UAVs are controlled aircraft without the presence of pilots in them. In its use, UAVs have been used for both military and civilian purposes. In the field of plantations, UAVs are used for mapping and monitoring (survey) of an area such as areas of industrial plantations, oil palm plantations and areas of forest fire disaster in a timely and precise manner. To develop a UAV capable of carrying out the mission of mapping the coastal estate’s area, in this research is done wing design UAV which is named serindit V-1. The design process begins with the design concept, then proceed with a preliminary design that aims to determine the dimensions and initial configuration of the wing UAV serindit V-1. Furthermore, the wing UAV serindit V-1 is simulated on XFLR5 software using Clark’s airfoil, GOE 611 and S7055. Simulations were performed to see the characteristics of aerodynamic at takeoff speed (12 m / s), cruising speed (20 m / s) and maximum speed (30 m / s). Simulation result at the take-off speed and cruising speed show the lift coefficients produced by the three airfoils meet the requirements. Then, the highest value of the lift coefficient ratio to the air drag coefficient at cruising speed, produced by airfoil S7055 at a 3-degree angle of attack. Furthermore, the graph of the pitching moment coefficient on all angles of attack produced by the three airfoils shows a negative gradient. This shows the condition of wing stability in the pitching direction.
One of a potential application of Empty Palm Fruit Bunch (EPFB) is the material of fuselage on Unmanned Aerial Vehicle (UAV). This study was began by Alkali Treatment on EPFB. Then, the fuselage was molded using Vacuum Bagging Method. There are three unit of mold with combination of fiberglass + carbon fiber, fiberglass + EPFB fiber and full EPFB fiber. The measurement show fuselage with hybrid composite material (fiberglass and EPFB) has the lightest mass of 559 gram. Deflection Test of all three fuselages show that the maximum deflections were under 1 mm. Next, the Static Impact Test show no damages or cracks on all three fuselages. The result of Flight Test show all fuselages could do well fly and survive belly landing.
To upgrade aerial vehicle of Atha Mapper 2150 capable of vertical take-off and landing capability, it needs to be integrated to the tricopter vehicle. In this study the tricopter frame structure was designed based on the Atha Mapper 2150 fixed wing vehicle. This study began with a calculation process to determine the dimensions of the tricopter.. Next, the process of building four tricopter concept designs with variations of the shape of the frame and the cross section of the arm. The four concept designs are selected using a decision matrix. Based on the values in decision matrix table, the design concept I (Y configuration and rectangular arm cross section) was the best design, because it has the highest weighting value. The selected design was then simulated for its structural strength in Ansys software by giving a load of thrust to the three arms of the tricopter frame. In the middle of frame is given a boundary condition in the form of hinges. From the static simulation results of the tricopter frame structure, the maximum stress value was 54,126 MPa, which occurred on the M3 arm. The greatest total deformation also occurred in the M3 arm with a value of 10,335 mm. The safety factor value of tricopter frame structure was 8.77. This shows the tricopter frame structure with the main material in the form of carbon fiber, acrylic and PLA meets the required safety criteria.
Serindit V-2 is an unnamed aircraft by the Serindit Aero UAV research team. It has the ability to fly rapidly in order to compete in KRTI in the Racing Plane division. Although it has been successfully produced and able to fly, comprehensive research on aerodynamic of Serindit V-2 aircraft flying behavior has never been done before. Aerodynamic research needs to be conducted to improve the aircraft performance such as flying capability, air resistance efficiency and etc. This study aims to determine the value of flow characteristic such as coefficient of drag, lift, moment and pressure distribution based on fluid flow that occurs in the aircraft with variations of Angle of Attack and air velocity. The method used is CFD (Computational Fluid Dynamic) which is a computer-based numerical method and performed with an iterative procedure to predict aerodynamic characteristics and fluid flow phenomena on the aircraft surface. Simulations were carried out using Ansys Fluent 2017 software on the Serindit V-2 aircraft model sourced from the Serindit Aero Team. The result of the lift coefficient value is CLo=0.3666 and CLMax value = 1.42626 at α 13o. The CDo obtained was 0.0589258. While the CMo value obtained is -8.34 x 10-5.
UAV Serindit V-1 merupakan wahana terbang tanpa awak tipe fixed wing yang didesain khusus untuk pemetaan atau monitoring wilayah terpencil seperti area perkebunan. Saat menjalankan misi pemetaan dan monitoring, wahana ini hanya mampu membawa kapasitas payload sebesar 250 gram dan terbang selama 10 menit dengan jangkauan terbang sejauh 5 kilometer. Untuk meningkatkan kapasitas payload dari wahana terbang UAV serindit V-1, perlu upaya peningkatan koefisien gaya angkat yang dihasilkan oleh sayap UAV Serindit V-1. Pada penelitian ini, upaya peningkatan koefisien gaya angkat dilakukan melalui desain perangkat Hight Lift Device (HLD). Perangkat hight lift device yang telah didesain, kemudian disimulasikan pada software XFLR5. Berdasarkan simulasi yang dilakukan, perangkat HLD dengan sudut defleksi sebesar 00 (flapless), 40, 80, 120, 160 dan 200 menghasilkan koefisien gaya angkat masing-masing sebesar 0,414; 0,484; 0,551; 0,616; 0,679 dan 0,74. Pada sudut defleksi yang sama, perangkat HLD menghasilkan koefisien gaya hambat udara masing – masing sebesar 0,017; 0,0235; 0,033; 0,045; 0,06 dan 0,076. Sedangkan untuk glide ratio, pada sudut defleksi perangkat HLD sebesar 00 (Flapless), 40, 80, 120, 160 dan 200 masing-masing menghasilkan lift drag ratio sebesar 24,296; 20,596; 16,697; 13,632; 11,363 dan 9,75.
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