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<![CDATA[ANALISIS TENSILE STRENGTH KOMPOSIT SERAT DAUN AGEL BERORIENTASI ARAH 0 DERAJAT DENGAN VARIASI MATRIKS ]]>
<![CDATA[Pinandhita, Lazuardy Rahendra]]>
<![CDATA[ Vortex Vol 3, No 1 (2022) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v3i1.1177
<![CDATA[Composite is a material that is made by combining two types of materials that have different properties. Composites material made of natural fiber continue to be researched and developed to become an alternative material for metal substitutes. Natural fibers have advantages such as environmentally friendly, low density, recyclable, biodegradable, non-toxic, low cost, and good non-abrasive and heat retaining properties. The test carried out is a tensile test that is adjusted to the ASTM D3039 test standard using a Universal Testing Machine (UTM) tool to obtain stress and strain values. The results of the tensile strength of the agel leaf fiber composite material with an epoxy matrix with fiber direction 00 is 9.588294 MPa and with a polyester matrix in same direction 00 is equal to 7,236818 MPa.]]>
<![CDATA[MAINTENANCE COST TERJADWAL TINGKAT SEDANG PESAWAT GROB G 120 TP-A di SKADRON TEKNIK 043 ADISUTJIPTO YOGYAKARTA ]]>
<![CDATA[Ginting, Charis Ira Sujana]]>;
<![CDATA[Rahamawati, Fajar Khanif]]>;
<![CDATA[Mulyani, Sri]]>
<![CDATA[ Vortex Vol 3, No 1 (2022) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v3i1.1180
<![CDATA[The aircraft that used in this research is Grob G 120TP-A. Purpose of this research is support planning costs for scheduled maintenance in the period of 2020 and forecast the maintenance costs on the PI-600 flight hours for the period 2021, so that the aircraft is always in a state of airworthiness in order to support the implementation of operational activities as a training aircraft for the Indonesian Air Force. Maintenance costs on Periodic Inspection 600 flight hours of Grob G 120 TP-A aircraft in 2020 include employee salaries, spare parts, consumable materials, and fuel costs. Forecasting maintenance costs using the trend exponential method which uses maintenance cost data from 2016 to 2020. The results of the 600 flight hours of periodic inspection maintenance costs are Rp.476.527.879,92.and the results of forecasting maintenance costs for the Periodic Inspection 600 Flying Hours of the Grob G 120 TP-A aircraft using the trend least square method for the 2021 fiscal year is Rp. 408.667.919,9.]]>
<![CDATA[GLIDER MODEL FLYING DYNAMICS SIMULATION EAGE-X ON LONGITUDINAL MATRA ]]>
<![CDATA[Retnowati, Nurcahyani Dewi]]>;
<![CDATA[Junaidin, Buyung]]>;
<![CDATA[Rande, Engelbertus]]>
<![CDATA[ Vortex Vol 3, No 1 (2022) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v3i1.1165
<![CDATA[The Glider Eagle-X aircraft is an unmanned aircraft which is expected to fly with a height of 7 meters above the ground in Yogyakarta (120 m above sea level) with a flying speed of 10 m/s. In order for the Eagle-X glider to fly stably, it is necessary to analyze the flight stability of the Eagle-X glider model. Therefore, in this study, the analysis phase of static stability and dynamic response of disturbances in the longitudinal dimension was carried out. This can be useful for students so that they can better understand the analysis of static stability and dynamic response of disturbances in the longitudinal dimension. The results of the analysis show that the flight dynamics is a value of CM-α < 0 indicating the plane is statically longitudinal and the initial response of the graph is getting smaller which indicates the plane's motion is dynamically stable. The output of the stability analysis of the flying dynamics of the Eagle-X glider model is in the form of a graph. The simulation of the flying dynamics of the Eagle-X glider in the expected longitudinal dimension is shown by the aircraft movement following the graph from the results of the stability analysis which is used as the path of the Eagle-X glider model.]]>
<![CDATA[RELIABILITY ANALYSIS OF MAIN ROTOR EC 155B1 ON PIN BLADE AND ATTACH BEAMS COMPONENTS USING MARKOV ANALYSIS ]]>
<![CDATA[Aditiya, Irvan]]>;
<![CDATA[Pinandhita, Lazuardy Rahendra]]>;
<![CDATA[Adiputra, Bangga Dirgantara]]>
<![CDATA[ Vortex Vol 3, No 1 (2022) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v3i1.1026
<![CDATA[Reliability is used to estimate the conditions of systems or components in the future based on previous conditions. The objects of this research are EC 155B1 aircrafts owned by Indonesia Air Transport & Infrastrucure (IAT), and the method used for analysis is markov analysis. Markov analysis is widely used as an analyzing technique the states of the system that has limited information (memoryless). From this research, ATA chapter 62 Main Rotor that meets the requirements of reliability analysis. The constituent components of main rotor states are Pin Blade, Lower Attach Beam, and Upper Attach Beam. The results of the markov analysis of main rotor system, the states that worked properly are state 1, state 3, and state 4. The probability of the state 1 showed that state has decreased from initial condition, while the state 3 and state 4 have increased from initial condition and subsequently have decreased. The reliability of main rotor system has decreased along with increasing of flight hours with the Mean Time To Failure (MTTF) is 2340.22 flight hours.]]>
