Kurnianto, Dennis Rakhman (2018) Penentuan Spesifikasi Motor BLDC pada UAV Militus. Diploma thesis, Institut Teknologi Sepuluh Nopember.
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Abstract
Teknologi Pesawat udara tanpa awak (drone) saat ini berkembang dengan pesat, pesawat tanpa awak (drone) banyak digunakan pada dunia militer maupun keperluan komersil. Karena mempunyai banyak kelebihan yaitu memperkecil resiko human error, pengoperasian mudah, dan lebih efektif dibandingkan dengan pesawat berpilot. Pesawat tanpa awak sengaja dibuat dengan bodi yang ringan serta aerodinamis.
Untuk mengetahui gaya aerodinamik serta penentuan spesifikasi motor BLDC pesawat UAV Militus, maka digunakan software SolidWorks 2016 dan aplikasi Static Thrust Calculate. Tujuan dari tugas akhir ini adalah menganalisa pesawat UAV Militus, meliputi kontur tekanan, koefisien drag (CD), koefisien lift (CL) menggunakan software SolidWorks 2016, lalu diintegrasikan dengan penentuan motor BLDC menggunakan aplikasi Static Thrust Calculate, dan sistem mekatronika dari pesawat tersebut.
Dari hasil analisa aliran yang melintas pada bodi pesawat UAV Militus, koefisien drag (CD) yang diperoleh selama simulasi pesawat UAV Militus senilai 0,0611 dan koefisien lift (CL) pada pesawat UAV Militus senilai 0.0753. Lalu hasil analisa teoritis kebutuhan gaya thrust (TR) harus sama atau kurang dari thrust propeller (T) yang dihasilkan dan didukung hasil dari aplikasi didapatkan static thrust pada putaran konstan diperoleh senilai 5,68 kg.
================================================================================================================== Technology unmanned aircraft (drone) is currently growing rapidly, unmanned aircraft (drone) is widely used in the military as well as commercial purposes. Because it has many advantages that minimize the risk of human error, easy operation, and more effective than piloted aircraft. Drone deliberately made with a lightweight body and aerodynamics.
To determine the aerodynamic forces and specification of
BLDC motor UAV Militus, then used software SolidWorks 2016 and aplication Static Thrust Calculate. The purpose of this thesis is to compare including the coefficient of drag (CD), the coefficient of lift (CL), then determination of BLDC motor using aplication static thrust calculate, and system mechatronics of that plane.
From the analysis of the flow passing through the fuselage UAV Militus, the coefficient of drag (Cd) obtained during the flight simulation UAV Militus worth 0,0611, and coefficient of lift (Cl) at Flyingwing ,UAV aircraft worth 0.0753. Then theoritical analysis of requirement thrust must to equal or lower than thrust propeller and supported of aplication static thrust at constant rotation obtained 5,68 kg.
| Item Type: | Thesis (Diploma) |
|---|---|
| Additional Information: | RSMI 629.132 2 Kur p |
| Uncontrolled Keywords: | kontur; tekanan; drag coefficient (CD); lift coefficient (Cl) separasi; kebutuhan thrust (TR); thrust (T); contour; pressure; drag coefficient (CD); lift coefficient (CL); separation; thrust requirement (TR); thrust (T) |
| Subjects: | T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL152.8 Vehicles, Remotely piloted. Autonomous vehicles. U Military Science > U Military Science (General) > UG Military Engineering > UG1242.D7 Unmanned aerial vehicles. Drone aircraft |
| Divisions: | Faculty of Vocational > Mechanical Industrial Engineering (D4) |
| Depositing User: | Dennis Rakhman Kurnianto |
| Date Deposited: | 02 May 2018 04:31 |
| Last Modified: | 19 Jun 2020 03:46 |
| URI: | http://repository.its.ac.id/id/eprint/51315 |
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