propulsion System) Pada Wahana Terbang Serindit V-2
ABSTRACT
Unmanned Aerial Vehicle (UAV) Serindit V-2 has entered the 2nd generation
development stage. The vehicle is designed to take part in the Indonesian Flying
Robot Contest (KRTI) in the Airplane category, where the vehicle is designed to fly
at high speed and maneuver. This study aims to determine the performance of the
propulsion system and the flight performance of the Serindit V-2 UAV theoretically
and experimentally. It is aimed at the development of the next generation. Initial
research by selecting and testing the thrust generated by plastic propellers from 8
to 12 inches in diameter. To get the optimal thrust, a static test was carried out
using the thrust benchmarking system method. The highest thrust produced is
29.607 N on a 12-inch propeller. Further flight testing was carried out, with the
vehicle being flown using a 12-inch propeller in autonomous mode. The flight
altitude is 100 m with an angle of 16° when climbing, and 1° horizontally (cruise)
on a straight track along the 1 Km, back and forth. Test was carried out several
times, with variations in the proportion of the throttle, ranging from 50 to 100%.
The parameters obtained from the test results are the rate of climb, stall speed,
maximum cruising speed, and flight time. From the test results, the value of the rate
of climb is 2,656 m/s, the stall speed is 13 m/s, and the maximum speed that can be
achieved by the vehicle is 24,562 m/s. The flight time required by the vehicle to
complete the flight mission, is 3.27 minutes.
Keywords: UAV, Propulsion System, Serindit V-2, Propeller, Flight Performance.
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