<![CDATA[AERODYNAMIC ANALYSIS OF SPORT UTILITY VEHICLE (SUV) BY COMPUTATIONAL FLUID DYNAMICS (CFD) APROACH ]]>
<![CDATA[Junaidin, Buyung]]>
<![CDATA[ Vortex Vol 3, No 1 (2022) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v3i1.1161
<![CDATA[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.]]>
<![CDATA[PRELIMINARY DESIGN OF UNMANNED AIRLAND (PUNA) ]]>
<![CDATA[Priyahapsara, Istyawan]]>;
<![CDATA[Mulyani, Sri]]>
<![CDATA[ Vortex Vol 3, No 1 (2022) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v3i1.1186
<![CDATA[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.]]>
<![CDATA[ANALISIS KEGAGALAN NOSE WHEEL STEERING SYSTEM PADA PESAWAT BOEING DENGAN MENGGUNAKAN METODE FAILURE MODE AND EFFECT ANALISYS ]]>
<![CDATA[Anggawaty, Dwi]]>;
<![CDATA[Mulyani, Sri]]>;
<![CDATA[Rahmawati, Fajar Khanif]]>
<![CDATA[ Vortex Vol 3, No 1 (2022) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v3i1.1179
<![CDATA[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.]]>
<![CDATA[ANALYSIS OF MAINTENANCE PLANNING C01 CHECK IN AIRBUS A320-214 PK-LUM AT BATAM AERO TECHNIC (BAT) ]]>
<![CDATA[Hazhiyah, Rika Raudhatul]]>;
<![CDATA[Pinandhita, Lazuardy Rahendra]]>;
<![CDATA[Mulyani, Sri]]>
<![CDATA[ Vortex Vol 3, No 1 (2022) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v3i1.1178
<![CDATA[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. ]]>
<![CDATA[CASE ANALYSIS ON FLIGHT CONTROL SYSTEM SIKORSKY S76 C++ FAILURE FROM YAW CONTROL ASPECT ]]>
<![CDATA[Rahmawati, Fajar Khanif]]>;
<![CDATA[Lukito, Indro]]>;
<![CDATA[Baihaqi, M Imam]]>
<![CDATA[ Vortex Vol 3, No 1 (2022) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v3i1.1155
<![CDATA[Flight Control is a system that functions as a helicopter control center. Failure that occurs in flight control would certainly result inconvenience of the pilot in operating the helicopter, even the movement of the helicopter can out of control causing incident or accident. The continuity of the helicopter operation is affected by the maintenance system applied. One of mode moving system helicopter is yaw control, that could control the nose helicopter to move right and left. Fault Tree Diagram could described analytical technique, whereby an undesired state of the system is specified (usually a state that is critical from a safety or reliability standpoint). The system then analyzed in the context of its environment and operation to find the solution. Based on the analysis results of failures that occurred in the Sikorsky S76 C ++ helicopter flight control from yaw control aspect in the period of January 2015 to May 2018 with an average use of helicopter’s 2092.05 flight hours, there were 46 failures which caused by yaw control. Based on diagram, there were 4 basic events which caused unschedule maintenance on Sikorsky S76 C ++ helicopter flight control system because of yaw fail control, so that a replacement or repair was needed for the components that affected to the system failure.]]>
<![CDATA[EXPERIMENTAL STUDY OF COOLING SPRAY METHOD ONTO INCLINED HEATED SURFACES ]]>
<![CDATA[Wibowo, Teguh]]>;
<![CDATA[Hermawan, Dedet]]>;
<![CDATA[Prakoso, Agung]]>
<![CDATA[ Vortex Vol 3, No 1 (2022) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v3i1.1164
<![CDATA[Single droplet impingement onto inclined heated surface is studied experimentally. Droplet in the form of aquades is dropped from a fixed height 70 mm to the metal surface with 45º impact angle. This experiment uses 3 types of metals; Stainless Steel AISI 304, Aluminum Alloy 2024, and Copper. All material surfaces are mirror polished and assumed to have the same surface treatment condition. Surface temperatures are 110 ºC, 150 ºC and 210 ºC to determine droplet behavior characteristics. The droplet has 3.0 mm diameter and 28.5 Weber Number (low impact category). In order to analyze droplet behavior in slow motion high velocity camera 4000 fps (frames per second) is used with image resolution 1024 x 768. Data obtained then processed using MATLAB image processing technique to analyze sequence of images visually and quantitatively to determine several parameters; spreading ratio, dimensionless height and contact time.The results showed droplets have different behavior characteristics even at the same surface temperature. Droplet contact time on the copper surface is shorter than aluminum and stainless steel. This is because droplets experienced bouncing due to film boiling regime takes place earlier. Maximum spreading ratio of stainless-steel surfaces is higher than copper because changes of boiling regime on stainless steel surfaces are slower and droplet is still experiencing spreading on the surface]]>
