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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 PERFORMA ENGINE MARCHETTI SF 260 Bismil Rabeta
Jurnal Teknologi Kedirgantaraan Vol 4 No 2 (2019): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v4i2.272

Abstract

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 KEKUATAN STRUKTUR SISTEM MEKANIK PESAWAT SINAR-X DIGITAL Ahmad Zayadi; Marsudi; Cahyono Her Prasetyo
Jurnal Teknologi Kedirgantaraan Vol 4 No 2 (2019): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v4i2.273

Abstract

Analysis of structural strength of mechanical systems on digital x-ray devices. This research is very important to know the strength and quality of the structure of mechanical system of digital x-ray plane. To research analysis strength structure system mechanical calculation methods were used counting stress, bending stress; the safety factor a tool, and calculate deflection occurring in structure.The result of his research or: the bending stress at order holders catcher of = 7,07 N/mm2, while the bending stress is equal to = 141,9 N/mm2. The bending stress on the tube holder is as big as = 7,8 N/mm2, while the bending stress is equal to= 141,9 N/mm2. Stress von mises in order arms part burden a counterweight of = 19,44 N/mm2, while the value of the safety factor is n = 11,05. Stress von mises in order to arms a part of encumbering tube = 18,41 N/mm2, while the value of the safety factor is n = 11,67. Bending stress happened to column of order = 22,60 N/mm2, while the bending stress is equal to = 141,9 N/mm2. The ball screw move of the operation Fbm = 777,9N. Bending stress occurred on the basis of order = 21,43 N/mm2, while the bending stress is equal to = 141,9 N/mm2. Based on the data has obtained, then structure mechanical system plane digital sinar-x expressed safe and strength.Analysis of structural strength of mechanical systems on digital x-ray devices. This research is very important to know the strength and quality of the structure of mechanical system of digital x-ray plane. To research analysis strength structure system mechanical calculation methods were used counting stress, bending stress; the safety factor a tool, and calculate deflection occurring in structure.The result of his research or: the bending stress at order holders catcher of = 7,07 N/mm2, while the bending stress is equal to = 141,9 N/mm2. The bending stress on the tube holder is as big as = 7,8 N/mm2, while the bending stress is equal to= 141,9 N/mm2. Stress von mises in order arms part burden a counterweight of = 19,44 N/mm2, while the value of the safety factor is n = 11,05. Stress von mises in order to arms a part of encumbering tube = 18,41 N/mm2, while the value of the safety factor is n = 11,67. Bending stress happened to column of order = 22,60 N/mm2, while the bending stress is equal to = 141,9 N/mm2. The ball screw move of the operation Fbm = 777,9N. Bending stress occurred on the basis of order = 21,43 N/mm2, while the bending stress is equal to = 141,9 N/mm2. Based on the data has obtained, then structure mechanical system plane digital sinar-x expressed safe and strength.
Analisis Lintasan Terbang Roket Model Satu Tingkat Dengan Berbantuan Perangkat Lunak Tri Susilo; Aris Widodo
Jurnal Teknologi Kedirgantaraan Vol 5 No 1 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v5i1.274

Abstract

This paper provides an explanation of the computational and analyses of flight line for single stage rocket model. There are two software’s used are that Visual Basic 6.0 to flight line analytic and MatCad 2000 to get the figure of position and flight history. The rocket analyses are including the maximum flight altitude, velocity, position, mass comparison, jet velocity, specific and total impulse on every altitude. The conclusion obtained is that the Rocket reaches its highest point (culmination point) at an altitude of 31,589.66 meters within 178.13 seconds after the rocket starts launching. The rocket section at an altitude of 17,772.49 meters in 11.23 seconds will experience a dead spot and will glide at Voff speed to the peak point (culmination point).
ANALISIS KINERJA PEMELIHARAAN BERDASARKAN SAFETY PERFORMANCE INDICATOR MENGGUNAKAN RELIABILITY MAPPING Mufti Arifin
Jurnal Teknologi Kedirgantaraan Vol 5 No 1 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v5i1.275

