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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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Analisis Perbandingan Performa Saat Takeoff Pada Engine CFM56-7b Dengan Konfigurasi Thrust Rating 26300 Lbs Dan 27300 Lbs Setiyawati, Defi; Alimin, Edy K.; Yuniarti, Endah
Jurnal Teknologi Kedirgantaraan Vol 7 No 1 (2022): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v7i1.51

Abstract

The CFM 56-7B engine is manufactured by CFM International which is used on the B737-600/700/800/900 aircraft. This engine has several variations of the thrust rating with varying performance. Engine performance parameters include Thrust, Specific Fuel Consumption (SFC), Core Speed (N2), and Exhaust Gas Temperature (EGT). Performance testing can be done using the Engine Test Cell. However, the engine test cell is a calibrated tool, which allows deviation of the test results. Then the performance calculation is done using the formula in the Engine Shop Manual - Test 003 - Engine Acceptance Test to find out the engine performance during the takeoff phase at the highest thrust rating of 26300 lbs and 27300 lbs and compare the performance of the two engines. Comparison of the calculation results states that an engine with a thrust rating of 26300 lbs is superior to Exhaust Gas Temperature, while an engine with a thrust rating of 27300 lbs has advantages at Thrust, Specific Fuel Consumption and Core Speed (N2).
Penyederhanaan Sistem Pemanas Dan Cairan Yang Digunakan Pada Smoke Generator Untuk Alat Peraga Ilmu Aerodinamika amat chaeroni
Jurnal Teknologi Kedirgantaraan Vol 7 No 1 (2022): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v7i1.52

Abstract

Alat uji wind tunnel saat dioperasikan tidak dapat memvisualisasikan kondisi aliran udara yang melewati benda uji seperti penampang airfoil sayap peawat terbang. Agar dapat terlihat aliran udaranya, maka perlu dibuat alat peraga simulasi kondisi aliran udara dengan asap, agar para mahasiswa mampu memahami dengan mudah kondisi aliran udara yang terjadi ketika melewati benda dengan berbagai macam bentuk permukaan.Alat peraga aerodinamika yang memiliki aliran asap disebut smoke tunnel yang memiliki dengan beberapa layer aliran asap yang dapat di atur jumlah layer aliran asap sesuai dengan kebutuhan. Alat yang menghasilkan asap untuk smoke tunnel adalah smoke generator. Saat ini memang sudah banyak yang memproduksi secara komersil smoke generator yang juga difungsikan sebagai alat disinfektan dengan menambahkan cairan disinfektan kedalam smoke generator.Untuk menyederhanakan cara kerja smoke generator dan juga menginformasikan cara pembuatannya, maka pada penelitian ini akan dijelaskan secara rinci cara pembuatan smoke generator yang murah dan mudah dengan menggunakan beberapa bahan yang sering dijumpai yaitu, cooling fan komputer, kawat nickelin, converter VAC ke VDC, sumbu kompor serta kontak plastik. Untuk menimbulkan asap pada smoke generator dapat menggunakan cairan yang mengandung minyak yang terdapat pada beberapa produk baby oil.
Pengaruh Waktu Tempering terhadap Karakter Baja s45c Pasca Quenching pada 950oc dan Tempering 500 C Ahmad Zayadi; Sungkono; Masyhudi; Ekky Setyawan T
Jurnal Teknologi Kedirgantaraan Vol 7 No 1 (2022): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v7i1.53

