Articles
<![CDATA[NUMERICAL SIMULATIONOF FLEXIBLE WINGOF HALE UAV USING TWO-WAY FLUID STRUCTURE INTERACTION METHOD ]]>
<![CDATA[Buyung Junaidin]]>
<![CDATA[ Angkasa: Jurnal Ilmiah Bidang Teknologi Vol 9, No 1 (2017): Mei ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/angkasa.v9i1.108
<![CDATA[This paper describes numerical simulation o f flexible High Altitude Long Endurance Unmanned Aerial Vehicle (HALE UAV)wingusing two-way fluid structure interaction (FSI) method. The HALE wing is designed with high aspect ratio. This configuration intended to reduce the vehicle induced drag and reduces the lift-loss at wingtip which caused by wingtip vortex. But the structure of the wing itself becomes more elastic that be able to give large deformation when the aerodynamic loads applied. This deformation changes the aerodynamic loads distribution on the wing that gives a new deformation to the wing structure and vice versa. This interaction in a couple process called as fluid structure interaction (FSI). ANSYS 15.0 software was used to simulate fluid structure interaction on the wing. The unsteadiness and viscous flows at low speed are evaluated using the solution o f timedependent Reynolds Averaged Navier-Stokes (RANS) with SST k-rn turbulent model. In addition, multiblock structured grids are generated to provide more accurate viscous result and to anticipate negative volume o f the mesh which may occur due to the deformation o f the wing during simulation. Five different o f simulations are performed with variation o f material characteristics including Young’s modulus and Poisson’s ratio.The results are global aerodynamic characteristics at various material characteristics.]]>
<![CDATA[Design of helical-blade rotor of Vertical Axis Wind Turbine (VAWT) ]]>
<![CDATA[Buyung Junaidin]]>
<![CDATA[ SENATIK STT Adisutjipto Vol 6 (2020): Keselamatan Penerbangan di masa Pandemi Covid-19 [ISBN 978-602-52742-2-0] ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/senatik.v6i0.439
<![CDATA[The vertical axis wind turbine (VAWT) with helical-blade has been developed, manufactured and applied in almost all developed countries. In Indonesia, vertical axis wind turbines are still not widely applied compared to horizontal axis wind turbines. Vertical axis wind turbines with helical-blade are still very rare in Indonesia. Research and development of the vertical axis wind turbine are needed because of its advantages compared to horizontal axis wind turbine. The advantages are: can operate in various wind directions, lower noise due to smaller tip speed ratio (TSR) and for large-scale, mechanical and electrical systems of turbine can be placed on ground. The aim of this research is to design a vertical axis wind turbine rotor with helical-blade that can be applied at low speeds and changing direction wind condition, such as urban wind characteristics. Performance analysis of wind turbine rotor is done by using double-multiple stream-tube (DMS) model approach. This research yields a rotor of vertical axis wind turbine with helical-blade with rotor length and diameter are 2m and 1m respectively, the rotor blade airfoil is DU-06-W-200 with chord length is 0.2m. From analysis, the optimum tip speed ratio of the rotor is 2.6 with a maximum power coefficient is 0.57.]]>
<![CDATA[Conceptual Design of Electrical Ducted Fan (EDF) ]]>
<![CDATA[Buyung Junaidin]]>;
<![CDATA[M. Ardi Cahyono]]>
<![CDATA[ SENATIK STT Adisutjipto Vol 5 (2019): Peran Teknologi untuk Revitalisasi Bandara dan Transportasi Udara [ISBN 978-602-52742- ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/senatik.v5i0.311
<![CDATA[Electric Ducted Fan (EDF) is an electric propulsion consist of duct, fan and electric motor with main power source is from battery which generates compression air for thrust. EDF is used as an alternative propulsion for high speed UAV especially for target UAV or “bomb” controlled UAV. It’s design is very simple and no need extra maintenance compared to jet engine. Design process of an EDF is more simple than a jet engine, nevertheless it could obtain enough thrust for high speed flying. The aim of this research is to design an EDF as an alternative propulsion for high speed UAV and performance analyzing of EDF using analitical approach. Design of EDF produce an EDF with inlet and outlet diameter are 70mm and 60mm. Total length of EDF is 116,1mm. Performance analysis of EDF shows that by 700W of motor power could reach 16N of thrust which is accepted performace for 70mm EDF.]]>
<![CDATA[AERODYNAMIC CHARACTERISTICS OF AIRFOIL USING PANEL METHOD ]]>
<![CDATA[Buyung Junaidin]]>
<![CDATA[ Angkasa: Jurnal Ilmiah Bidang Teknologi Vol 8, No 1 (2016): Mei ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/angkasa.v8i1.131
<![CDATA[Potential flow over an airfoil plays an important historical role in the theory of flight. The governing equation for potential flow is Laplace’s equation, a widely studied linear partial differential equation. One of Green’s identities can be used to write a solution to Laplace’s equation as a boundary integral. Numerical models based on this approach are known as panel methods in the aerodynamics community. This paper introduces the availability of a computational tool for constructing numerical modelfor potential flow over an airfoil based on panel methods. Use of the software is illustrated by implementing a specific model using Hess and Smith panel method to compute the flow over a member of the NACA four-digit airfoils.]]>
