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Endah Yuniarti
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Jurnal Teknologi Kedirgantaraan (JTK)
Published by Universitas Dirgantara Marsekal Suryadarma
ISSN : 25282778     EISSN : 26849704     DOI : https://doi.org/10.35894/jtk.v6i2
Core Subject : Science, Social, Engineering,
Aerospace Engineering Engineering Environmental Science Materials Science & Nanotechnology Transportation
Jurnal Teknologi Kedirgantaraan (JTK) memuat artikel-artikel hasil penelitian dan kajian analitis kritis bidang teknik penerbangan yang belum pernah dipublikasikan pada media lain. Adapun lingkup bahasan meliputi: propulsi, avionik, struktur, material pesawat terbang, pemeliharaan dan operasional pesawat terbang dan topik-topik yang berkaitan. Tujuan utama dari Jurnal Teknologi Kedirgantaraan adalah mempublikasikan hasil penelitian yang dilakukan dan memotivasi produktivitas karya ilmiah dalam bidang Teknik Penerbangan/Aeronautika. Jurnal Teknologi Kedirgantaraan (JTK) terbit secara berkala dua volume dalam satu tahun. Kami selaku pengelola juga selalu melakukan pembenahan dan perbaikan agar Teknologi Kedirgantaraan ini dapat diakui secara nasional maupun internasional.
Arjuna Subject : Teknik (semua kategori) - Teknik Mesin
Articles 179 Documents
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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

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.
Analisis Angkutan Kargo Antara ATR 72-600 Passenger, ATR 72-600 Freighter Dan ATR 72-600 Converted Pada Rute Makassar – Kendari Somadi, Ridho Misbahudin; Arifin, Mufti; Yuniarti, Endah
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.v7i2.57

Abstract

Delivery of goods (cargo) between islands or between countries is faster by air transportation. Air cargo can use passenger aircraft (bulk cargo), Air freighters, Combined air freighters, Converted freighters for the same type of aircraft, such as ATR 72-600. This study discusses fuel consumption, comparison of payload capacity, and comparison of fuel consumption per payload of ATR 72-600 aircraft for the Makassar – Kendari route. namely the ATR 72-600, ATR 72-600 Freighter and ATR 72-600 Converted aircraft. The method used is a quantitative method. The results of the calculation using the flight crew operation manual for ATR 72-600 passenger fuel carried 1.143,4 kg and fuel consumption of 609.4 kg, ATR 72-600 Freighter and Converted aircraft carried 1.210,3 kg of fuel and 613,3 fuel consumption, 4 kg. Fuel costs per kg of cargo, ATR 72-600 Passenger aircraft are more expensive, namely Rp. 1,279 per kg, freighter Rp. 1,136 per kg, converted bulk cargo Rp. 1,175 per kg, Converted Large cargo door Rp. 1,202 per kg. The largest Cargo capacity is 9,000 kg on ATR 72-600 Freighter aircraft and the smallest is 2,150 on ATR 72-600 Passenger aircraft. If cargo delivery does not exceed 2,150 kg, it is more profitable to use ATR 72-600 passenger aircraft, but if the weight or volume sent much larger should use the ATR 72-600 Freighter.
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

Abstract

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. 
Analisa Perancangan Smoke Tunnel Portable Sebagai Alat Visualisasi Airflow Wind Tunnel Chaeroni, Amat; Sugiharto, Agus
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.v7i2.61

Abstract

Cara memahami tentang benda-benda yang bergerak didalam aliran udara ada banyak sekali macamnya, seperti alat uji terowongan angin (wind tunnel). Agar dapat terlihat aliran udaranya, maka perlu dibuat alat peraga simulasi aerodinamika yang mampu memvisualisasikan kondisi airflow atau aliran udara dengan menggunakan asap, sehingga praktikan mampu memahami dengan mudah kondisi aliran udara yang terjadi ketika melewati benda dengan berbagai macam bentuk permukaan seperti penampang airfoil. Alat peraga simulasi wind tunnel dengan menggunakan asap dinamakan smoke tunnel. Akses untuk merubah posisi benda yang diuji didalam test section smoke tunnel sangat penting agar dapat dilakukan perubahan posisi selama proses pengujian. Dari beberapa jenis bentuk nozzle (cerobong asap) yang diuji, didapat bentuk yang paling ideal yaitu bentuk cerobong asap yang lurus dengan diameter kecil yaitu Ø4 mm berjumlah 19 buah disusun dari bawah keatas dengan jarak antar cerobong asap 10 mm. Posisinya berada di tengah ke arah benda uji searah dengan aliran udara. Ukuran chamber sebagai test section adalah 40 cm x 24 cm x 8 cm. Ukuran smoke tunnel secara keseluruhan adalah 65 cm x 24 cm x 8 cm, dimensi tersebut termasuk ukuran yang kecil sehingga bisa di kategorikan sebagai alat yang portable dan dapat di operasikan dimanapun termasuk didalam kelas sebagai alat peraga simulasi ilmu aerodinamika.
Analisis Dimensi Propeler Untuk Kebutuhan Desain Konseptual Pesawat Piston Rosalie, Rhea Anggun; Alimin, Edy Karyadi; Arifin, Mufti
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.v7i2.62

