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Dwi Hartini, Buyung Junaidin, Habibi Habibi
Published: 15 January 2022
Vortex, Volume 3, pp 1-7; https://doi.org/10.28989/vortex.v3i1.1153

Abstract:
The Cargo-X UAV aircraft is a UAV aircraft designed to carry medicines, packages and blood bags in areas that require fast and efficient handling. One of the important components of the Cargo-X UAV aircraft is the wing, so the strength of the wing structure must be seriously considered to ensure safety during flight under unexpected conditions. The purpose of this study was to analyze the wing structure of the UAV Cargo-X aircraft made of sandwich composite material to determine the level of safety of the wing structure. The loading of the wing structure uses the load due to the lift. The wing structure modeling uses CATIA software, while the analysis uses PATRAN/NASTRAN software. From the analysis results, the skin and spar wing structures are safe against loading, while the core section is not safe against loading. Keywords UAV; Wing; Sandwich Composite; Strength of the Structure Full Text: PDF References Wildan. 2018. Desain Awal dan Manufakturing Pesawat UAV Cargo-X. Skripsi. STTA.Yogyakarta. Atmaja, YS. 2018. Desain Internal Struktur dan Analisis Statik Struktur PesawatUAV Cargo-X. Skripsi. STTA.Yogyakarta. Sruthi, K, T. Lakshmana Kishore and M. Komaleswara Rao, (2017), Design and Structural Analysis of An Aircraft Wing by Using Aluminium Silicon Carbide Composite Materials, International Journal of Engineering Development and Research Volume 5 Issue 4. Anggara. 2019. Analisis Kekuatan Wing Uav Cargo-X Bermaterial Hardfoam dan Bermaterial Komposit Sandwich terhadap Beban Bending. Skripsi. STTA.Yogyakarta. Lamani, Shivaji, dkk, (2020), Analysis, Fabrication and Testing of a Sandwich Composite for an UAV Wing, AIP Conference Proceedings Volume 2311 Issue 1. K. Abdurohman, Simulasi Uji Tarik Komposit Glass-Epoxy Hasil Vacuum Bagging, (Pustekbang, Bogor, 2015) http://asm.matweb.com Ministry of Transportation, Civil Aviation Safety Regulation (CASR) Part 23 Amdt 2, (Ministry of Transportation, Jakarta, 2014). Niu, M.C.Y. (1997). Airframe Stress Analysis and Sizing (p.795). Hong Kong: Conmilit Press. Hadi, Bambang K., Mekanika Struktur Komposit. ITB. http://dx.doi.org/10.28989/vortex.v3i1.1153 Refbacks There are currently no refbacks.
Lazuardy Rahendra Pinandhita
Published: 15 January 2022
Vortex, Volume 3, pp 53-58; https://doi.org/10.28989/vortex.v3i1.1177

Abstract:
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.
Fajar Khanif Rahmawati, Indro Lukito, M Imam Baihaqi
Published: 15 January 2022
Vortex, Volume 3, pp 84-90; https://doi.org/10.28989/vortex.v3i1.1155

Abstract:
Flight Control is a system that functions as a helicopter control center.Failure that occurs in flight control would certainly result inconvenience ofthe pilot in operating the helicopter, even the movement of the helicoptercan out of control causing incident or accident. The continuity of thehelicopter 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 thesystem is specified (usually a state that is critical from a safety or reliability standpoint). Thesystem then analyzed in the context of its environment and operation to find the solution. Based on the analysisresults of failures that occurred in the SikorskyS76 C ++ helicopter flight control from yaw control aspect in the period of January 2015 to May 2018 with an average use ofhelicopter’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 replacementor repair was needed for the components that affected to the system failure. Keywords flight control system; yaw control; fault tree diagram Full Text: PDF References DGCA,2000, Civil Aviation Safety Regulation Part 43. (Rev.01), Maintenance, Preventive Maintenance, Rebuilding, and Alteration, Jakarta: DGCA. Fault Tree Handbook With Aerospace Applications, Nasa Office of Safety and Mission Assurance, Washington DC. 2002 Kinnison A, Harry dan Siddiqui, T., 2004, Aviation Maintenance Manajemen 2nd Edition, The Mc Graw-Hill, New York. Maintenance Manual (MM) Sikorsky S-76, PT. Pelita Air Service, Tangerang Selatan. 2013 (1990), "Helicopter Yaw Control: Review of Royal Aeronautical Society Conference", Aircraft Engineering and Aerospace Technology, Vol. 62 No. 5, pp. 23-25. https://doi.org/10.1108/eb036942 Rahmawati, F. K. (2019). Inventory Planning Management Of Low Pressure Filter Web (LPFW) On KT1-BEE Aircraft Based On Reliability Component In SKATEK 043. Angkasa: Jurnal Ilmiah Bidang Teknologi, 11(2), 131-139. Septiyana, A. (2020). STABILITY AND CONTROLABILITY ANALYSIS ON LINEARIZED DYNAMIC SYSTEM EQUATION OF MOTION OF LSU 05-NG USING KALMAN RANK CONDITION METHOD. Jurnal Teknologi Dirgantara, 18(2), 81-92. http://dx.doi.org/10.28989/vortex.v3i1.1155 Refbacks There are currently no refbacks.
Irvan Aditiya, Lazuardy Rahendra Pinandhita, Bangga Dirgantara Adiputra
Published: 15 January 2022
Vortex, Volume 3, pp 18-24; https://doi.org/10.28989/vortex.v3i1.1026

