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Vortex

vortex
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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 86 Documents

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Design And Analysis of CFD Geometry Configuration Canted Winglet Toward Aerodynamic Characteristic on Wing Profil of The UAV LSU-05 NURUL ANWAR; Lazuardy Rahendra Pinandhita; Bangga Dirgantara Adiputra
Vortex Vol 2, No 1 (2021)
Publisher : Institut Teknologi Dirgantara Adisutjipto

The wing is part of an aircraft or UAV which has a function as a major component of producing lift, therefore if a problem occurs such as a vortex at the end of the wing it will affect its performance capability. This study aims to determine the condition of the airflow, the value of induced drag, and the selection of the design of the wingtip devices on the wing profile of the UAV LSU-05. The method used is numerical or computational methods with CFD-based software to predict the aerodynamic characteristics and phenomenon of airflow around the wing with wingtip devices and without it. The model used in this study is a half-wing LSU-05 with NACA 4415 made with CATIA V5R20 software and the simulation uses ANSYS CFX 17.1. Based on the previous simulation results, it was found that the application of the canted winglet geometry to the wing profile of the UAV LSU-05 affects the coefficient lift (CL)/coefficient drag (CD) value and induced drag. Whereas the coefficient lift (CL)/coefficient drag (CD) value before using the canted winglet was 18.904 after application, increased to 21.616, this causes the induced drag value to change inversely with the coefficient lift (CL)/coefficient drag (CD) value where the value before the application was 30.4181 N to 29.0566 N.Keywords: Canted Winglet, CFD, Wing

STRUCTURE POWER AIRCRAFT FUSELAGE 5774 TRAINER Fandi Syafri Pratama
Vortex Vol 2, No 2 (2021)
Publisher : Institut Teknologi Dirgantara Adisutjipto

The analysis process using software aims to determine whether an object or material is suitable for use or not before carrying out the manufacturing process. To find out whether the material is strong or not when applied to the aircraft, an analysis is carried out using the ABAQUS CAE 6.14 software. This software will show the stress value that occurs in the sandwich composite structure when it receives the load experienced by the aircraft.

COMPARISON OF SANDWICH COMPOSITE WING STRUCTURE WITH BALSA WOOD (CASE STUDY OF UAV AIRCRAFT FIXED WING VTOL VX-2) Santoso, Djarot Wahju; Hariyanto, Kris
Vortex Vol 3, No 2 (2022)
Publisher : Institut Teknologi Dirgantara Adisutjipto

UAV aircraft with a fixed wing configuration with multi-rotor are aircraft capable of vertical take-off and landing (VTOL). In designing the wing structure of aircraft, the weight factor and the strength of the wing structure are factors that need to be considered. The use of sandwich composite materials on UAV wings is expected to be able to meet the requirements of UAV aircraft, namely having a light weight, having high rigidity and strength. In this study, a comparative analysis the strength of the sandwich composite wing structure with the balsa wood wing of the UAV VTOL VX-2 aircraft was carried out. The steps taken are to model the composite wing structure of sandwiches and balsa wood using CATIA. Performing the process of structural analysis using ANSYS software. Both half-span models are subjected to lift and vertical take-off loads. From the analysis results, the sandwich composite wing (glass fiber skin with styrofoam core) is stronger than the balsa wood wing structure under vertical take off loads. While the VTOL rods, upper and lower spars of the balsa wood wing model are stronger than the sandwich structure under lift loads, but overall the sandwich wing structure is stronger than the balsa wood wing

ADDITION OF FLY ASH TO THE FIBER COMPOSITE GLASS ON COMPOSITE FUEL RESISTANCE PROPERTIES Bahas Loh Kertabait
Vortex Vol 1, No 2 (2020)
Publisher : Institut Teknologi Dirgantara Adisutjipto

The process of making composites into several main stages, namely preparation of tools, cutting of specimens. Then the base (glass) is cleaned and coated with molding wax and PVA. Mix the resin with the addition of variations of fly ash 0%, 10%, 20% and 30%. Next, apply resin and glass fiber to the base (glass) for up to 3 layers then press it. After 12 hours remove the specimen and cut it to size

DETERMINATION OF WEIGHT AND BALANCE ON THE BOEING 737-800 NG AND AIRBUS A320 Fajar Harry Kurniawan
Vortex Vol 2, No 2 (2021)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Perhitungan weight and balance sebuah pesawat yang dilakukan secara akurat sesuai standar yang ditetapkan oleh IATA (International Air Transport Association) merupakan prioritas utama terhadap keamanan pesawat dan keselamatan penumpang serta pesawat itu sendiri selama melakukan penerbangan. Oleh karena itu seorang Flight Operation Officer (FOO) harus terlebih dahulu mengetahui dan menyiapkan kondisi pesawat tersebut, antara lain berat maximum yang mampu diangkat oleh pesawat dan keakuratanya terhadap Center Of Gravity (CG) pada pesawat tersebut. Pesawat dalam keadaan tidak seimbang sangat berbahaya, karena dapat menjadi tidak stabil dalam proses manuver lepas landas.. Kondisi ini benar-benar dialami oleh penerbangan teramat singkat maskapai Air Midwest nomor penerbangan 5481 penerbangan berjadwal dari Charllote Douglas International Airport, Charllote, North Carolina ke Greenville Spartanburg International Airport, Greer, South Carolina. Kejadian yang terjadi pada tanggal 8 Januari 2003 tersebut, di awali ketika pesawat ini baru saja lepas landas dan masih berada diketinggian yang sangat rendah, ketika pesawat melakukan pergerakan arah heading (hidung pesawat) yang terus mendongak ke atas tanpa dapat dikendalikan. Peringatan stall pesawat berbunyi terus tanpa dapat di atasi. Tindakan itu disebut sebagai Loss of Picth Control During Take-off. Terhitung, 35 detik setelah waktu lepas landas, tanpa dapat dikendalikan lagi, pesawat itu menukik dan jatuh di atas bangunan hanggar. Setelah badan penyelidik kecelakaan nasional Amerika (NTSB) bersama otoritas penerbangan federal (FAA), melakukan penyelidikan atas jatuhnya pesawat tersebut, ditemukanlah faktor utama penyebabnya, yaitu hilangnya kendali pitch pesawat saat lepas landas.

