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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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ANALYSIS OF MECHANICAL STRENGTH OF CONNECTION BETWEEN COMPOSITE AND ALUMINUM SHEET METAL USING HOLE CLINCHING PROCESS Ravenskya Hana Hardiyantie; Lazuardy Rahendra P
Vortex Vol 2, No 2 (2021)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Aluminum and composite materials are the types of materials that are used to construct structures on aircraft airframes. It is not uncommon for both types of materials to be used together with the joining method. In the process of connecting between two types of material in the aircraft structure, it is mostly carried out by the riveting method. This process is carried out by making a hole in the two materials according to the rivet diameter and then the hole diameter is then filled with rivets and the riveting process is carried out. The process uses rivets so that it will relatively increase the weight of the structure because there is additional rivet material. In this study, the objectives are to determine the mechanical strength of the joint between the composite and aluminum sheet metal using the mechanical clinching and riveting processes. The method used is an experimental method, namely by making test specimens with composite and aluminum, solid rivet type fasteners and punches to determine the connection of the riveting, the drilling process is carried out with a hole diameter of 3.5 mm, for the clinching method with variations in the diameter of the punch 3.5 mm, 4.0 mm. , and 4.5 mm. Then the tensile test, macro photo test were carried out. The results obtained from this research are that the maximum load increase in the specimen tested by clinching is because the damage length (gap) value is obtained at the joint boundary between the rivet and the test material.

ANALISIS FAKTOR DELAMINASI PADA MATERIAL SERAT GELAS TERHADAP PARAMETER DRILLING Priyahapsara, Istyawan
Vortex Vol 3, No 2 (2022)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Delaminasi adalah sebuah ukuran dari area rusak sekitar lubang (Abdullah, 2019). Delaminasi tinggi bisa mengakibatkan kekuatan struktur yang berkurang. Dalam penelitian ini, akan dilakukan drilling dengan parameter permesinan yang sesuai dalam kaedah permesinan, selanjutnya dilakukan observasi citra makro terhadap lubang yang dihasilkan. Pengujian dilakukan pada material serat gelas 5 layer, dengan pahat drilling diameter 6.3 mm. Parameter drilling menggunakan variasi putaran mesin 1860 rpm, 2920 rpm, 4540 rpm, dan kecepatan pemakanan vertikal (plunging) 0.038 m/menit, 0.067m/menit. Didapatkan hasil nilai terendah delaminasi didapat pada spindle speed 1860 RPM dan plunging rate 0.038 rev/min sebesar 1.24. Nilai tertinggi delaminasi didapat pada spindle speed 4540 RPM dan plunging speed 0.076 rev/min

PULL AND BENDING FORCE CARBON FIBER COMPOSITE Moh Ardi Cahyono; Laura Laksamana
Vortex Vol 1, No 2 (2020)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Based on the test data, it can be seen that the average stress value on the carbon fiber composite with the fiber direction of 0 ° -30 ° -60 ° has the highest tensile stress value in the TA 2 specimen, namely 121.439 MPa, the highest strain value in the TA 1 specimen is 0.031, the value The highest modulus of elasticity in the TA 3 specimen is 438,460 MPa, while for the fiber direction 0 ° -45 ° -90 ° the highest tensile stress value in the TB 3 specimen is 670.691 MPa, the highest strain value in the TB 3 specimen is 0.096, the highest elasticity modulus value in the specimen TB1 is 1076,993 MPa.

THE FEASIBILITY ANALYSIS OF BOEING 737-500 OPERATION AT NORTH ACEH MALIKUSSALEH AIRPORT Aldrian Nasaifal R
Vortex Vol 2, No 2 (2021)
Publisher : Institut Teknologi Dirgantara Adisutjipto

The large number of Acehnese people who are outside Aceh with various needs, such as doing business, working or studying. The optimal transportation to use to the destination quickly in a short time, namely air transportation. North Aceh Malikussaleh Airport is the second busiest airport in Aceh Province.The analysis in this study used PKP-PK analysis, analysis of the feasibility of Boeing 737-500 aircraft using the FPPM method, and analysis of the load capacity of Boeing 737-500 aircraft.From the calculation results, the Boeing 737-500 aircraft is not suitable to be flown at the Malikussaleh Airport in North Aceh due to the limitations of the PKP-PK category level and the strength of the Malikussleh Airport runway. Therefore, North Aceh Malikussaleh Airport must be upgraded

AERODYNAMIC ANALYSIS OF SPORT UTILITY VEHICLE (SUV) BY COMPUTATIONAL FLUID DYNAMICS (CFD) APROACH Junaidin, Buyung
Vortex Vol 3, No 1 (2022)
Publisher : Institut Teknologi Dirgantara Adisutjipto

