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All Journal Conference SENATIK STT Adisutjipto Yogyakarta Jurnal Teknologi Kedirgantaraan (JTK) Jurnal Mahasiswa Dirgantara

Rabeta, Bismil

Universitas Dirgantara Marsekal Suryadarma

Author-ID : 893261

Aerospace Engineering Computer Science & IT Control & Systems Engineering Electrical & Electronics Engineering Engineering Environmental Science Industrial & Manufacturing Engineering Materials Science & Nanotechnology Mechanical Engineering Transportation

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Title

ANALISIS PERFORMA ENGINE MARCHETTI SF 260 Rabeta, Bismil
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 4, No 2 (2019): JURNAL TEKNOLOGI KEDIRGANTARAAN
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

The Aerospace Air Marshal Surydarma University (Unsurya) is a college of movement in aerospace technology that attempts to contribute and information related to aviation technology. One of the facilities owned by Unsurya is the Marchetti SF-260 aircraft which is used as a practice facility for implementing ground run-up engine tests. As long as this aircraft is in Unsurya, no one has ever tried to analyze the engine's performance. Therefore in this study do an analysis of the performance of the marchetti aircraft SF-260 was carried out using the Lycoming O-540 E4A5 engine to determine engine torque, engine power and mechanical efficiency varied by cruising altitude. From the results of the analysis it was found that the highest value at torque was 480.24 Nm, engine power 182 BHP and mechanical efficiency 42.83% obtained at an altitude of 10,000 ft.

Analisis Linear Statik Pada Vertical Tail dengan Variasi Defleksi Rudder Rabeta, Bismil; Arifin, Mufti; Fairuza, Syarifah
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 2, No 2 (2017): JURNAL TEKNOLOGI KEDIRGANTARAAN
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

Desain ekor vertikal pada pesawat sangat beragam bentuknya, bergantung pada karakteristik dan fungsinya. Pada ekor vertikal tersambung rudder yang merupakan control surface pada sumbu vertikal dengan gerakan menggeleng (yaw). Penulisan tugas akhir ini bertujuan untuk menganalisa beban aerodinamis pada ekor vertikal dengan defleksi rudder yang berbeda. Material yang digunakan pada pemodelan adalah aluminium alloy 7075-T6, merupakan paduan dari zinc dan copper. Pemodelan ekor vertikal dan analisa perhitungan dilakukan menggunakan pendekatan elemen hingga dengan bantuan software solidworks 2016. Dengan menggunakan menu flow simulation dan simulation pada solidworks, dapat diketahui output berupa stress, strain, displacement, dan safety factor. Dari hasil yang didapat distribusi stress dan strain memiliki nilai maksimal pada daerah hinge dan nilai minimal terjadi pada root leading edge dari ekor vertikal. Nilai stress maksimal pada pemodelan semakin meningkat seiring bertambah besarnya defleksi rudder yang diberikan, tetapi tidak melebihi yield strength dari material yang digunakan.

ANALISIS NUMERIK DISTRIBUSI TEKANAN & KECEPATAN ALIRAN UDARA PADA FUSELAGE B737-9 MAX Susilo, Tri; Rabeta, Bismil; Falah, Fikry
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 4, No 2 (2019): JURNAL TEKNOLOGI KEDIRGANTARAAN
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

Aerodynamic characteristics can be known by using computational Fluid Dynamics (CFD) methods. This study analyzes the pressure distribution and velocity of air flow on Fuselage B737-9 MAX using the Computational Fluid Dynamics (CFD) method with variations in attack angles of 0o, 15o, 30o and 45o. The results obtained are at 0o attack angle, 15o the difference in speed and pressure is not too significant or normal, while at the attack angle 30o and 45o the difference in speed and pressure is very significant or abnormal because the air flow at that angle experiences turbulence around the fuselage.

ANALISIS PENGARUH WINGLET PADA SAYAP PESAWAT CESSNA 172 MENGGUNAKAN PERANGKAT LUNAK XFLR5 Rabeta, Bismil; Hidayat, Fauzan Taufik; Franciscus, Freddy
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 5, No 1 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

Inovasi pada sayap pesawat terbang terus dikembangkan guna memperoleh efisiensi sayap yang lebih baik. Terutama untuk mengoptimalisasi bentuk sayap dan mengurangi induce drag pada pesawat dengan memasang sebuah alat yang dinamakan dengan Winglet. Pada penelitian ini dilakukan studi untuk mengetahui pengaruh winglet jika ditambahkan pada sayap pesawat Cessna 172. Winglet berfungsi untuk meningkatkan efisiensi pada sayap sehingga dapat mengurangi induce drag dan meningkatkan rasio perbandingan antara koefisien lift terhadap koefisien drag. Objek yang akan diuji merupakan modifikasi sayap pesawat Cessna 172 yang dimodelkan mempuyai variasi cant angle winglet 0°, 30°, 60°, dan 90° menggunakan perangkat lunak XFLR5. Hasil pengujian menunjukkan, bahwa modifikasi pemodelan sayap dengan modifikasi sayap berupa winglet memiliki perbandingan koefisien lift dan drag paling besar pada sudut cant angle 30° dengan nilai CL/CD optimum terdapat pada angle of attack 2.5° sebesar 24,728.