ANALISIS KEGAGALAN NOSE WHEEL STEERING SYSTEM PADA PESAWAT BOEING DENGAN MENGGUNAKAN METODE FAILURE MODE AND EFFECT ANALISYS Anggawaty, Dwi; Mulyani, Sri; Rahmawati, Fajar Khanif
Vortex Vol 3, No 1 (2022)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Aircfrat use nose wheel steering system when landing, take off and landing. In the research discuses the problem of nose wheel steering system B737 – 800 to minimize problems ini nose wheel steering system. The stage of this research are to study the work system of nose wheel steering. Then look for the cause of the problem using the FMEA analysis method. This research is based on data from AFML (aircraft Flight and Manual Log) of the B737 – 800 Aircraft from January 2020 to Junu 2021 at Lion Airline. The results showed that the problem of nose wheel steering system in the failure mode analysis process using FMEA method data in the highest RPN ( Risk priority Number) value is 175 with the case steering collar dan torQ link need lubrication and case Tire pressure that caused by the lack of lubrication on the component and different pressure in tire. Then it is necessary to do inspection before flight.

STRUCTURE ANALYSIS AND MANUFACTURING OF WINGS TRAINER-5774 Suciari Dewi Triani; Moh Ardi Cahyono; Lazuardy Rahendra Pinandhita
Vortex Vol 1, No 2 (2020)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Unmanned Aerial Vechicle (UAV) is one of the types an aircraft. Trainer is part of an airplane where the aircraft is controlled by a remote control for its flight. One of the things that must be considred in design an airplane is strength and and resistance of the wing structure in accepting distributed aircraft loads. In addition to the structural design and load, the material to be used can have an effect. The process is starting from modification of the aircraft wing using CATIA V5R20 which is then carried out analysis of the wing structure by being given the aircraft load using ANSYS 19. The largest structural value is in the Joiner section of 7,967 with manuvering load and smallest value is 0,026 on the Spar section. Margin of safety smallest value in the spar when its manuver. After analysis it is continued with the manufacturing process according to the design that has been made.

RELIABILITY OF AIR SEPARATION MODULE COMPONENTS ON THE NITROGEN GENERATION SYSTEM OF BOEING AIRCRAFT Wahyu Kurniawan
Vortex Vol 2, No 1 (2021)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Aircraft is a type of transportation that can reach a certain area in a short time compared to other types of transportation. Every aircraft used will experience a decrease in performance along with the use of flight hours, to maintain and restore the aircraft condition to its original condition, maintenance effectiveness is needed. Aircraft maintenance carried out to keep the aircraft systems or components working properly, one of the components that need maintenance is the Air Separation Module. The purpose of this study to determine the reliability, failure rate, type of failure, and effectiveness of maintenance of the Air Separation Module.

ANALYSIS OF MAINTENANCE PLANNING C01 CHECK IN AIRBUS A320-214 PK-LUM AT BATAM AERO TECHNIC (BAT) Hazhiyah, Rika Raudhatul; Pinandhita, Lazuardy Rahendra; Mulyani, Sri
Vortex Vol 3, No 1 (2022)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Maintenance is all activities undertaken to maintain the aircraft, its aircraft components and equipment in an air condition including inspection, repair, servicing, overhaul and part change. To be able to perform maintenance properly, every aircraft is required to have a maintenance program. . Batam Aero Technic (BAT) handles MRO work on Airbus A320-214 aircraft with registration number PK-LUM. By analyzing the results of the aircraft maintenance planning to find out the comparison of the results of the planning with the implementation of maintenance. This can maximize the implementation of future maintenance so as not to interfere with aircraft flight operations at Batam Aero Technic (BAT). Before carrying out the treatment process, you should do the planning in advance to ensure that the treatment process runs in accordance with the planning made. To find out the treatment process is running in accordance with its planning or not, it will be analyzed using a fiishbone diagram. Fishbone diagrams are generally used in the stage of identifying problems and determining the cause of the problem. This treatment planning analsis process includes analysis of C01 check care implementation, evaluation of the implementation of C01 check treatment program, treatment delay solution, and C01 check care planning. Then from the results of the analysis the author obtained the cause of delays that occur in the field that is difficult to control such as the problem of delays in the availability of materials / spare parts where ordering and delivery time is needed. Therefore the authors propose to multiply the estimated manhours by 2.5 as an alternative to the anticipation of delayed completion of treatment. This is done to minimize the occurrence of delays in manhours on the ground.

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

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.

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Home Page

OAI Link

Editorial Team

Contact

Reviewer

Google Scholar

Contact Name Istywan Priyahapsara

Contact Email itywan@itda.ac.id

Phone +6287839258012

Journal Mail Official herowintolo@itda.ac.id

Editorial Address https://ejournals.itda.ac.id/index.php/vortex/pages/view/editor

Location Kab. bantul, Daerah istimewa yogyakarta INDONESIA

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Contact Name
Istywan Priyahapsara

Contact Email
itywan@itda.ac.id

Phone
+6287839258012

Journal Mail Official
herowintolo@itda.ac.id

Editorial Address
https://ejournals.itda.ac.id/index.php/vortex/pages/view/editor

Location
Kab. bantul,

Daerah istimewa yogyakarta

INDONESIA