The main purpose of aerodynamics analysis of a vehicle is optimizing it’s form to increase aerodynamics efficiency. More streamline of aerodynamic design of a vehicle not just effecting to lower fuel consumption which is cause by lower drag due to wind at highspeed, but also increasing stability dan control of the vehicle itself. The vehicles are existed with many variations of form so they have difference aerodynamic characteristics. For a personal vehicle like cars, have many variants such as sedan, sport utility vehicle (SUV), multipurposes utility vehicle (MPV), ect. It becomes a motivation to do research about aerodynamic analysis of a SUV car which is a car variant with huge utilize in Indonesia. In this research, aerodynamic characteristics of SUV car are evaluated by computational simulation with computational fluid dynamics (CFD) approach. CFD simulation yields aerodynamic characteristics data and flow behaviors around car model. Simulation results show that critical drag coefficient (CDcrit) of SUV car is 0.36 with lift coefficient is 0.25. the CDcrit of the car is lower than typical value for a modern car. So that, optimalization of SUV car form which analyzed is needed. Contours of pressure at car surfaces show that high pressure area are located at front of grill and windshield, and low-pressure area are located at nose and leading-trailing roof due to the form nose and leading-trailing roof are streamlines. At back surface of the car, low pressure area are formed by flow separation which creates wake.

Calculation Clearance Between Aircraft Hartono Hartono
Vortex Vol 1, No 2 (2020)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Airport aprons, aprons, ramps, or asphalt, are areas of an airport where aircraft are parked, unloaded or loaded, refueled, or ridden. Although the use of an apron is covered by regulations, such as lighting on a vehicle, it is usually more accessible to users than a runway or taxiway. The method used is to look at the rules or regulations in force in Indonesia, namely on Peraturan Direktur Jenderal Perhubungan Udara, No : SKEP/77/VI/2005 about Persyaratan Teknis Pengoperasian Fasilitas Teknik Bandar Udara. In this study, the extent of apron needs with the ability to accommodate 2 to 3 aircraft will be calculated. If the calculation results use aircraft specifications N219 (Nurtanio) and Stemme S-15, the Clearance between aircraft ready to takeoff is 556.5 m2.

CIVIL FLIGHT GUIDE WHEN TAKE OFF FROM THE GADING FIELD Maria Ermelinda Bupu
Vortex Vol 2, No 1 (2021)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Until now, Gading Airfield cannot be used for commercial flights. However, in the future, along with the increasing number of commercial and training flights, Gading Airfield will continue to be developed to help smooth flights in DI Yogyakarta. Thus some flight guidelines for civil aviation must be made. Several analysis and calculation methods are carried out starting from general analysis of the airfield, counting and design of the takeoff guide patron starting from two sides of the runway, namely from RWY 10 and 28. The calculation consists of MTOW calculation which is limited by PCN, calculation of takeoff path, calculation Takeoff distance requirement, calculation of climb segment up to 1.500 feet, calculation of flight turn 1.500 feet, to design patron takeoff path guidance.

PRELIMINARY DESIGN OF UNMANNED AIRLAND (PUNA) Priyahapsara, Istyawan; Mulyani, Sri
Vortex Vol 3, No 1 (2022)
Publisher : Institut Teknologi Dirgantara Adisutjipto

The development of the number of vehicles exceeding the capacity of highways in urban areas causes frequent traffic jams and increases the risk of accidents. This often happens during year-end holidays and Eid holidays. So it is very necessary to monitor traffic density during the annual holiday period to reduce the number of fatalities due to traffic accidents. Monitoring traffic density using helicopters is expensive because of the high fuel consumption and maintenance. So we need a new alternative, namely using Unmanned Aircraft (PUNA) because it is easy to operate and cheap to maintain. So it is very necessary to design PUNA for traffic density monitoring missions. Aircraft for this purpose are classified as small because the payload, namely the camera, only weighs 2 kg. Study obtained the following results: fuselas/body length 1.94 m, wingspan 1.46 m, airfoil NACA 2412. engine OS MAX-40FX, engine located in the nose, take-off Gross Weight 6.11 kg, material weight 321.09 grams, use an Oblique Camera type camera, the camera weight is 2 kg, and the camera position is 3 ft from the nose.

EXPERIMENTAL STUDY OF PORTABLE STOVE PERFORMANCE USE SOLAR ENERGY Afisna, Lathifa Putri; Adimas, Fransiskus; Adryansyah, Rizky Sultan
Vortex Vol 3, No 2 (2022)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Alternative energy has begun to develop over time, such as thermal stoves that use solar energy as a heat source for cooking. The solar cooker must be of high quality, affordable, user friendly, lightweight and, stackable. A thermal solar cooker can cook a meal because the plates are heated by the sun's energy. Sunlight enters the pan or thermal solar panel and reflected toward the can or heated object. Then, Sunlight turns into heat energy.Thermal stove performance analysis was carried out starting from 09:00 WIB to 16:00 WIB. The most efficient time to use a thermal stove is 13:00 WIB, it is recorded that 350 ml of water from a temperature of 27℃ reaches a temperature of 83℃ with a heating duration of 55 minutes. One of the conclusion of this study is the time of heating influenced by weather temperature. Last, to shorten the time, then we must use the shape of sun catcher like a parabola.

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

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.

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Istywan Priyahapsara

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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