Abstract

Baja merupakan salah satu bahan struktur yang berfungsi sebagai wadah secara fisik, memberikan kekuatan mekanik, dan struktur penyangga untuk berbagai komponen industri nuklir, bahan tersebut membutuhkan sifat mekanik yang tinggi. Baja S45C memiliki kekuatan mekanik yang sedang sehingga dapat ditingkatkan sifat mekaniknya dengan perlakuan panas. Penelitian ini mempunyai tujuan untuk mendapatkan karakter mekanik, mikrostruktur, kekerasan, dan komposisi kimia pada Baja S45C. Metode yang digunakan adalah komposisi kimia dengan spark spectrometer, pengujian Tarik menggunakan mesin uji Tarik 50 KN, pengamatan mikrostruktur menggunakan mikroskop optik, dan kekerasan dengan vickers microhardness tester. Hasil penelitian menunjukkan bahwa komposisi kimia sampel pengujian adalah baja S45C, kekuatan tarik baja S45C yang menggunakan sampel tarik pasca perlakuan panas austenisasi, quenching media oli dan tempering 500 OC waktu penahanan 60 menit pendinginan suhu tungku lebih tinggi UTS (Ultimate tensile strength) dengan nilai UTS 805,12 (N/mm2), kekuatan luluh (Y)= 619,14 (N/mm2), dan regangan (e) = 15,00 %. dibandingkan sampel tanpa perlakuan panas dengan nilai (UTS) = 331,9 (N/mm2), kekuatan luluh (Y) = 267,27 (N/mm2) , dan regangan (e) = 20,08 %. Regangan baja S45C sampel tarik standar dan silinder pasca perlakuan panas lebih rendah dibandingkan sampel tanpa perlakuan panas. Mikrostruktur baja S45C tanpa perlakuan panas mempunyai fasa ferit dan perlit, sedangkan pasca quenching dan tempering adalah fasa martemper dan ferit. Semakin lama waktu penahanan pada proses tempering baja S45C, maka akan semakin rendah nilai kekerasan yang didapat. Proses perlakuan panas yang diterapkan pada sampel tarik baja S45C akan meningkatkan ketangguhan baja S45C yang ditandai dengan kenaikan kekuatan tarik dan keuletannya. Kekerasan logam dasar lebih rendah dibandingkan pada daerah patahan yang disebabkan adanya fenomena pengerasan regangan di daerah patahan selama uji tarik berlangsung.
Pengembangan Perangkat Lunak Rencana Terbang (Flight Plan) Simulasi Terbang Ariawan D Rachmanto; Hernawati
Jurnal Teknologi Kedirgantaraan Vol 8 No 1 (2023): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v8i1.66

Abstract

Flight plan (rencana terbang) merupakan salah satu tahapan yang harus dilakukan sebelum melakukan penerbangan. Flight plan harus dikirimkan kepada ATS (Air Traffic Services) paling lambat satu jam sebelum pesawat lepas landas dari bandara asal. Flight plan merupakan persyaratan apakah terbang IFR atau VFR. Pada penelitian ini akan dibuat sebuah perangkat lunak untuk membuat flight plan yang berisi informasi dasar (rute penerbangan) seperti nomer pesawat, awal keberangkatan, bandara tujuan/kedatangan, bahan bakar (fuel) yang dibawa, titik waypoint(rute) yang dilalui dengan Navaid sebagai panduan penerbangan, ketinggian. Perangkat lunak dikembangkan dengan menggunakan pemodelan peta menggunakan MapX 4.0 dengan bahasa pemrograman menggunakan C# Visual Studio 2010, database menggunakan MySql untuk menyimpan data airport,data NavAids, data flight plan termasuk data-data waypoint yang merupakan rute . Peta dilengkapi dengan titik-titik bandara udara Indonesia, NavAids (VOR dan NDB), waypoint dan airways. Metoda pengembangan perangkat lunak menggunakan metoda Prototipe.
SIMULASI NUMERIK FLOAT PESAWAT 19 PENUMPANG DENGAN STRUKTUR CARBON-EPOXY COMPOSITE KETIKA LANDING DI PERMUKAAN AIR: NUMERIC SIMULATION OF 19 PASSENGER AIRCRAFT FLOAT WITH CARBON-EPOXY COMPOSITE STRUCTURE WHEN LANDING ON THE WATER SURFACE Dwi Juniarsah, Fahri; Sitompul, Sahril Afandi; Yuniarti, Endah
Jurnal Teknologi Kedirgantaraan Vol 8 No 1 (2023): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v8i1.67