ANALISIS NUMERIK EFEK TUMBUKAN DAN POLA DEFORMASI CRASH BOX BERBENTUK ORIGAMI Rabeta, Bismil; Afandi, Sahril; Fransisco, Romario
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 5, No 1 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

Crash Box adalah batang longitudinal yang terintegrasi dengan bumper yang digunakan untuk menyerap energi tumbukan akibat tabrakan melalui proses deformasi (progressive buckling). Tujuan dari analisis ini adalah untuk mengetahui respon tabung crash box ketika dikenakan beban tumbukan dengan kecapatan rendah. Selain itu analisis ini juga untuk mengetahui besarnya Pmax (peak force) terhadap variasi geometri yang meghasilkan output berupa nilai gaya terhadap perpindahan, sebagai acuan untuk menentukan nilai dari mean crushing force (Pmean) dan crushing force efficiency (CFE). Pada setiap model memiliki mean crushing force (Pmean) dan crushing force efficiency (CFE) yang berbeda-beda. Pada model 1 memiliki nilai mean crushing force (Pmean) sebesar 12.976 kN dan crushing force efficiency (CFE) sebesar 0.584, model 2 memiliki nilai mean crushing force (Pmean) sebesar 10.458 kN dan crushing force efficiency (CFE) sebesar 0.789, dan model 3 memiliki nilai mean crushing force (Pmean) sebesar 9.282 kN dan crushing force efficiency (CFE) sebesar 0.798.

Perbandingan Analisis Termodinamika Mesin TPE-331 dan PT6A-42 Terhadap Variasi Ketinggian Terbang Bismil Rabeta
Jurnal Teknologi Kedirgantaraan Vol 5 No 2 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Mesin turboprop merupakan jenis mesin hybrid yang menyediakan gaya dorong jet sekaligus menggerakan baling-baling. Pada dasarnya proses pengoperasiannya sama dengan turbojet kecuali kerja turbin melalui sebuah poros utama yang terhubung dengan reduction gear yang digunakan untuk memutar baling-baling. Analisis termodinamika telah banyak dilakukan untuk mengetahui kinerja dari mesin turbofan dan turbojet, sedangkan untuk mesin turboprop masih sangat sedikit dilakukan. Pada penelitian ini dilakukan perbandingan analisis termodinamika mesin TPE-331 yang digunakan pada pesawat CASA-212 dimana disertifikasi pada awal tahun 1965 dan mesin PT6A-42 yang digunakan pada pesawat N-219 dimana disertifikasi pada tahun 1983. Perbandingan dilakukan untuk melihat perkembangan mesin turboprop selama hampir 20 tahun dan membandingkan kinerja mesin secara termodinamika untuk masing-masing mesin. Kinerja mesin yang akan dibandingkan meliputi gaya dorong propeller ,kerja kompresor, fuel to air ratio, laju aliran bahan bakar, kerja turbin, kerja spesifik poros propeller, daya poros , jet thrust , daya total dan equivalent shaft horsepower ESHP) .Adapun hasil perhitungannya untuk mesin TPE-331 memiliki nilai gaya dorong propeller tertinggi dengan perbedaan sebesar 21,22 % dengan mesin PT6A-42, kerja kompresor tertinggi ada pada mesin PT6A-42 dengan persentase 8 % lebih besar dibandingkan dengan mesin TPE-331, fuel to air ratio terendah ada pada mesin PT6A-42 yaitu sebesar 3,43% lebih rendah , sedangkan untuk laju bahan bakar tertinggi ada pada mesin PT6A-42 yaitu rata-rata sebesar 40,32%. Kerja turbin terbesar ada pada mesin PT6A-42 yaitu sebesar 3,3% lebih tinggi dibandingkan dengan mesinTPE-331, kerja poros , daya poros, Jet thrust, daya total dan ESHP terbesar dimiliki oleh mesin PT6A-42 masing-masing besarannya secara berturut-turut 1,65 %, 42,60%, 52,40%, 42,40%, 42,40% dibandingkan dengan mesin TPE-331.

Simulasi Graphical User Interface Analisis Termodinamika Mesin Turboprop Menggunakan Perangkat Lunak Matlab R2020a Bismil Rabeta; Mohammad A.F Ulhaq; Aswan Tajuddin; Agus Sugiharto
Jurnal Teknologi Kedirgantaraan Vol 6 No 2 (2021): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

