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<![CDATA[SIMULASI KESTABILAN PROTOTYPE UAV-SPRAYER BERBASIS QUADCOPTER TERHADAP PENAMBAHAN SEKAT PADA PENAMPUNG CAIRAN ]]>
<![CDATA[Kris Hariyanto]]>;
<![CDATA[Bangga Dirgantara]]>
<![CDATA[ Vortex Vol 3, No 2 (2022) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v3i2.1229
<![CDATA[The use of UAVs has begun to penetrate the world of agriculture. One of the functions of UAVs in agriculture is to spray pesticides. The pesticides used are liquid so that when the UAV is airborne and maneuvering, the fluid experiences fluid motion or sloshing. Sloshing that occurs can cause the balance of the UAV to be disturbed. To overcome this, a bulkhead or baffle is needed in the reservoir in order to reduce fluid movement. In the case of the research studied, the simulation of sloshing in the reservoir with the presence of baffles and without the presence of baffles. This research uses different reservoir variations and different water levels, namely 55 mm, 35 mm and 15 mm. Simulations are carried out during cruising and maneuvering flights at a speed of 2 m/s. The container modeling uses the Catia V5R20 software and the simulation uses the Ansys 14.5 software. The simulation results show that the effect of baffle placement is more visible if the baffle is placed in the xy plane, while for the baffle placement in the yz plane, the force caused by sloshing is greater. In spraying the UAV-Sprayer will more often fly forward (cruise), while for maneuvers (right or left) it is only done occasionally/not too often. So that giving baffles is more effective in the xy plane because it can reduce sloshing better than the baffles in the yz plane.]]>
<![CDATA[MENGGALI POTENSI ENERGI LISTRIK “ENERGI BARU TERBARUKAN” BERSUMBER DARI PRODUKSI KELAPA SAWIT BIOMASSA DI ACEH TAMIANG ]]>
<![CDATA[Rahmad Purnama]]>;
<![CDATA[Hefri Yuliadi]]>;
<![CDATA[Boas Aritonang]]>;
<![CDATA[Mhd Fitra Zambak]]>;
<![CDATA[Feri Kurniawan]]>
<![CDATA[ Vortex Vol 1, No 2 (2020) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v1i2.898
<![CDATA[Listrik merupakan kebutuhan primer, sehingga Pemerintah Pusat didalam hal ini dibawah menteri ESDM bertanggung jawab atas pemenuhan kebutuhan ini dengan cara mengeluarkan Undang undang tentang penyediaan energi listrik seperti yang tertuang dalam Undang-Undang No. 30 tahun 2009 tentang ketenagalistrikan. Pemda baik Kabupaten dan Kabupaten/Kota Mempunyai peran membuat kebijakan berdasarkan kajian potensi energi listrik yang dimiliki gunakan untuk menjaga penyediaan energi listrik dari sekarang. Penelitian ini mengkaji tentang potensi pembangkit energi listrik yang bersumber dari energi terbarukan Biomass di Kabupaten Aceh Tamiang. Tujuan untuk mendapatkan gambaran potensi energi baru terbarukan yang ada di Kabupaten Aceh Tamiang dan dapat menentukan kebijakan energi listrik untuk pembangunan penyediaan energi listrik yang tepat dan efektif. metode penelitian adalah penelitian kuantitatif penelitian ini menggunakan data sekunder. Produksi sawit pada tahun 2013 mencapai 6.735.795,45 ton denganjumlah lahan 393.990 ha Setiap hektar kebun kelapa sawit menghasilkan 17 ton tandan buah segar dan setiap Hektar lahan ditanami 148 pohon sawit dengan demikian untuk setiap pohon kelapa sawit menghasilan 115 kg/tahun. Sehingga dengan jumlah produksi yang bersar tersebut maka didapatkan energi listrik yang terbangkit dari potensi limbah produksi kelapa sawit adalah 1.573 MWh. Potensi ini dapat membantu pemenuhan energi nasional 35 Ribu MWh]]>
<![CDATA[ANALYSIS DESIGN SYSTEM FOR PROSPECTIVE AIRCRAFT PASSENGERS IN NYIA AIRPORT ]]>
<![CDATA[Rianto Rianto]]>;
<![CDATA[Nanda Tri Aini S]]>
<![CDATA[ Vortex Vol 2, No 2 (2021) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v2i2.1003
<![CDATA[Air transportation is a necessity for regional economic activities, where passengers will have an important role for the survival of the aviation world. Knowing what factors are the most influential in the movement of prospective passengers is important to know the future of the aviation world, especially for the Special Region of Yogyakarta. So in this study designed a system that can be used to solve these problems. Where this system uses eight variables, namely the number of passengers, the number of residents, the number of hotels, the number of universities, the number of students, the number of hospitals, the number of workers, and the number of companies.]]>
<![CDATA[GLIDER MODEL FLYING DYNAMICS SIMULATION EAGE-X ON LONGITUDINAL MATRA ]]>
<![CDATA[Nurcahyani Dewi Retnowati]]>;
<![CDATA[Buyung Junaidin]]>;
<![CDATA[Engelbertus Rande]]>
<![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 OF EC 155 B1 AIRCRAFT COMPONENTS USING UPPER CONTROL LIMIT (ALERT LEVEL) FORMULATION ]]>
<![CDATA[Ali Mahroni]]>
<![CDATA[ Vortex Vol 1, No 2 (2020) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v1i2.902
