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All Journal Jurnal Ilmu Dasar Rancang Bangun Computational and Experimental Research in Materials and Renewable Energy (CERiMRE)
Kusumoaji, Danartomo
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Civil Engineering, Building, Construction & Architecture Computer Science & IT Control & Systems Engineering Energy Engineering Materials Science & Nanotechnology Mathematics Physics Transportation

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Perhitungan Aerodrome Reference Code (ARC) pada Rumpin Airfield, Berdasarkan Regulasi International Civil Aviation Organization (ICAO) Hartono, Hartono; Kusumoaji, Danartomo; Aziz, Abdul; Rusmin, Muhammad
Jurnal Teknik Sipil : Rancang Bangun Vol 6, No 2 (2020): Oktober 2020
Publisher : Universitas Muhammadiyah Sorong

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (361.377 KB) | DOI: 10.33506/rb.v6i2.1142

Abstract

Penelitian ini bertujuan untuk mengetahui nilai Aerodrome Reference Code (ARC) pada landasan pacu rumpin. Maksud dari ARC atau kode referensi adalah menyediakan suatu metode sederhana untuk menghubungkan beberapa spesifikasi yang mengacu pada karakteristik dari Bandar Udara (Bandara), sehingga di dapatkan sejumlah fasilitas Bandara yang cocok bagi pasawat terbang yang akan dioperasikan. ARC didapatkan dari dua buah elemen yang berhubungan dengan karakteristik performansi dan dimensi pesawat terbang. Dimana penelitian perhitungan ARC ini menggunakan peraturan atau prosedur dari International Civil Aviation Organization (ICAO) - Annex 14 Vol.1 Aerodrome Design and Operations dibutuhkan beberapa data seperti koreksi ketinggian (elevasi), koreksi temperature, koreksi kemiringan landasan pacu hingga nilai dari Aeroplane Reference Field Length (ARFL). Hasil perhitungan dari penelitian ini adalah ARC untuk bandara udara dan/atau landasan pacu Rumpin yaitu 2B dengan arti, angka 2 menunjukkan bahwa ARFL berada pada angka 800-1200 dan huruf B menyatakan bentangan sayap sekitar 15-24 meter.
Engine Performance Testing and Fuel Consumption of Unmanned Aerial Vehicle with Octane Rating Variations Kusumoaji, Danartomo; Hartono, Hartono; Rohman, Abdul; Yunus, Meila Filhasni
Computational And Experimental Research In Materials And Renewable Energy Vol 6 No 2 (2023): November
Publisher : Physics Department, Faculty of Mathematics and Natural Sciences, University of Jember

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.19184/cerimre.v6i2.43757

Abstract

Unmanned aerial vehicles or often known as Drone / UAV are used for various missions, some of which are for aerial photography, monitoring, load testing, spraying fertilizers and so on. The performance of unmanned aircraft is supported by several aspects, one of which is the propulsion or engine of the aircraft. The Aeronautical Technology Research Center, BRIN, Indonesia has several series of unmanned aerial vehicles used for several missions. To support the missions that must be taken by unmanned aircraft, engine performance is one of the important factors for carrying out missions. In this study, engine testing will be carried out to see the performance of the engine by varying the octane rating of the fuel used. This test used an LSU-04 aircraft engine with a 3W-110i B2 engine type with a capacity of 110 cc and a propeller size of 26x8. Engine tests were carried out using 3 types of fuel with octane ratings of 92, 95 and 98. The data taken is engine speed data (rpm), thrust data and fuel consumption data. Tests and measurements were carried out at the highest rpm value of 6000 rpm and the test was carried out for 1 hour. From the test results, the results were obtained that the performance of the engine that has the largest thrust value is the one that uses fuel with an octane rating of 92, namely with a thrust value of 14.13 kgf, while the thrust value for fuel with an octane rating of 95 is 13.35 kgf, and the thrust produced in fuel with an octane rating of 98 is 13.06 kgf. Then from the results of measuring fuel consumption, the most economical value is an engine that uses fuel with an octane rating of 98, which consumes 1007 ml of fuel, while for fuel consumption with an octane value of 95 of 1028 ml and for an octane value of 92 of 1061 ml.Keywords: UAV, 3W-110i B2 Engine, 92 Octane, 95 Octane, 98 Octane, Engine Performance
Analysis of Propeller Selection for Unmanned Aircraft Kusumoaji, Danartomo; Aziz, Abdul; Rismayanti, Irma; Nahak, Ildefonsa A. F.
Jurnal ILMU DASAR Vol 25 No 2 (2024)
Publisher : Fakultas Matematika dan Ilmu Pengetahuan Alam Universitas Jember

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.19184/jid.v25i2.43794

Abstract

Unmanned aircraft are usually used to perform missions, for example surveillance missions. This mission is not always carried out in a suitable location. Researchers must ensure that the aircraft can take off properly. For this reason, runway distance greatly affects the performance of the aircraft. The aircraft can fail to take off due to the lack of thrust generated by the propeller. The propeller diameter size of each unmanned aircraft can differ from one another and this difference in propeller diameter causes a difference in thrust force. Therefore, it is very important to determine the right propeller diameter to be used on an unmanned aircraft that is adjusted to the runway distance. This propeller selection analysis is carried out using experimental methods, which is tool testing and simulation with Propeller Power Calculator software. The results of this study can be seen that a propeller with a larger diameter will produce a greater thrust force. The size of the diameter and pitch and the number of blades of a propeller can also affect the amount of thrust generated. This will be a consideration for choosing a propeller to be used on an unmanned aircraft. So that the selected propeller can be used optimally by reviewing the amount of thrust that is influenced by the amount of diameter.
Co-Authors Abdul Aziz Abdul Rohman Hartono Hartono Muhammad Rusmin Nahak, Ildefonsa A. F. Rismayanti, Irma Yunus, Meila Filhasni