Abstract:
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. Keywords EC 155B1; Markov Analysis; Probability; Reliability Full Text: PDF References Utama, F.Y. 2012. Simulation and Modelling Aircraft Components Reliability of Boeing 737-300/-400 Type. Institut Teknologi Sepuluh November. Surabaya. Indonesia. Balagurusamy, E. 1984. Reliability Engineering. Tata Macgraw Hill. New Delhi. India Ericson, C.A. 2005. Hazard Analysis Technique for System Safety. John Wiley & Sons, Inc. New Jersey. USA. Srinath, L.S. 2013. Reliability Engineering. East West Press. New Delhi. India. Kalaiarasi, S. Anita, A.M. Geethanjalii, R. 2017. Analysis of System Using Markov Technique. Global Journal of Pure and Applied Mathematics. India. Saritha, G. Devi, M Tirumala. Maheswari, T S U. 2020. Reliability and Availability for Non-Repairable & Repairable Systems using Markov Modelling. Kakatiya University. Warangal. India Ramadhan, Adil Labib. 2020. Analisis Keandalan Komponen Pesawat EC 155B1 Menggunakan Metode Weibull. Institut Teknologi Dirgantara Adisutjipto. Yogyakarta. Indonesia Rouvroye, J.L. 2001. Enhanced Markov Analysis as A Method to http://dx.doi.org/10.28989/vortex.v3i1.1026 Refbacks There are currently no refbacks.
Charis Ira Sujana Ginting, Fajar Khanif Rahamawati, Sri Mulyani
Published: 15 January 2022
Vortex, Volume 3, pp 8-17; https://doi.org/10.28989/vortex.v3i1.1180

Abstract:
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.
Buyung Junaidin
Published: 15 January 2022
Vortex, Volume 3, pp 67-74; https://doi.org/10.28989/vortex.v3i1.1161

Abstract:
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. Keywords Aerodynamics; CFD; Car; SUV Full Text: PDF References H. Braess Herman & U. Seiffert, Handbook of Automotive Engineering, SAE International, Warrendale, SA, 2005. Manan Desai, S.A.Channiwala, H.J. Nagarsheth, Experimental and Computational Aerodynamic Investigation of a Car, Wseas Transactions on Fluid Mechanics, vol.3, pp 359-368, Oct. 2008. Subrata Roy, Pradeep Srinivasan, External Flow Analysis of a Truck for the Hambat Reduction, Kattering University, 2000. A. Muthuvel, M. K. Murthi, Sachin N. P, Vinay M. Koshy, S. Sakthi, E. Selvakumar, Aerodynamic Exterior Body Design of Bus, International Journal of Scientific & Engineering Research, Volume 4, Issue 7, July 2013. A. M. Biadgo, A. Simonovic, J. Svorcan, S. Stupar, Aerodynamic Characteristics of High Speed Train under Turbulent Cross Winds: a Numerical Investigation using Unsteady-RANS Method, FME Transaction, vol.42, pp 10-18, 2014. J. Katz, Race Car Aerodynamics: Designing for Speed, Bentley Publishers, Cambridge, USA, 1995. http://dx.doi.org/10.28989/vortex.v3i1.1161 Refbacks There are currently no refbacks.
Rika Raudhatul Hazhiyah, Lazuardy Rahendra Pinandhita, Sri Mulyani
Published: 15 January 2022
Vortex, Volume 3, pp 32-39; https://doi.org/10.28989/vortex.v3i1.1178

Abstract:
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.  Keywords planning; maintenance; Airbus A320-214; delay; analysis Full Text: PDF References Pratiwi, Retno. 2018. Analisis Perencanaan Schedule Maintenance Pesawat KT-1B Woong Bee Di Skadron Teknik 043. Yogyakarta: Sekolah Tinggi Teknologi Adisutjipto. Wirawan, I Made Pandu. 2018. Analisis Planning Dan Evaluasi Pelaksanaan Program Perawatan C01 Check, Additional Task Pesawat ATR 72-600 PK-GAK di PT GMF AeroAsia Tbk. Yogyakarta: Sekolah Tinggi Teknologi Adisutjipto. Laksmono, Andi Tri. 2005. Analisis Proses Perawatan Pesawat Dengan Menggunakan Konsep Diagram Fishbone Dan Metode Critical Path Method. Yogyakarta: Sekolah Tinggi Teknologi Adisutjipto. Kinnison, Harry A. 2013. Aviation Maintenance Management. Mc Graw Hill Ardhia, Warta. 2012. Jurnal Penelitian Perhubungan Udara Vol. 38 No. 4. Peneliti Pusat Penelitian dan Pengembangan Udara. Diagram Fishbone. (2020, Juni 20). Diambil kembali dari Referensi Manajemen Kualitas: https://sites.google.com/site/kelolakualitas/Diagram-Fishbone Pengertian cause effect diagram fishbone. (2016, Juni 27). Diambil kembali dari Ilmu Manajemen Induustri: https://ilmumanajemenindustri.com/pengertian-cause-effect-diagram-fishbonediagram-cara-membuat-ce/ Perawatan Pesawat. (2008, Juli 18). Diambil kembali dari aeroBlog: https://aeroblog.wordpress.com/2008/07/18/perawatan-pesawat/ Rita Ummi Hanik, Budi Santosa, Nani Kurniati (t.thn.). Perencanaan Manhours C-Check Maintenance Pada Unit Base Maintenance PT. GMF Aeroasia. academia. http://dx.doi.org/10.28989/vortex.v3i1.1178 Refbacks There are currently no refbacks.
Dwi Anggawaty, Sri Mulyani, Fajar Khanif Rahmawati
Published: 15 January 2022
Vortex, Volume 3, pp 75-83; https://doi.org/10.28989/vortex.v3i1.1179