<![CDATA[Airport Rescue & Fire Fighting equipment at Adi Soemarmo International Airport, Operational Vehicle PKP-PK, the number of main vehicles is 3 units, and 6 supporting units meet the standard requirements that have been determined according to the PKP-PK category at Adi Soemarmo Airport, namely category 8. it has a Daily Checklist of operational equipment in each main vehicle and support vehicle. Supporting Facilities for Airport Rescue & Fire Fighting totaled 194 where required for category 8 was 167 but there were still some shortcomings of the equipment needed. This can be shown in the table, namely the types of hydraulic / electrical (or combination) portable rescue equipment, oxygen resuscitation, and thermal imaging cameras. There are 380 Supporting Reserve Facilities for Rescue & Fire Fighting where the minimum equipment required is 355 but there is a lack of equipment, namely Proximity suit, Resuscitator, Helmet, and Binocular equipment.]]>
<![CDATA[CFM56- 7B TAKE-OFF ENGINE PERFORMANCE WITH THRUST 26300 LB AND 24200 LB ]]>
<![CDATA[Joseph Pradana Hutamadi]]>
<![CDATA[ Vortex Vol 2, No 1 (2021) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v2i1.935
<![CDATA[As an one of engine manufacturers, CFM produces CFM56-7B with some thrust rating versions to fulfill market demand. In this case, operator has some considerations in choosing engine which is appropriate with the demand. The engine performance is very important to be considered, especially the engine capabilities when it is being maximally operated in takeoff phase.This research discusses about the CFM56-7B engine takeoff performance comparison between 26300 lbs and 24200 lbs thrust rating configuration. By processing Test Cell Result data using formula in Engine Shop Manual - 003, author did a performance calculation to know how much the difference that happened to both of those thrust rating configuration.]]>
<![CDATA[RELIABILITY ANALYSIS OF MAIN ROTOR EC 155B1 ON PIN BLADE AND ATTACH BEAMS COMPONENTS USING MARKOV ANALYSIS ]]>
<![CDATA[Irvan Aditiya]]>;
<![CDATA[Lazuardy Rahendra Pinandhita]]>;
<![CDATA[Bangga Dirgantara Adiputra]]>
<![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[PENGARUH KECEPATAN FEEDRATE FRICTION STIR WELDING (FSW) TERHADAP SIFAT MEKANIK DAN STRUKTUR MIKRO PADA ALUMINIUM PADUAN AA 2024-T3 ]]>
<![CDATA[Fajar Nugroho]]>;
<![CDATA[Nurfi Ahmadi]]>;
<![CDATA[Sarif Hidayat]]>
<![CDATA[ Vortex Vol 3, No 2 (2022) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v3i2.1265
<![CDATA[Friction stir welding (FSW) adalah suatu teknologi pengelasan yang merupakan proses solid-state joining yang bisa digunakan untuk menyambungkan material aluminium dengan mampu las yang rendah. Proses FSW memanfaatkan putaran dari tool yang menggesek dua buah lempengan logam yang akan disambung. Aluminium 2024 T3 dengan ketebalan 4 mm disambung menggunakan proses FSW dengan variasi feedrate yang digunakan 13 mm/menit, 15 mm/menit, dan 25 mm/menit, kecepatan putaran spindle 910 rpm dan kedalaman pin 3 mm. Pengujian yang dilakukan adalah pengujian tarik, kekerasan dan uji struktur mikro pada masing-masing variasi pengelasan.Hasil penelitian menunjukkan bahwa kekuatan tarik dan regangan tarik tertinggi terjadi pada pengelasan dengan feedrate 25 mm/menit sebesar 221,51 MPa dan 3,60. Kemudian kekuatan tarik dan regangan tarik terendah terjadi pada pengelasan dengan feedrate 13 mm/menit sebesar 198,63 MPa dan 2,26. Nilai kekerasan tertinggi di area nugget zone dihasilkan pada pengelasan dengan feedrate 25 mm/menit yaitu sebesar 137 VHN dan nilai kekerasan terendah dihasilkan pada pengelasan dengan feedrate 13 mm/menit yaitu sebesar 105 VHN. Hasil foto struktur mikro pada area nugget zone dan TMAZ (Thermomecanically Affected Zone) mengalami perubahan seiring dengan berubahnya feedrate.]]>
<![CDATA[THE FAILURE OF AIR CONDITIONING SYSTEM IN B737NG AIRCRAFT ]]>
<![CDATA[Anindia Istikomah]]>
<![CDATA[ Vortex Vol 1, No 1 (2020) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v1i1.722
<![CDATA[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]]>
<![CDATA[CRITERIA FOR MULTI AIRPORT SYSTEM DEVELOPMENT IN METROPOLITAN AREA ]]>
<![CDATA[Surya Apriansyah]]>
<![CDATA[ Vortex Vol 2, No 1 (2021) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v2i1.921
<![CDATA[Soekarno Hatta International Airport and Halim Perdana Kusuma Airport are located in the Jabodetabek metropolitan area which is the largest area for air transportation users in Indonesia. Along with the increasing number of users of air transportation modes, a multi-airport system is needed to reduce the burden on one airport. The method used is a qualitative analysis method by comparing existing data with data obtained from research to determine a multi-airport criteria. From the results of data processing, it is concluded that the development of a multi-airport system in the Jabodetabek metropolitan area has several criteria, namely airport distance, accessibility, airport management, airport route services, passenger demand as well as government regulations and policies governing the multi-airport systems. ]]>
