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Vortex
Published by Institut Teknologi Dirgantara Adisutjipto
ISSN : 27216152     EISSN : 30217601     DOI : https://doi.org/10.28989/vortex
Core Subject : Science, Engineering,
Aerospace Engineering Earth & Planetary Sciences Energy Materials Science & Nanotechnology Mechanical Engineering
Vortex merupakan jurnal ilmiah dalam diang dirgantara dengan cakupan Perancangan Pesawat Terbang, Perawatan Pesawat Terbang, Operasi Penerbangan, Mesin Pesawat Terbang dan Elektronika Penerbangan
Arjuna Subject : Ilmu Material (semua kategori) - Logam dan Paduan Logam
Articles 7 Documents
 1 
Search results for , issue "Vol 1, No 1 (2020)" : 7 Documents clear
ANALISIS TERBANG MELUNCUR (GLIDE FLIGHT) PESAWAT TERBANG STTA-12MXA bahrun bahrun; Bangga Dirgantara Adiputra
Vortex Vol 1, No 1 (2020)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (388.329 KB) | DOI: 10.28989/vortex.v1i1.725

Abstract

In designing the STTA-12MXA aircraft, analysis of the ability of the glide is one of the important aspects. The analysis was carried out using a numerical approach. There are 2 scenarios used to see the ability of the glide, namely the maximum distance and maximum flight time. The results showed that the maximum distance that the STTA-12MXA aircraft could reach when glide from 13500 ft is 64 km and for the maximum flight time is 23 minutes.
ANALYSIS OF SUPPLY COMPONENT OF BETA VALVE, BLEED VALVE AND PROPELLER REDUCTION GEARBOX Ririn Isnawati
Vortex Vol 1, No 1 (2020)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (353.463 KB) | DOI: 10.28989/vortex.v1i1.701

Abstract

Maintenance  is  a  very  important  thing  to  do  in  order  to  keep  the  aircraft  in flightworthiness. One form of maintenance activity is the replacement of components that have been damaged (failed). Inventory components can not be a avided because to get it can not be done  suddenly  while  for  those  needs  can  occur  suddenly.  Thus,  it  is  necessary  to  plan  the number  of  component  inventories  so  that  smooth  production  is  maintained.  Efforts  to  solve these problems use the Mean Time Between Removal (MTBR) equation. Where MTBR is used to determine inventory levels and component replacement scheduling. In addition, the MTBR is a formula or model to determine how much inventory per year will minimize the depletion of  inventory  in  the depository  and  for  estimating  component  replacement.  From  the  data processingof the G120 TP-A GROB, the number of component inventories in one year is based on  the  age  of  components  from  manufacture (MTBRStandard),  among  others:  10  Beta  Valve Components, 17 Bleed Valve Components, and 13 Propeller Reduction Gearbox Components
THE FAILURE OF AIR CONDITIONING SYSTEM IN B737NG AIRCRAFT Anindia Istikomah
Vortex Vol 1, No 1 (2020)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (500.048 KB) | DOI: 10.28989/vortex.v1i1.722

Abstract

The analysis done by the FMEA and RCFA methods shows that the main cause of the damage because of the accumulation of impurities. And it often occurs in the Heat Exchanger (Hx) component. In Indonesia with the special condition  where the air has a relatively higher humidity and air temperature, it is recommended to clean the heat exchanger more frequently to prevent dirt build up and avoid the problem of AC in producing hot air on the ground. In the standard maintenance manual the heat exchanger must be cleaned with 2000 FC (Flight Cycle) intervals, then the heat exchanger cleaning interval is changed to around 1000 FC (Flight Cycle) based on calculations performed by GMF
RELIABILITY LEVEL ON AFCS ACTUATOR COMPONENT OF THE SIKORSKY S-76 HELICOPTER Aryanti Dwi Puspita; Sri Mulyani; Karseno KS
Vortex Vol 1, No 1 (2020)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (504.629 KB) | DOI: 10.28989/vortex.v1i1.716

Abstract

The use of helicopters is very useful for Indonesia's natural conditions which is in the form of islands. In order to support the helicopter's capabilities, an AFCS actuator or automatic flight control system actuator is needed to make the flight automatically. Therefore, the author tries to conduct a reliability analysis to determine the level of reliability of the AFCS Actuator component in S-76 helicopter. The method used to conduct the analysis is the Weibull distribution method, which is one of several methods that are often used. The main objective is to determine the level of reliability and characteristics of the failure modes that often occur in these components. By analyzing at the results of calculations and types of failures, it can be seen the types of effective treatments to be applied to the AFCS Actuator component.
SIMULATION OF MISSILE LAUNCH USING SUKHOI SU-35 AND VYMPEL R-73 3D MODELLING Federiqo Ervan Novianto Dagomes; Nurcahyani Dewi Retnowati; Anggraini Kusumaningrum
Vortex Vol 1, No 1 (2020)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (931.757 KB) | DOI: 10.28989/vortex.v1i1.702

Abstract

The simulation is the operations imitating technique or processes that occur in the system and media, which can speed up the understanding of many things including missile launches. Missile launch simulation process on combat aircraft can be operated using computer simulation and application. The simulation is created using unity program and its buttons tested work fine. The results were tested with 10 questions to 10 flight department respondents. The data which is got showed 70.6% approached the process and missile launch function.
ANALYSIS OF THE EFFECT OF BYPASS RATIO ON PERFORMANCE ENGINE CFM56-5A1 IN CRUISING CONDITIONS opri surya yustinoto
Vortex Vol 1, No 1 (2020)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (275.192 KB) | DOI: 10.28989/vortex.v1i1.717

Abstract

The value of engine performance is known to decrease and increase with increasing and decreasing variation of the value of the parameter bypass ratio, so that if the value of these parameters is greater, then the fuel consumption when the aircraft operates will be less and the thrust will decrease. In addition to changing the value of the specific fuel consumption due to the influence of the bypass value, variations in altitude are also very influential where the higher the aircraft, the resulting specific fuel consumption value will be smaller 
THE EFFECT OF BLEED WATER ON JT8D-15 ENGINE PERFORMANCE IN CRUISING CONDITION Primadika Kampil
Vortex Vol 1, No 1 (2020)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (332.158 KB) | DOI: 10.28989/vortex.v1i1.715

Abstract

Bleed air is an affected component of the performances engine. Bleed air is pressurized air taken from the compressor. On cruising condition, the bleed air is used for pressurization and AC (Air Conditioner). Because the decrease percentage of the pressure on the compressor, it will influence the value of other parameters. In this journal, the author discusses the effect of bleed air on JT8D-15 engine performance in cruising condition. The method used in this journal is Parametric Cycle Analysis of Real Engine through manual and numerical calculation methods. This research analyzed the performance of engine JT8D-15 within bleed air on and bleed air off condition which had been affected by variations of cruising altitude. The results of calculations from JT8D-15 engine performance and the effect of bleed air for thrust are higher when the aircraft's altitude rises, both in the bleed off and on condition. The values are at the altitude of 27000 ft, 31000 ft and 35000 ft when bleed on are 10638,668 lb, 10954,356 lb, 11266,251 lb, otherwise when bleed off are 10964,851 lb, 11278,715 lb, 11588,257 lb. SFC (specific fuel consumption) on bleed off has a lower value than the SFC value of bleed on. 

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