Abstract:
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 pressurethat caused by the lack of lubrication on the component and different pressure in tire. Then it is necessary to do inspection before flight. Keywords FMEA; Nose wheel steering; failure Full Text: PDF References Boeing,2020,Aircraft Maintenance Manual 737 NG Chapter 12, Boeing Boeing,2020,Aircraft Maintenance Manual 737 NG Chapter 32, Boeing Boeing,2020,Fault Isolation Manual 737 NG Chapter 32, Boeing SAEJ-1739,Failure Mode and Effect Analysis,AIAG,&ASQC,USA Minda Mora,2012,Literatur Review On Aircraft Maintenance Program, Cara menentukan nilai RPN FMEA http://www.fmea-fmea.com-rpn.html (diakses pada 10 februari 2021) http://dx.doi.org/10.28989/vortex.v3i1.1179 Refbacks There are currently no refbacks.
Nurcahyani Dewi Retnowati, Buyung Junaidin, Engelbertus Rande
Published: 15 January 2022
Vortex, Volume 3, pp 59-66; https://doi.org/10.28989/vortex.v3i1.1165

Abstract:
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. Keywords simulation; Eagle-X Glider; longitudinal matra Full Text: PDF References Ardila, A. P. B., Tarmukan, T., & Nurcahyo, S. (2020). SISTEM KONTROL UNTUK MENCAPAI ALTITUDE POINT PADA UAV (UNMANNED AERIAL VEHICLE) GLIDER. Jurnal Elektronika Otomasi Industri, 3(3), 70-75. Prakoso, T., Setiawan, B., & Safitri, H. K. (2020). SISTEM KESTABILAN SUDUT PITCH PADA UAV (UNMANNED AERIAL VEHICLE) GLIDER. Jurnal Elektronika Otomasi Industri, 3(2), 76-84. Junaidin, B., Hartini, D., & Herlambang, S. (2020). CONCEPTUAL DESIGN OF BIRD-LIKE UNMANNED AERIAL VEHICLE FOR PEST BIRD CONTROL. Angkasa: Jurnal Ilmiah Bidang Teknologi, 12(1), 19-24. Firmansyah, H. N., Junaidin, B., & Mauliadi, M. F. (2016). Perancangan Awal Scale Model Glider Stta-25-02_sailplane. Angkasa: Jurnal Ilmiah Bidang Teknologi, 8(2), 87-98. Syamsiah, S. (2019). Perancangan Flowchart dan Pseudocode Pembelajaran Mengenal Angka dengan Animasi untuk Anak PAUD Rambutan. STRING (Satuan Tulisan Riset Dan Inovasi Teknologi), 4(1), 86-93. http://dx.doi.org/10.28989/vortex.v3i1.1165 Refbacks There are currently no refbacks.
Istyawan Priyahapsara, Sri Mulyani
Published: 15 January 2022
Vortex, Volume 3, pp 25-31; https://doi.org/10.28989/vortex.v3i1.1186

Abstract:
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. Keywords drone; puna; design Full Text: PDF References Daniel P. Raymer. (1989). Aircraft Design: A Conseptual Approach,. California: President, Conceptual Research Corporation Sylmar. John D. Anderson, J. (1999). Aircraft Performance and Design. Tata McGraw Hill. Putra, A. N. (2018). Desain Awal dan Analisis Aerodinamika Pesawat UAV V- SKY 14. Yogyakarta: Sekolah Tinggi Teknologi Adisutjipto. Wildan (2018). Desain dan Analisis Aerodinamika Pesawat UAV Cargo X. Yogyakarta: Sekolah Tinggi Teknologi Adisutjipto. Syamsuar, S. (2015). Studi Kasus Prestasi Terbang Takeoff-Landing. Jurnal Perhubungan Udara , 49-58. Mohammad H.Sadraey (2013). Aircraft Design A Systems Engineering Approach,.USA, New Hampshire, Daniel Webster Collage. http://dx.doi.org/10.28989/vortex.v3i1.1186 Refbacks There are currently no refbacks.
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