Abstract

This research conducted a comparative analysis of propeller dimensions for the conceptual design of a piston aircraft. The method used is statistical linear regression by comparing some variables related to propellers from 27 piston aircraft data. Based on comparison results obtained 6 strong relationships, namely aircraft speed and engine power, aircraft weight and engine power, aircraft weight and propeller weight, aircraft weight and the number of propellers blades, engine power and propeller weight, and propeller weight and the number of propellers blades so that it can be used for conceptual design reference. The propeller diameter and engine speed variables do not have a strong relationship in regression but form a cluster so that it can be used as a conceptual design reference. The conceptual design simulation with an aircraft weight of 3500 lb produces a propeller with a diameter of 80 inches, the engine power of 325.51 hp, propeller weight of 86.13 pounds, engine speed of 2500 rpm, and 3 blade propellers with a thrust of 1340.05 lbf.
Analisis Pemeliharaan Battery Menggunakan Metode Reliability Mapping Pada Pesawat A330-900 Bilhaq, Muhammad Kevin; Arifin, Mufti
Jurnal Teknologi Kedirgantaraan Vol 9 No 1 (2024): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v9i1.92

Abstract

Airplanes is transportation that need a high level of safety and comfort. Therefore, the aircraft's parts must be in excellent shape and able to fly. This study aims to assess the reliability of battery maintenance on A330-900 aircraft using the reliability mapping method, as well as to assess the efficiency of doing so in order to compare the reliability mapping method's implementation to maintenance schedules for the batteries on these aircraft. The stages of this study started with gathering maintenance information for the A330-900, then went on to classify the different types of maintenance and create reliability mapping tables. Additionally, a comparison between the implementation and maintenance schedule for the A330-900 aircraft battery was made in order to analyze the reliability of battery maintenance on the A330-900 aircraft and to determine the effectiveness of using the reliability mapping method. After that, carry out reliability mapping optimization computations till conclusions about the research's findings are reached. Reliability mapping makes it evident where and when unforeseen maintenance takes place. The fact that just 3 unscheduled maintenance visits totaling 5.5% of the total maintenance were made out of the 54 replacements shows how dependable the battery maintenance on the A330-900 is. The execution of battery maintenance is reportedly wrong, with numbers based on estimations made according to calendar time being 77% early, 19% late, and 4% accurate
Simulasi Perhitungan Fuel Consumtion Pada Pesawat A320 Saat Holding Di Bandara Internatioanal Halim Perdanakusuma Menggunakan Teori Antrian Dhimas, Dhimas Ilyas Ramadhani; Arifin, Mufti; Julizar, Ade
Jurnal Teknologi Kedirgantaraan Vol 9 No 1 (2024): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v9i1.95

Abstract

In aircraft operations, to determine the amount of fuel consumption on the aircraft, it is necessary to know the time used for holding. Holding time is influenced by the number of aircraft using runway facilities and can be calculated using queuing theory. This study aims to determine the calculation of fuel consumption on aircraft when holding at Halim Perdanakusuma International Airport using queuing theory. Data for queue calculation is based on observations on flightradar24. Fuel consumption is estimated using aircraft maximum landing weight data, turning flight performance theory and aircraft manuals. From the results of the calculation, it was found that it took 6 minutes for the aircraft to queue during holding, from this time the fuel consumption calculation was carried out on the holding pattern and obtained the most fuel consumption results on the KOMIT holding pattern, which was 241,8 kg based on queuing theory and 554,8 kg based on actual data calculations. The difference in fuel consumption results is far due to the difference in time used. The time obtained based on queuing theory is 6 minutes and is equal for each holding pattern, while the time obtained based on actual data varies from one aircraft to another. For turning flight performance capabilities, the A320 aircraft can maneuver 180º within 1 minute with the largest radius of 9.204 m in 61 seconds or 1 minute 1 second on the IMU holding pattern and a radius of 2.327 m in 60,6 seconds or 1 minute 6 seconds on the COMMIT holding pattern.
Analisis Tingkat Kebisingan Pesawat Saat Take-Off Berdasarkan Variasi Tinggi Lintasan di Bandara Halim Perdanakusuma Arindho Andrifa Faturrohman; Mufti Arifin; Ericko Chandra Utama
Jurnal Teknologi Kedirgantaraan Vol 9 No 1 (2024): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v9i1.97