Abstract

The 19-passenger aircraft can be modified into a seaplane by providing it with a floating device in the form of a float. The use of float is very advantageous because it does not change the configuration of the fuselage much, but the mass and design of the float must be adjusted so that the performance of the aircraft does not decrease. Impact between the water and the float structure can create critical loads or even cause structural damage. The purpose of this research is optimizing the direction of the composite fiber by comparing the four arrangement of fiber directions by looking at the results of the Tsai-Hill failure criteria. In addition, the finite element method simulation is carried out in static simulation conditions to determine the response of the float structure with Carbon-epoxy material due to static loading based on variations in pressure loads during landing and to determine the effect of composite thickness on pressure distribution. which is applied to the bottom surface of the float. From the analysis, it was found that the most optimal fiber direction was [0o2/45o2/-45o2/90o2]s with a composite thickness of 2 mm. The biggest displacement is at the back of the float. In the condition of the pressure load when VS0 the received stress is 202.422 MPa. The current received stress VREF 352,927 MPa. When the speed is 70 knots, the received stress is greater, namely 437.876 MPa with a Tsai-Hill value of 0.2622. This indicates that Carbon-epoxy is ideal for use as a float material because of its resistance to high stresses.
Analisis Kekuatan Struktur Komposit Sandwich Pada Main Landing Gear UAV : Strength Analysis of Sandwich Composite Structures Main Landing Gear UAV Jauharul Akfiya sudjaelan; Sahril Afandi; Endah Yuniarti
Jurnal Teknologi Kedirgantaraan Vol 8 No 1 (2023): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v8i1.68

Abstract

Tricycle landing gear is a landing gear configuration on an aircraft with nose landing and main landing. Strength analysis of sandwich composites with impact loads aims to determine the maximum strength that can be resisted by sandwiches with several layers of lamina arranged with variations orientation fiber to obtain stiffness, to determine the type of damage caused by excessive loading. Fiber direction optimization was carried out to obtain optimal fiber direction variations in receiving loading, the optimal fiber direction was [(0)(45)(-45)(90)(0)]s with a significant Tsai-hill value from 0.091052752 to 0.057597845 after optimization. Simulation of impact loading with vertical velocity variations of 2 m/s, 3 m/s 4 m/s, 6 m/s, 8 m/s, 10 m/s, 12 m/s, 15 m/s using the finite element method by utilizing the Abaqus CAE software on the tricycle landing gear model and conducting tests to obtain large displacem ents, stresses and strains. By doing the test, it is found that the main landing gear structure is able to withstand a landing speed of up to 12 m/s with a large X-axis stress (S11) of 447.118 Mpa, a Y-axis stress (S22) 30.4995 Mpa, a shear stress of 26.2218 Mpa with a large a displacement of 11.9461 mm and a tsai-hill value of 0.5920. At a landing speed of 15 m/s the landing gear structure fails with a tsai-hill value that has passed the failure index 1, with a large X-axis stress (S11) 477.556 mpa, Y-axis stress (S22) 44.4075 Mpa, shear stress of 35 .2047 Mpa with a large displacement of 15.8297 mm and a tsai-hill value of 1.1336 where the landing speed of this landing gear structure failed, indicated by the tsai-hill value which had exceeded the failure index value 1. Keywords: Main Landing Gear, UAV, Drop Impact, CompositeSandwich.
PENGUKURAN TINGKAT KEBISINGAN PESAWAT CASA 212-200 SAAT GROUND RUN TEST BERDASARKAN VARIASI SUDUT Adam Wahyu Saputra Adam; Mufti Arifin; Ericko Chandra Utama
Jurnal Teknologi Kedirgantaraan Vol 8 No 1 (2023): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v8i1.70

Abstract

Noise is an unwanted sound, including sound that as a result of side effects from activities such as industrial and transportation activities. The greatest intensity of noise in the aircraft maintenance hangar environment is produced by the operation of the aircraft engine when it is ground or what is often called the Aircraft Ground Run Test. An This study was conducted by taking samples using CASA 212-200 aircraft equipped with a turboprop engine type. The measurement of noise generated by aircraft activity is measured using a tool such as the AS804 Sound Level Meter. This study aims to determine the intensity of aircraft noise when conducting a ground run test which is measured based on variations in the angle of measurement location to the source with a distance of 30 m based on an angular reference of 0o in front of the aircraft nose and 180o is behind the aircraft with a clockwise rotation. The measurement of noise levels is based on three references, namely LAmax, LAmin and LAeq. At idle the variation in the direction of the noise receiver which has the potential to produce the largest LAmax value at an angle (30o) of 97 dB. The lowest LAmin at an angle (180o) and (210o) of 84.6 dB. The largest LAeq at an angle (330o) of 95.3 dB. At the time of max power the variation in the direction of the noise receiver which has the largest potential LAmax value at an angle (45o) of 99.1 dB, the lowest LAmin at an angle (135o) of 94.8 dB. The highest LAeq at an angle (45o) of 97.8 dB.
Analisis Keterlambatan Penyelesaian C-check: Delay Maintenance Martina, Ayu; Suwondo, Edy; Yuniarti, Endah
Jurnal Teknologi Kedirgantaraan Vol 8 No 1 (2023): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v8i1.76

