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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 166 Documents
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Analisis Kerusakan Kepala Silinder Blok Mesin Pada Kendaraan Jenis Minibus Kapasitas 1500 CC Ahmad Zayadi; Sungkono; Masyhudi
Jurnal Teknologi Kedirgantaraan Vol 8 No 2 (2023): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v8i2.79

Abstract

Four-wheeled vehicles are one of the commonly used modes of transportation. The vehicle engine has a cylinder head to place the valves and cooling mantle. Damage to the cylinder head will disrupt the engine's working system for a long time. The damaged  will take a long time for the repair process. The cylinder head is usually damaged at a milage of 80,000 km. The damage experienced by the cylinder head is the emergence of a rough sound in the engine, the mixing of cooling water into the combustion chamber and the temperature rises quickly, in this study a study will be conducted on the damage that occurs to the cylinder head. Based on the results of macrostructure testing, corrosion occurs due to engine cooling fluid, besides that there is a deposit that is very strong and corrosive to the cylinder head on the engine block, microstructure testing shows the presence of (black) deposits which are thought to affect the corrosion process, dendrite grains and rods in the microstructure do not change grain size. Based on the hardness test results show the hardness value of the damaged surface of 102.22 HV and the hardness value of the undamaged surface of 102 HV based on the damage to the engine block cylinder head is not caused by material deformation due to mechanical and thermal loads. The results of the chemical composition test of the cylinder head that was damaged decreased Al 1.1%, Si 0.11%, Cu 0.37, Fe 0.088% and Mg 0.081% and the decrease in the chemical composition of the constituent elements of the material was caused by the interaction of water with the surface of the cylinder head which was characterized by the formation of oxides of Al, Si, Cu, Fe, and Mg. Based on the test results, cylinder head damage is more due to lack of maintenance of the engine block.
KONSEP DESAIN KAPAL UDARA SEBAGAI TRANSPORTASI MASSAL UDARA DI WILAYAH JABODETABEK Riyan Eko Prasetiyo; Michael Tobing; Sovian Aritonang; Novsky Asmoro; Gita Amperiawan
Jurnal Teknologi Kedirgantaraan Vol 8 No 2 (2023): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v8i2.80

Abstract

The existing mass transportation cannot accommodate Jakarta’s population increase. The Central Statistics Agency stated that the number of vehicles in Jakarta in 2022 was 26.370.535. The high level of vehicle mobilization results in vehicle congestion in Jakarta. For this reason, it is necessary to have a mode of mass transportation to be a solution to solving congestion. Airships are air mass transportation with a propulsion system consisting of gas and engines. The design of the mode of transportation is carried out using a quantitative method through a literature review approach and numerical formulation analysis. The resulting airship designs have a capacity of 40 people, a total load of 9764 kg, balloon dimensions of 46 m x 13 m x 18 m, and gondola dimensions of 11 m x 4 m x 2m. This research provides a study of the design of mass transportation modes with air operations, which can be a solution to the congestion that occurs. Can reduce existing congestion with efficient routes for the mobilization process at work time.
ANALISIS KORELASI USIA PESAWAT AIRBUS A320-200 TERHADAP JUMLAH KOROSI YANG TIMBUL MENGGUNAKAN METODE KORELASI PEARSON PRODUCT MOMENT Reynaldo Mulya Tedja; Mufti Arifin; Erna Shevilia Agustian
Jurnal Teknologi Kedirgantaraan Vol 8 No 2 (2023): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v8i2.83

Abstract

Corrosion is the destruction of materials caused by the environment, where metals separate from their metal atoms and form compounds from water or gas, resulting in oxidation until the metal atoms disappear. Corrosion can also be referred to as material that is damaged by the environment and is mostly caused by natural impacts that increase as the age of the aircraft increases. Failure to maintain the strength of the main structure is caused by excessive stress that occurs in the corrosion area resulting in cracks in the structure. Due to the frequent occurrence of corrosion in the aircraft, observations, data analysis and further literature studies were carried out. This study aims to determine the relationship between aircraft aging and the amount of corrosion found during periodic "c-check" servicing of Airbus A320-200 aircraft at the study site. The research method that used in the discussion of this thesis is to use pearson product moment correlation analysis on age data and the amount of corrosion that occurs on each aircraft. The conclusion of the results is analysis using the Pearson product moment method on 30 sample aircraft, the correlation 0.922 is categorized as having a very strong relationship. Each aircraft section does not have a strong correlation between corrosion and age, but as a whole has a strong correlation with age. From the results of the analysis using the linear regression equation, it can be identified and estimated the amount of corrosion that occurs at a certain age on the Airbus A320-200 aircraft. The results of the linear regression equation show that the aircraft is 23 years old, the amount of corrosion that will arise is estimated at 39 points, it can be concluded that aircraft with XU-029 registration are known to have a total corrosion rate of 42 points with poor corrosion conditions, then when compared to aircraft with registration XU-030 which is 23 years old is also known to have a corrosion rate of 30, so it can be concluded that the corrosion conditions on this aircraft are better than expected.
ANALISIS KEANDALAN SKIN AIR OUTLET VALVE 22HQ PADA PESAWAT AIRBUS 320 DI MASKAPAI BBB Harun Alrasid; Mufti Arifin; Aprilia Sakti
Jurnal Teknologi Kedirgantaraan Vol 8 No 2 (2023): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v8i2.85