Abstract

An increase in flight frequency can have a negative impact on the surrounding environment, one of which is high noise levels. Noise can come from full activity, runway stay, movement towards the runway, or aircraft engine testing. Airplane noise during take-off is one of the environmental problems that need attention at airports. The height of the aircraft's trajectory during take-off can affect the noise level generated by the aircraft, but not much research has been conducted to measure the impact of variations in the height of the disturbance on the noise level of aircraft at Halim Perdanakusuma Airport. This study aims to measure the noise level of aircraft during take-off with variations in track height at Halim Perdanakusuma Airport. The method used in this study is to observe 4 aircraft taking off at Halim Perdanakusuma Airport with a research time of 3 days, and the measuring instrument used is a sound level meter. Sound level meters measure noise in dBA units between 30 and 130 dB at a frequency of 20 to 20.000 Hz. Based on the calculation and measurement results obtained, it is known that the maximum height when the measurement is on the second day is at point A of 277 meters, while at point B is 299 meters. While the highestnoise measurement at point A is 93,1 dB while at point B it is 91,5 dB. The measured noise value based on calculations is estimated at 66,2 dB and is still below the Airbus A320 aircraft noise certification for flyover takeoff of 73,7 dB.
ANALISIS PEMBEBANAN STATIS PADA STRUKTUR HEXACOPTER DRONE UNTUK PERTANIAN (DRUPER) Erlangga, Noval; Sindhu, Simon; Yuniarti, Endah
Jurnal Teknologi Kedirgantaraan Vol 9 No 1 (2024): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v9i1.100

Abstract

Menurut data dari Pusat Data dan Sistem Informasi Pertanian Sekretariat Jenderal – Kementerian Pertanian 2020, area lahan pertanian di Indonesia seluas 36.817.086 Hektar. Dengan luas lahan pertanian yang begitu potensial, petani bisa menggunakan teknologi drone untuk membantu tugas untuk meningkatkan produktifitas. Tujuan dari peneltian ini untuk mengetahui nilai kekuatan yang diterima drone dalam menahan beban pada kondisi terbang hover. Desain drone terdiri dari tiga bagian utama yaitu Body frame menggunakan material plastik polikarbonat, Support structure, dan Skid yang menggunakan material aluminium dengan konfigurasi hexacopter. Sketsa dan model drone didesain dan dirancang menggunakan perangkat lunak CAD (Computer Aided Design) Solidworks dan simulasi pembebanan struktur dilakukan menggunakan perangkat lunak CAE (Computer Aided Engineering) ANSYS Workbench. Perhitungan simulasi analisis kekuatan struktur drone dengan metode elemen hingga diperoleh nilai Regangan Von Mises sebesar 0,00089 dan Tegangan Von Mises maksimum sebesar 21,96 MPa yang terjadi pada bagian komponen Support Structure. Dimana nilai tegangan ini masih dibawah nilai kekuatan luluh (Yield Strength) materialnya yang berupa aluminium 6061-T6 yaitu sebesar 259,2 MPa, sehingga secara umum drone untuk pertanian ini dinyatakan aman.
Analisis Kerusakan Pelat Komposit Akibat Beban Low Velocity Impact Terhadap Variasi Energi Impak Dengan Menggunakan Elemet Split Widanto, Muhammad Hadi; Amat Chaeroni; Surya, Eggy
Jurnal Teknologi Kedirgantaraan Vol 9 No 1 (2024): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v9i1.103

Abstract

Komposit merupakan material yang paling banyak digunakan pada struktur pesawat terbang. Hal ini karena material komposit memiliki kekuatan struktur yang tinggi dan berat yang ringan. Namun komposit mempunyai kelemahan yaitu tidak tahan terhadap beban impak karena sifatnya yang getas. Beban impak dapat terjadi akibat human error pada saat dilakukan perawatan akibat benda jatuh atau karena tumbukan benda asing lainnya. Pada penelitian ini dilakukan simulasi impak struktur komposit untuk mengetahui ketahan komposit dengan variasi energi impak. Pada simulasi impak menggunakan metode elemen hingga dengan memodelkan intralaminar dan interlaminar menggunakan metode kegagalan hashin dan cohesive zone model. Penelitian terhadap pengaruh element split yang dimodelkan pada pelat komposit menjadi penelitian utama. Dari hasil menunjukkan pengaruh element split terhadap respon dinamik dan kerusakan delaminasi dapat memberikan hasil dengan korelasi yang lebih baik terhadap hasil eksperimen.

Page 8 of 18 | Total Record : 179

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