Abstract

PT XYZ is one of the air transportation companies in Indonesia that experienced delays in completing C-check maintenance based on a predetermined schedule. The TAT (Turn Around Time) indicator is used to measure the performance in completing the maintenance at PT XYZ. This research aims to determine the factors that cause maintenance delays on the B737NG aircraft and minimize TAT delays. This research uses fishbone diagrams and Pareto diagrams to find the root causes. There are three main factors that cause the delays, namely due to lack of manpower, the process of waiting for material supply, and the length of time to process the findings. In order to strengthen the analysis, this research uses the Define Measure Analyze Improve Control (DMAIC) method with the support of FMEA to develop a table for the RPN values or risk priority scale. The calculation results show that the highest RPN value is not paying attention on the ratio of work to manpower, which gives an RPN value of 216. Then a solution is recommended to reduce the RPN value to become value 168 where the aim is to reduce the TAT delay in completing the C-check maintenance of PT XYZ’s Boeing 737NG aircraft.
ANALISIS PERFORMA PESAWAT ATR 72-500 SEBAGAI PESAWAT CHARTER RUTE BANDARA HALIM PERDANAKUSUMA-MATAK DAN HALIM PERDANAKUSUMA- BADAK BONTANG FORTUNE JR OMBUH; Mufti Arifin; Endah Yuniarti
Jurnal Teknologi Kedirgantaraan Vol 8 No 1 (2023): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v8i1.81

Abstract

With the area and geography of Indonesia consisting of small islands, causing the difficulty of exploration efforts of Natural Resources (SDA) in these small islands. Companies that carry out these exploration activities must build supporting facilities to facilitate the exploration process in the area. The airport is one of the supporting facilities built by the company for exploration activities. The airport built by the company to support this air transportation, must be built according to the land and needs of the company, one of which is the runway. With limited runways, many companies use ATR 72-500 aircraft as charter aircraft to support exploration activities in areas far from commercial airports. Therefore, an analysis of the performance of the ATR 72-500 aircraft as a charter aircraft with the Route Halim Perdanakusuma Airport (HLP) -Matak (MWK) and Halim Perdanakusuma Airport - Badak Bontang (BXT) to determine operational costs. The performance of the ATR72-500 aircraft is seen from the take-off performance needed, range, fuel consumption, and payload. On the route HLP-MWK with 68 passengers traveled with a distance of 577 NM requires fuel as much as 2,456 kg with TOW 22,342 kg, while for take-off requires runway length of 1056 m, operating costs of Rp. 235.535.469, 92 and the cost per passenger is Rp. 3.463.756,91. For the route HLP-BXT with 68 passengers traveled with a distance of 742 NM requires fuel as much as 2.584, 862 kg with TOW 22.471 kg, while for take-off requires runway length of 1068 m, operational costs of Rp. 247.891.620, 16 and the cost per passenger is Rp. 3.645.465.
Analisis Keandalan Business Class Seat Terpasang Di Pesawat A330-200/300 Garuda Indonesia Aditia Kusuma Wibawa; Freddy Franciscus; Endah Yuniarti
Jurnal Teknologi Kedirgantaraan Vol 8 No 1 (2023): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v8i1.82

Abstract

From January 1, 2021 to June 30, 2021, the AIRBUS A330-200/300 aircraft belonging to PT Garuda Indonesia has experienced 36 cases of damage to the business class seat. These cases most often occur due to external factors on the seat. often damaged by crew of flight attendants as well as technicians working. In the study that discussed the factors that caused the failure of the recline mechanism on the B/E Aerospace Minipod Seat and B/E Aerospace MCX Diamond Seat, then aimed at finding a comparison of reliability and cost benefits with the fishbone method. From the results of the study, it was found that the reliability score obtained with the MAREP rate on the B/E Aerospace Minipod seat was 5.798/1000FH and the B/E Aerospace MCX Diamond seat was 5.551/1000FH. As for the maintenance costs, the results obtained on the B/E Aerospace Minipod require a total cost of US$ 9,587.59 with an average maintenance seat price of US$ 24.21/seat and B/E Aerospace MCX Diamond is US$ 5,134.24 with an average treatment seat of US$ 53.48/seat in beetwen 6 months.

Page 6 of 18 | Total Record : 179

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