<![CDATA[CONCEPTUAL DESIGN OF BIRD-LIKE UNMANNED AERIAL VEHICLE FOR BIRD PEST CONTROL ]]>
<![CDATA[Buyung Junaidin]]>;
<![CDATA[Dwi Hartini]]>;
<![CDATA[Santo Herlambang]]>
<![CDATA[ Angkasa: Jurnal Ilmiah Bidang Teknologi Vol 12, No 1 (2020): Mei ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/angkasa.v12i1.559
<![CDATA[Finch (Lonchura) pest bird becomes a serious problem for rice-plant farmers when entering harvest period because it could make crop yields decreases or even crop failure. There are many method have been done for pest bird control but almost all of those are not effectives. Bird-like unmanned aerial vehicle is proposed as an alternative solution to control pest bird. The aim of this research is to do conceptual design of unmanned aerial vehicle which look like predator bird for pest bird control in farm area. The predator bird which means is black eagle (Ictinaetus Malaiensis) which is one of natural predators of small birds including finch family. Conceptual design of bird-like unmanned aerial vehicle follows general design process of aircraft with some simplification. Method of design adopt to Raymer’s method and sketching of black eagle planform especially wings and tail. The design results an unmanned aerial vehicle look like black eagle with cruise speed is 10m/s and operational altitude 120m above sea level. From aerodynamics analysis shows that bird-like unmanned aerial vehicle which have designed fill lift requirement at angle of attack 3o and longitudinal static stability criteria. ]]>
<![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[AERODYNAMIC ANALYSIS OF SPORT UTILITY VEHICLE (SUV) BY COMPUTATIONAL FLUID DYNAMICS (CFD) APROACH ]]>
<![CDATA[Buyung Junaidin]]>
<![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[STRENGTH ANALYSIS OF CARGO-X UAV WING STRUCTURE USING SANDWICH COMPOSITE MATERIALS ]]>
<![CDATA[Dwi Hartini]]>;
<![CDATA[Buyung Junaidin]]>;
<![CDATA[Habibi Habibi]]>
<![CDATA[ Vortex Vol 3, No 1 (2022) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v3i1.1153
<![CDATA[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.]]>
<![CDATA[THE SIMULATION OF UNMANNED AERIAL VEHICLE EAGLE-X AS SPARROWS PESTS REPELLENT ]]>
<![CDATA[Nurcahyani Dewi Retnowati]]>;
<![CDATA[Buyung Junaidin]]>;
<![CDATA[Dasrial Dasrial]]>
<![CDATA[ Vortex Vol 3, No 2 (2022) ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/vortex.v3i2.1223
<![CDATA[The technology that can be developed from Unmanned Aerial Vehicle (UAV) in agriculture is the Unmanned Aerial Vehicle Eagle-X. This technology can help farmers in carrying out their daily activities to repel bird pests on agricultural land. However, people have difficulty understanding how to use UAVs. So, with this simulation, it is hoped that it can help farmers and producers understand the workings of the eagle-x aircraft. The simulation is made using 3Ds Max software which functions to create all 3D objects and also uses Unity software to create animations and simulations. This simulation can run well on a PC or laptop that has a Windows 10 operating system with 64bit and a minimum of core i-3 specifications. Trials using simulations were carried out on 30 farmers and the results showed that 86.67% of farmers stated that this simulation was effective in providing an overview of how the Unmanned Aerial Vehicle Eagle-X works in repelling sparrow pests.]]>
<![CDATA[Rancang Bangun Pengukur Kecepatan Angin Berbasis Arduino untuk Terowongan Angin Low Subsonic ]]>
<![CDATA[Buyung Junaidin]]>;
<![CDATA[Anggraeni Kusumaningrum]]>;
<![CDATA[Wisnu Prayogih]]>;
<![CDATA[Yosep Reo]]>
<![CDATA[ Aviation Electronics, Information Technology, Telecommunications, Electricals, Controls (AVITEC) Vol 4, No 2 (2022): August ]]>
Publisher : <![CDATA[Institut Teknologi Dirgantara Adisutjipto ]]>
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DOI: 10.28989/avitec.v4i2.1295
<![CDATA[The wind speed gauge in a wind tunnel plays an important role in the airflow simulation process so that it is similar to the actual conditions as desired. Wind speed measurement in wind tunnel mostly use manometer with special fluid (red manometer fluid) and the resulting data is in the form of analog data. The red manometer fluid is unavailable in Indonesia and its price is quite expensive so it becomes a challenge for wind tunnels that still use manometer. Therefore, it is necessary to make a new instrument for measuring wind speed that is easy to use by utilizing materials that are easily obtained but still apply the same measurement principles as a manometer in measuring wind speed in wind tunnels. The design of the wind speed measuring device can take advantage of microcontroller technology. The wind speed sensor design process goes through three stages including hardware design, software design, and system design. The hardware used for the system are an Arduino Uno R3 microcontroller, a differential pressure sensor MPXV7002DP, and an LCD. Research results obtain a wind speed sensor that can be used to measure wind speed in a low subsonic wind tunnel based on Bernoulli's principle that utilizes a pitot tube with a maximum speed of 30m/s. The wind speed sensor is an Arduino-based design that can display the wind speed measurement results on the LCD screen. The wind speed sensor was declared valid to be used to measure wind speed because there were no deviations from the wind speed measurement when compared to the measurement results from a calibrated anemometer.]]>