Abstract

–ICAO Annex 19 Safety Management required safety measurement using Safety Performance Indicator (SPI). SPI parameter determined by operator. One of example is maintenance parameter related with accident or incident. SPI maintenance consist of Pilot Report, Dispatch Reliability, Deferred Maintenance (DMI), Service Difficulty Report, Air Turn Back, Rejected Take Off, and Repeated Defect. Some of SPI parameters have correlations. Simulation using reliability mapping with varies maintenance scenario to see correlation between Deferred Maintenance Item, Repeated Defect, and Technical Interruption which is used for Dispatch Reliability calculation has been done. Maintenance performance analysis also simulated with this method. The result shows cause effect correlation in two and one way between three SPI parameters. Maintenance performance could be predicted using reliability mapping mainly for time needed for defect rectification and repeated defect, repeated DMI, or repeated technical interruption
Analisis Konsep Circular Airport Untuk Wilayah Kepulauan Indonesia Freddy Franciscus; Aprilia Sakti K
Jurnal Teknologi Kedirgantaraan Vol 5 No 1 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v5i1.276

Abstract

The Circular Airport Concept, issued by Hessellink in 2014, attracted the attention and differed opinions of airport experts. Until now this project is still ongoing. This paper makes a preliminary analysis of the application of the concept of a circular airport in the Indonesian Archipelago. Building an airport in a limited area is a big challenge. Development of several pioneering routes that connect the regions with small aircraft continues to be done. Another challenge in airport construction is environmental sustainability. The circular airport concept is expected to be the right solution for the Indonesian Archipelago. Discussion included technical and safety analysis related to airport design, aircraft characteristics, Air Traffic Management [ATM} and also analysis of the environment and regional population to be developed.
RANCANG BANGUN SISTEM PEMANTAUAN GETARAN KERETA REL LISTRIK COMMUTER LINE SECARA ONLINE Erna Kusuma Wati; Fraska Anangga
Jurnal Teknologi Kedirgantaraan Vol 5 No 1 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v5i1.277

Abstract

Dense settlements around the railroad track need a vibration monitoring device that can monitor the acceleration of vibrations. The level of risk of exposure to waves can cause health problems. A vibration measuring device can determine the acceleration value of a passing KRL vibration so that it can be as a reference in establishing settlements. This research has succeeded in designing a KRL vibration measurement system and can display it online, using the ADXL345 accelerometer sensor, Arduino Uno board, and ESP8266 Module. The sensor will detect changes in vibration around the railroad tracks when passed by a passing train. Furthermore, the data is sent to the webserver using the ESP8266 Module. The impact of vibrations generated by the moving train can cause health problems in the long run with a distance of ± 5 meters from the railroad tracks. The wave to show with the most substantial value at a distance of 1 meter from the railroad was 0.983507 m / s², at a distance of 5 meters from the railroad was 0.491333 m / s², At a distance of 9 meters from the railroad was 0, 12 m / s², and at a distance of 13 meters from the railroad tracks of 0.026 m/s.
DEVELOPMENT OF RETURN TO BASE FLIGHT TRAJECTORY GENERATOR BASED ON DUBINS PATH – VECTOR FIELD METHOD Neno Ruseno; Muhammad Royyan; Prianggada I. Tanaya
Jurnal Teknologi Kedirgantaraan Vol 5 No 1 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v5i1.278