A turboprop engine is a hybrid engine that delivers thrust or jet thrust and also drives the propeller. This is basically similar to a turbojet except the turbine works through the main shaft which is connected to the reduction gear to rotate the propeller in front of the engine. This research was conducted to determine the development of engine performance in thermodynamic analysis so as to know the value of each parameter on a engine that has been developing for 20 to 50 years with different engine manufacturing. So that in this study a comparison of the thermodynamic analysis of the TPE-331, PT6A-42 and H85-200 engines was carried out. In the TPE331-10, PT6A-42, and H85-200 turboprop engines the value of fuel to air ratio and shaft work increases with increasing altitude while compressor work, fuel flow rate, shaft power, propeller thrust, jet thrust, total thrust, equivalent engine power and ESFC decrease with increasing altitude. Furthermore, the turbine's working value is relatively stable as the altitude increases. After that, the value of compressor work and turbine work on the PT6A-42 engine was greater than that of the TPE331-10, and H85-200 engines. However, the value of the fuel to air ratio, fuel flow rate, shaft power, jet thrust, equivalent engine power and ESFC on the H85-200 engine was greater than the TPE331-10 and PT6A engines. Furthermore, at sea level, the value of the axle, propeller thrust, and total thrust on the H85-200 engine is greater than that of the TPE331-10 and PT6A-42 engines but at an altitude of 25,000 ft, the PT6A-4 engine has a greater value than that of the TPE331-10 and PT6A-42 engines. TPE331-10, and H85-200 engines.

Analisis Aplikasi Coating Pada Roller Track Cargo Compartment Pada Airbus 330-200/300 Vetho Tigelrito; Freddy Franciscus; Bismil Rabeta
Jurnal Teknologi Kedirgantaraan Vol 7 No 2 (2022): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v7i2.59

Aircaft are the most popular means of transportation in the delivery of goods from one area to another. These things can be inaminate objects or living things. Goods transported to the cargo area can be a trigger for damage to the cargo area of the Airbus 330 aircraft, such as spilling fluid from the cargo packaging and the loading process or unloading cargo can cause corrosion in the cargo areaRoller track cargo compartment is one part of the aircraft that is susceptible to corrosion. In aircraft maintenance manual there is no step to apply coating application, where it is known that the coating is one of the protective coatings of a metal to overcome the attack from corrosion. The trial of coating application on the A330-200-200/300 roller track compartment roller track model was conducted for 1670 hours to determine the comparison of roller track corrosion rate values given the av15 adrox protective coating with roller tracks that were not given the av15 adrox protective coating. The test results obtained that the average value of corrosion rate of roller track models with coating coating layers is 0.1505 and without coating layer which is 0.4045 mmpy with coating usage efficiency of 62.7%. So it can be concluded that the application of coating on roller track cargo compartment is effective in inhibiting corrosion rate.

Desain Iterasi Dudukan Pelat Pengukur Gaya Pada RIG Alat Uji Jatuh Bebas Menggunakan Optimasi Topology Maulana, Ilham; A. Sitompul, Sahril; Rabeta, Bismil; Fitriansyah, Rizky; Nurrohmad, Abian
Jurnal Teknologi Kedirgantaraan Vol 7 No 2 (2022): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v7i2.56

Abstract -. This research was conducted based on data obtained during testing at LAPAN (Lembaga Antariksa dan Penerbangan Nasional), where there was a case that became a concern. The test is about the free fall test, which results in a deflection that is considered too large. From these results it was decided to investigate further. This free fall test uses impact testing where a material is measured for its shock load resistance. Impact testing simulates the operating conditions of a material where the loading that occurs is not only in static conditions but also occurs in dynamic conditions. In the free fall test, a test was carried out to measure and see the resistance of the landing gear and crash box in receiving dynamic loads, when the aircraft landed. The main purpose of simulating this tool is for research and development of the free fall test equipment itself, as well as the design of the landing gear of the LSU (Lapan Survaillance UAV) drone in the future. The impact platform on the free fall test equipment plays an important role in impact testing, where the deformation of the plate holder will be converted by the load cell, into a signal received by the acquisition system. So it is designed to fit the existing needs. In this test equipment, the test object is given a load (50 kg and 200 kg), height (4.72 m and 1,204 m), so that it reaches a velocity (9,623 m/s and 4,861 m/s) with impactor crash box geometry and main landing gear as well as plate holder design based tools in the field. Based from testing, impact, and analysis using the finite element method in this study, it was found that the deflection value was 1.771 mm which reduced 94.61% for the crash box case and the deflection value was 2.696 mm with a reduction value of 87.85 % for the main landing gear case from the existing initial design. Keywords: Free fall test equipment, impact platform, landing gear, plate mount, main landing gear, crash box, finite element method, LSU.

Co-Authors A. Sitompul, Sahril Agus Sugiharto Aswan Tajuddin Fairuza, Syarifah Fairuza, Syarifah Falah, Fikry fitriansyah, Rizky Fransisco, Romario Freddy, Franciscus Hidayat, Fauzan Taufik Ilham Maulana Imron Rosadi Indirwan Alex Mochammad Haekal Farisi Mohammad A.F Ulhaq Mohammad Reza Pahlevi muftiarifin Nopelandi, Aldi Nurrohmad, Abian Ozi Satria Nanda Reza Enzal Pratama Putra Sitompul, Sahril Afandi Tri Susilo Vetho Tigelrito Yudisthira setyaji Zainal Fikry Heryanto Supit

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