Abstract

Setiap komponen elektronik yang terpasang pada pesawat menghasilkan panas yang harus dikontrol agar setiap komponen elektronik dapat berkerja dengan baik dan menghindari terjadinya panas yang berlebih. Panas yang dihasilkan oleh komponen elektronik pada pesawat Airbus 320 didinginkan oleh sistem Avionic Equipment Ventilation (AEV). Salah satu komponen AEV ialah Skin Air Outlet Valve yang merupakan katup pembuangan udara panas, katup ini harus tertutup ketika terbang dan terbuka ketika pesawat di darat (suhu skin lebih dari 12 derajat celcius). Jika terjadinya kegagalan pada katup utama dan terbuka ketika pesawat terbang, maka sistem pressurization akan terganggu dan menyebabkan operational interruption seperti Rejected Take-Off (RTO), In-Flight Turn Back (IFTB), Return To Apron (RTA) dan bahkan Aircraft On Ground (AOG).  Perlunya analisis keandalan serta menentukan langkah-langkah yang tepat agar operational interruption dapat diminimalisir. Dengan menggunakan metode perhitungan Alert Level, MTBUR, serta metode Root Cause Analysis (RCA), didapatkan hasil grafik CURR yang melebihi batas AL pada bulan Mei 2022 dan nilai tertinggi MTBUR adalah 9935,63 FH dan nilai terendahnya adalah 5672,26 FH. Terlihat MTBUR dari SAOV maskapai BBB berada dibawah dari MTBUR worldwide dan guarantine MTBUR. Hasil dari perbandingan ini memperlihatkan keandalan dari komponen SAOV yang buruk. Faktor utama penyebab gagalnya Skin Air Outlet Valve (SAOV) menutup saat penerbangan berlangsung diketahui adanya beberapa kesalahan yang disebabkan oleh faktor kelalaian dan prosedur yang kurang detail. Adapun tindakan korektif yang dilakukan seperti penambahan prosedur pemeriksaan dan catatan pada dokumen MEL, merekomendasikan overhaul setiap 7000 FH dan rekomendasi untuk setiap engineer yang melakukan perawatan supaya mengikuti langkah-langkah pada AMM. 
ANALISIS PERFORMA TAKEOFF PADA PESAWAT ATR 72 DALAM PENGARUH TAILWIND Dwiki Fahreza Andreanto; Mufti Arifin; Freddy Franciscus; Evi Endarti
Jurnal Teknologi Kedirgantaraan Vol 8 No 2 (2023): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v8i2.86

Abstract

Information on weather conditions is needed to support flight safety, especially in the process take-off. One of the required weather information is wind data, wind direction and wind speed. One of the wind components is the tailwind(wind from behind). In the small airports it can only be visited by aircraft such as ATR72 and its kind, due to the limited availability of runways and currently many of these airports are still using landing and take-off in the direction of thewind. This can result in a lack of lift during take-off during the tailwind conditions. To prevent this from happening, there is a reduction in the capacity of the aircraft. The purpose of this study was to analyze the performance of the ATR72 aircraft during take-off with tailwind conditions. By calculating the takeoff under normal conditions on the ATR72 aircraft then varying the tailwind speed. The results obtained are the value of the ground roll distance  (????????) and the reduction in aircraft weight (????) at the time of tailwind. a speed tailwind of 0 or normal, obtained a distance of ground roll 849 m, take-off weight of 20948 kg, reduction in aircraft weight of 0. Speed tailwind of 5 kts, distance of ground roll 773 m, take-off weight of 20333 kg, reduction in aircraft weight of 615 kg, while speed of tailwind 10 kts obtained distance of ground roll 697 m, take-off weight of 19308 kg, reduction in aircraft weight of 1640 kg, and speedtailwind of 15 kts, distance of ground roll 621 m, take-off weight of 18225 kg, was obtained. reduction in aircraft weight by 2723 kg.
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.
Rancang Bangun Alat Peraga Up Lock Box Pada Nose Landing Gear Pesawat ATR 72 Untuk Media Pembelajaran Septian, Diaz; 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.v7i2.54

Abstract

Abstract - Airplane is a very important mode of transportation, one of which is ATR aircraft. In this study, the type of aircraft used was the ATR 72-600 aircraft. One of the safety factors that need to be considered on aircraft is the landing gear system. The landing gear system regulates the wheel system on the aircraft for landing and also taking off. Given the importance of ensuring that the plane's wheels are securely locked or not, an up lock box system is needed on the landing gear. In the Up Lock Box system, it is not directly visible from the outside so that the working mechanism is not widely known. This study aims to determine the workings of the up lock box nose teaching aid system on the landing gear and to make a trial up lock box nose teaching aid on the landing gear. The research method begins with a literature study, then looks for design references, namely from the ATA 32 training manual. After that, make a design using the image of the up lock box from the ATR 72 aircraft, assemble the demonstran tool, calibrate and test the demonstran tool. The conclusions in this study are, how the up lock box teaching aids work in accordance with the up lock box working concept in the training manual, the results of the design and manufacture of props accompanied by modifications, as well as the test results on up lock box props in accordance with the up lock work concept box. The size of the props that have been made has a length of 37.8 cm and a width of 16.2 cm.

Page 7 of 17 | Total Record : 166

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