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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 8 Documents
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Search results for , issue "Vol 7 No 1 (2022): Jurnal Teknologi Kedirgantaraan" : 8 Documents clear
Analisis Kerusakan Trim Air Pressure Regulating and Shutoff Valve Pada Pesawat Boeing 737-800 Menggunakan Metode Failure Mode and Effect Analysis (FMEA) Rizwan Maulana; Freddy Franciscus; Mufti Arifin
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.v7i1.48

Abstract

Air Conditioning (AC) is the one of system in aircraft to make a passanger and all cabin crew comfortable. Trim Air Pressure Regulating and Shutoff Valve or also known as Trim Air PRSOV is a component on the Boeing 737-800 aircraft to regulate flow of hot air constantly before entering the aircraft cabin. Refering to the data for the last 6 years, the replacement of the component belonging to one of the Indonesian national flight carrier using Boeing 737-800 aircraft was the occurance of 84 times the cooling system failure which caused the light indiacator in the cockpit to light up. Among them happened 70 times unscheduled maintenance and 14 times scheduled maintenance. Thus, this essay was made to analyze the causes of the damage that occurred to the Trim Air PRSOV. The method used in this research is Failure Mode and Effect Analysis (FMEA) is the technique used to find, identify and eliminate failures or damage to a system or process. The first step is to analyze using a Pareto diagram and then continue with the FMEA method so that an analysis of the damage that often occurs is damage to the diaphragm with 42% damage with an RPN value of 389.1, erosion on the ring seal with 22% damage with an RPN value of 376 and shaft seal damaged with 12% damage with an RPN value of 295.1 for it requires aggressive treatment. Therefore, repairs with a long TAT of 14 days are expected to increase the reliability of the PRSOV Trim Pressure component. For this reason, repairs are carried out with a long TAT of 14 days, it is hoped that there will be an increase in the reliability of the PRSOV Trim Pressure componen. 
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 Wind Tunnel Berbasis Digital Sebagai Media Pembelajaran Pada Program Studi Teknik Penerbangan Universitas Dirgantara Marsekal Suryadarma Tajuddin, Aswan; Hanafi, Ivan; Kusumohadi, Catur S.
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.v7i1.45

Abstract

Penelitian ini bertujuan untuk mengembangkan wind tunnel berbasis digital sebagai media perbelajaran untuk mendukung kegiatan praktikum mata kuliah aerodinamika. Metode penelitian yang digunakan adalah metode penelitian dan pengembangan (Research and Development) dengan model penelitian pengembangan Dick and Carey. Media pembelajaran berbasis digital ini telah melalui tahap uji validasi dengan rata-rata persentase secara keseluruhan tingkat validasi materi pada media pembelajaran adalah 87.96%. Dari perolehan tiga aspek yang dinilai secara keseluruhan tingkat validasi ahli media sebagai media pembelajaran pada ekstrakurikuler aerodinamika adalah 85.79 %. Dari hasil penelitian ini dapat disimpulkan bahwa media pembelajaran berbasis digital ini memenuhi persyaratan dengan kualitas sangat baik untuk digunakan sebagai media penunjang dalam kegiatan pembelajaran ekstrakurikuler aerodinamika.
Perbandingan Kebisingan Pesawat berdasarkan Waktu Operasional Bandara (Studi Kasus: Bandara Halim Perdana Kusuma) Syahputra, Bramantio Wijaya
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.v7i1.47

Abstract

Halim Perdana Kusuma Airport is 12 km from the center of Jakarta, has an area of ​​about 170 hectares, located in East Jakarta, there are many settlements around the airport that receive noise from airport operations. This study was made to determine the comparison of noise received by the community based on airport operating time. The study began with the determination of 3 measurement locations, namely on Jl. Kampung Baru 1, Jl. Amd XII, and Jl. Main Radar based on coordinates using GPS. The next step is to prepare a Sound Level Meter measuring device by installing it at a height of ± 200 cm. Measurements are made when without aircraft activity and with aircraft activity, the results of which will be used to obtain Leq and DNL values. By using measurement and calculation methods that have been adopted from Kep. Men. LH No.48 of 1996, so that at 3 points of measurement locations, it was found that aircraft noise was quite influential on residents living in settlements around the airport, where at Location 1 when there were no active aircraft, the DNL value dropped by 14.9 dB. 2 of 4.3 dB, and Location 3 of 9.2 dB. The DNL value obtained from the measurement results for Location 1 was 69.5 dB, Location 2 was 76.5 dB, and Location 3 was 71.1 dB. So that the DNL value in residential areas around the airport has exceeded the quality standard regulated in Kep. Men. LH No.48 of 1996, that is 55 dB.
Analisis Numerik Pengaruh Gasket pada Windshield Pesawat Komuter 19 Penumpang Terhadap Fenomena Bird Strike Laksono, Agung; Sitompul, Sahril Afandi; Suprianto, Agus; Fitriansyah, Rizky
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.v7i1.49

Abstract

Aircraft are currently quite popular transportation, due to its ability to utilize air space as a flight path, so that it can be efficient in mileage. To support the safety of airplane passengers, every component on the aircraft must pass the test. One of them in the aircraft windshields that are prone to collisions with other objects. In accordance with the regulations in the Civil Aviation Safety Regulation (CASR) the windshield must withstand the impact load of a 0,91 kg bird. In this simulation, the material shape of the bird uses the EOS Tabular type. For modeling windshields, frame¸ gaskets and birds use a general method for solid materials, namely the Lagrangian method. Rubber used as gasket material with mooney rivlin for modeling material behavior. the polymethyl methacrylate and aluminum alloy 7075 T6 material is used in the windshield and frame. Numerical modeling is validated using analytical results. The gasket thickness of 2 mm produces the most optimum energy absorption. The use of gaskets on the windshield does not have a significant effect on the windshield because the gasket on average is only able to absorb 5% of the total energy absorbed by all windshield parts. The collision parameter that produces the greatest failure occurs at a speed of 87,5 m/s with -15o angle. The area that is most prone to material failure is in the area of the upper bolt hole.
Analisis Aerodinamika pada Sayap JABIRU J430 dengan Penambahan Vortex Generator menggunakan Metode CFD
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.v7i1.50

Abstract

Jabiru J430 aircraft is a type of light aircraft produced by the Jabiru aircraft manufacturer with four passenger seats which has a length of 6550 mm and a height of 2200 mm with a high wing type with additional winglets. This study aims to determine the effect of installing a vortex generator on the upper surface of the Jabiru J430 aircraft wing on aerodynamic characteristics, especially at critical angle conditions. As it is known that the vortex generator functions to produce a vortex in the air flow on the upper surface of the wing so that it can delay the occurrence of flow separation and improve the performance of the wing. In this study, a comparison was made between the aerodynamic characteristics of the wing without a vortex generator and the addition of a vortex generator. The vortex generator used is a flat plate vortex with a counter-rotating configuration. From the simulation results, it can be seen that the airflow characteristics on the wings using a vortex generator are more stable when compared to airfoils without a vortex generator and it can be seen that the increase in the maximum lift coefficient from CL 0.997 (20 angle of attack) to CL 1.126 (angle of attack 24º) or an increase of 12.9%, and an increase in the drag coefficient occurs as the angle of attack increases.

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