cover
Contact Name
Endah Yuniarti
Contact Email
endah.yuniarti13@gmail.com
Phone
-
Journal Mail Official
ftkunsurya@gmail.com
Editorial Address
-
Location
Unknown,
Unknown
INDONESIA
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN
ISSN : 25282778     EISSN : 26849704     DOI : -
Core Subject : Engineering,
Jurnal ini 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, sistem transportasi penerbangan dan topik-topik yang berkaitan dengan engineering. Tujuan utama dari Jurnal Teknologi Kedirgantaraan adalah mempublikasikan hasil penelitian yang dilakukan dan memotivasi produktivitas karya ilmiah dalam bidang keteknikan secara umum dan teknik Penerbangan/Aeronautika secara khusus.
Arjuna Subject : -
Articles 6 Documents
Search results for , issue " Vol 4, No 2 (2019): JURNAL TEKNOLOGI KEDIRGANTARAAN" : 6 Documents clear
ANALISIS PERFORMA ENGINE MARCHETTI SF 260 Rabeta, Bismil
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 4, No 2 (2019): JURNAL TEKNOLOGI KEDIRGANTARAAN
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

Show Abstract | Original Source | Check in Google Scholar | Full PDF (831.627 KB) | DOI: 10.35894/jtk.v4i2.315

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 Zayadi, Ahmad; sudi, Mar
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 4, No 2 (2019): JURNAL TEKNOLOGI KEDIRGANTARAAN
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

Show Abstract | Original Source | Check in Google Scholar | Full PDF (667.303 KB) | DOI: 10.35894/jtk.v4i2.316

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.
ESTIMASI DISTRIBUSI BERAT SAYAP DAN DISTRIBUSI LIFT UNTUK OPTIMASI BENDING MOMENT DENGAN SISTEM FUEL TRANSFER PADA PESAWAT BOEING 737-500 Arifin, Mufti; Yuniarti, Endah; Sari, Rafika Arum; Said, Ahmad Akmal
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 4, No 2 (2019): JURNAL TEKNOLOGI KEDIRGANTARAAN
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

Show Abstract | Original Source | Check in Google Scholar | Full PDF (1101.347 KB) | DOI: 10.35894/jtk.v4i2.310

Abstract

Aside from being a manufacturer of lift force, a wing is functioning hold the load that occurs in the structure of the aircraft, such as the shear load, twist and bending. Of all the load the load bending is the greatest burden are received by the wings. Setting the load bending is one of the major factors in reducing the burden experienced by the wing. However, the optimal value indicated opposite between on land and in the air, to take advantage of the situation to use fuel system transfers the load alleviation. Fuel transfer load alleviation is a system that automatically move the fuel more in the tank at the time in part on land and are on the outside of the tank at the time in the air so that the effect of the load bending bending loads can be reduced, which generated as the result of addition between the weight distribution and the distribution of lift that occurs on the wings so as to calculate the bending data needed weight distribution and the distribution of lift on the wing. This research aims to know the weight distribution occurs on the wings of the Boeing 737-500. The value of the weight distribution and distribution of lift yield optimization moment on two States namely, on land and in the air with three variations of the fuel transfer that is, constant with a value of 40134.53 N, linear with a value of 48059.53 N, and the maximum value of 172386.50 N.
PENGARUH PEMODELAN SMOOTH PARTICLE HYDRODYNAMICS UNTUK APLIKASI SIMULASI NUMERIK BIRD STRIKE DI LEADING EDGE S, Sahril Afandi; Franciscus, Freddy; Afrianto, Muhammad Faisal
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 4, No 2 (2019): JURNAL TEKNOLOGI KEDIRGANTARAAN
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

Show Abstract | Original Source | Check in Google Scholar | Full PDF (977.475 KB) | DOI: 10.35894/jtk.v4i2.312

Abstract

Accidents due to bird strike often occur in flight operations and during the migratory period of birds, this can cause structural failure and threaten flight safety. The effect that occurs on the structural components of the aircraft affected by the collision of the bird hit is generally in the form of dent deformation or the perforation of the plane's skin layer and other structures. This study discusses bird strike in Leading Edge with SPH (smooth particle hydrodinamics) method based on finite element method. Leading Edge structure is assumed to only consist of skin by varying 4 bird speeds, namely: 75 m / s, 100 m / s, 125 m / s and 150 m / s, and 2 angular variations of 0o and 45o. The simulation results show the deformation of Leading Edge increases with increasing speed, and the impact force is higher in the direction of the 0o collision for each of the same speed. The maximum impact force at each speed for the collision direction is 0o and 45o in the range of 6 - 17 kN and 3 - 12 kN. While the maximum displacement results at each speed for collision directions are 0o and 45o in the range 148 - 336 mm and 89 - 198 mm.
ANALISIS NUMERIK DISTRIBUSI TEKANAN & KECEPATAN ALIRAN UDARA PADA FUSELAGE B737-9 MAX Susilo, Tri; Rabeta, Bismil; Falah, Fikry
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 4, No 2 (2019): JURNAL TEKNOLOGI KEDIRGANTARAAN
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

Show Abstract | Original Source | Check in Google Scholar | Full PDF (1127.078 KB) | DOI: 10.35894/jtk.v4i2.313

Abstract

Aerodynamic characteristics can be known by using computational Fluid Dynamics (CFD) methods. This study analyzes the pressure distribution and velocity of air flow on Fuselage B737-9 MAX using the Computational Fluid Dynamics (CFD) method with variations in attack angles of 0o, 15o, 30o and 45o. The results obtained are at 0o attack angle, 15o the difference in speed and pressure is not too significant or normal, while at the attack angle 30o and 45o the difference in speed and pressure is very significant or abnormal because the air flow at that angle experiences turbulence around the fuselage.
REVIEW KLASTER MRO DI INDONESIA DAN STRATEGI PENGEMBANGANNYA Franciscus, Freddy
JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN Vol 4, No 2 (2019): JURNAL TEKNOLOGI KEDIRGANTARAAN
Publisher : JTK: JURNAL TEKNOLOGI KEDIRGANTARAAN

Show Abstract | Original Source | Check in Google Scholar | Full PDF (478.87 KB) | DOI: 10.35894/jtk.v4i2.314

Abstract

The MRO market in Indonesia is growing quite high at around 9.2% per year up to 2025, number 2 (two) after India which has an MRO market growth rate of around 10.0% per year and above China with a growth rate of around 8 .7% per year. In 2018 the Indonesian MRO market is around 1 Million US $ and only absorbed by Indonesian MRO around 30%. Most of the 70% portion of the markets that are not absorbed are the engine maintenance and component maintenance. Meanwhile, most existing MRO Indonesia is a cluster of engines and component maintenance. There is an absorption anomaly in Indonesia MRO market. The cause of the anomaly are lack of capability and capacity of Indonesia's MRO, the quality of MROs are not international standard, lack of the quantity and quality of technicians and the value chain of aircraft spare parts procurement is inefficient. The short-medium term strategies are to develop the capability and capacity of existing MROs, especially engine and component maintenance B737-800 / 900, A320-200 and ATR 42/72. Improve the quality of MRO. Improve the quality & quantity of technicians. Increasing the value chain efficiency in the procurement of aircraft spare parts. The long term strategy is to build Aerospace Park in West, Central and East Indonesia.

Page 1 of 1 | Total Record : 6