Abstract

In a Return to Base (RTB) situation, aircraft needs to immediately fly back to its origin airport. Since there is no published flight procedure for an RTB, an Air Traffic Controller (ATC) will assist the pilot for the flight procedure to fly. The objective of this work is to generate a flight trajectory in RTB situation based on the available airport flight procedures (departure and arrival) in Kertajati airport. The Dubins Path was used as a method to generate the flight trajectory and supported by the Vector-Field Methodology. The Python programming simulation was used to simulate the flight trajectory generation in the normal condition, second closest waypoint condition, and different parameters value condition. The trajectory was simulated based on flight characteristic of a single engine aircraft (Cesna 172) and multi-engine aircrafts (Boeing 737-800NG). The simulation results show that the Dubins Path and Vector-Field methodology success to generate the flight trajectory in different types of condition and parameters. The increase in aircraft velocity and the decrease in aircraft bank angle caused an increase in the aircraft turning radius. While, the decrease in aircraft flight path angle caused increase in the length of Dubins Path line.
Simulator Pesawat Melewati VHF Omnidirectional Radio Range (VOR) Ariawan D. Rachmanto; Iswanto
Jurnal Teknologi Kedirgantaraan Vol 5 No 1 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v5i1.279

Abstract

Commercial airplane flights always follow the flight plan that was made, the flight plan was made by the pilot based on the existing airways. Airways connects airports with VOR/DME, where VOR/DME in flight are known as air navigation equipment. VOR/DME is needed by a pilot so that he does not lose direction so that the aircraft can fly to the destination airport. The HSI instrument provides visualization of bearing, course, from to and destination VOR/DME deviations. Information from HSI is information that the pilot uses to get to the next VOR/DME. The purpose of this research is to make an aircraft movement simulation software approaching VOR, a software development method using the Prototype model by looking at existing devices. Simulation and modeling are done by placing VOR/DME at latitude and longitude in accordance with the location on land, then modeling the location of VOR/DME using MapX4.5 map, air conditioned flight at the specified airport, HSI instrument is modeled using GL Studio, using language C # programming, Indonesian VOR/DME data and Indonesian airports are stored in Excel. The calculation results are then visualized on the HSI instrument, the instrument visualization results are compared with the Garmin Integrated Flight Deck (GIFD) Trainer, version 14.01 under the same conditions.
Analisis Pengaruh Winglet Pada Sayap Pesawat Cessna 172 Menggunakan Perangkat Lunak XFLR5 Bismil Rabeta; Fauzan Taufik Hidayat; Freddy Franciscus
Jurnal Teknologi Kedirgantaraan Vol 5 No 1 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v5i1.280

Abstract

Innovations on aircraft wings always continued in order to achieve better wing efficiency. Especially to optimalization wing shape and reduce induce drag on aircraft by adding device called winglet. This research conduct a study to determine the effect of winglet when adding on Cessna 172 wing. Winglet has a purpose to increase wing’s efficiency by reducing induce drag and increase ratio between lift coefficient and drag coefficient. The test object is modification Cessna 172 wing that modeled with cant angle variation 0°, 30°, 60°, and 90°using software XFLR5. The result shows that wing modification with 30° cant angle winglet has the highest CL/CD ratio about 24,728 with optimum value at 2.5° angle of attack.
ANALISIS NUMERIK EFEK TUMBUKAN DAN POLA DEFORMASI CRASH BOX BERBENTUK ORIGAMI Bismil Rabeta; Sahril Afandi S; Romario Fransisco
Jurnal Teknologi Kedirgantaraan Vol 5 No 1 (2020): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v5i1.281

Abstract

Crash box is a longitudinal bar integrated with a bumper of the car is used to absorp the energy due to collision through a process of deformation (progressive buckling). The purpose of this analyis is to determine the response of the crash box when the subject to collision load with low speed. In addition, this analysis is also to determine the value of Pmax (peak force) against the geometry variations of the crash box that produce the value of theforce on the displacement and as a reference to determine the value of mean crushing force (Pmean) and crushing force efficiency (CFE). Every models has a different the value of mean crushing force (Pmean) and crushing force efficiency (CFE). In model 1 has a Pmean value of 12.976 kN and a CFE value of 0.584, Model 2 has a Pmean value of 10.458 kN and a CFE value of 0.789, and Model 3 has a Pmean value of 9.282 kN and a CFE value of 0.798.

Page 14 of 17 | Total Record : 166

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