Garuda - Garba Rujukan Digital

STUDI ALIRAN 3-D NEAR ENDWALL PADA INTERAKSI AIRFOIL DAN PLAT DATAR Rachman, Arfidian; Yuana Dewi, Arfita; Effendi, Asnal
Jurnal Teknologi dan Vokasi Vol 2 No 2 (2024): Jurnal Teknologi dan Vokasi
Publisher : ITP Press

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21063/jtv.2024.2.2.106-112

Studies of the existence of these secondary flow structures are based on the effect of the emergence of secondary flows in the wing-body configuration on aircraft, i.e. the presence of wingtip-vortex on the tip region and the creation of several elements of the vortex flow on the endwall region, both of which together will cause the blockage of the main flow. The existence of this blockage effect will affect the aerodynamic characteristics of the lift and drag, where it directly affects the effectiveness and efficiency of the wing. In the endwall area the phenomenon can be observed is the shift of the position of the saddle point towards the pressure side. Whereas from the isobar contour the movement of the minimum pressure point on the upper surface is found to be closer to the leading edge, and the area of maximum pressure on the lower surface moves towards the press side. The research will be conducted experimentally on a wing geometry variation modeled on a flat plate with an angle of attack variation (α) = 0o.

PERANCANGAN SISTEM KENDALI HEXACOPTER MENGGUNAKAN FUZZY LOGIC CONTROL Al, Al; Saputra, Arifwindi; Premadi, Aswir; Effendi, Asnal; Dasman, Dasman
Jurnal Teknologi dan Vokasi Vol 3 No 1 (2025): Jurnal Teknologi dan Vokasi
Publisher : ITP Press

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21063/jtv.2025.3.1.87-95

The development of hexacopters has progressed significantly in both hardware and software, leading to increased complexity. Despite these advancements, several challenges remain. The nonlinear, multivariable, and dynamic nature of hexacopter systems often results in flight instability, suboptimal precision in movements, and reduced flight duration. To address these issues, this study proposes the implementation of a fuzzy logic control (FLC) system to enhance the performance and stability of hexacopters during flight. The control system aims to minimize rise time, settling time, and overshoot. The research methodology involves developing a mathematical model of the open-loop system using the System Identification Toolbox in MATLAB, optimizing PID values through the PID Tuner, and designing the fuzzy control system based on error and delta error. The open-loop system demonstrates performance metrics of rise time (Tr) 4.60 s, delay time (Td) 2.76 s, peak time (Tp) 6.50 s, settling time (Ts) 5.91 s, and overshoot (Mp) 1.29%. With PID control, the performance improves to rise time (Tr) 3.24 s, delay time (Td) 1.85 s, peak time (Tp) 10.00 s, settling time (Ts) 9.55 s, and overshoot (Mp) 0%. Furthermore, the fuzzy logic controller achieves superior results with rise time (Tr) 3.19 s, delay time (Td) 1.53 s, peak time (Tp) 4.64 s, settling time (Ts) 3.37 s, and overshoot (Mp) 0%.

STUDI NUMERIK ALIRAN 3D INTERAKSI AIRFOIL DAN PLAT DATAR Rachman, Arfidian; Yuana Dewi, Arfirta; Effendi, Asnal
Jurnal Teknologi dan Vokasi Vol 3 No 1 (2025): Jurnal Teknologi dan Vokasi
Publisher : ITP Press

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21063/jtv.2025.3.1.101-107

The effect of secondary flows in the wing-body configuration on aircraft—that is, the presence of wingtip-vortex on the tip region and the creation of multiple elements of the vortex flow on the endwall region—is the basis for studies of the existence of these secondary flow structures. These two factors combined will obstruct the main flow. The presence of this blocking effect will have an impact on the lift and drag aerodynamics, which directly impacts the wing's efficacy and efficiency. The saddle point's position shifting toward the pressure side is a phenomenon that can be seen in the endwall area. On the other hand, the area of maximum pressure on the lower surface travels towards the press side, and the movement of the minimum pressure point on the upper surface is found to be closer to the leading edge based on the isobar contour. The study will be carried out experimentally on a flat plate model with a wing shape change with an angle of attack variation (α) = 0o.

EXPERIMENTAL ANALYSIS OF HEAT RECOVERY WHEEL FOR TROPICAL CLIMATE Rachman, Arfidian; Yuana Dewi Rachman, Arfita; Effendi, Asnal; Nesti, Lisa
Jurnal Teknologi dan Vokasi Vol 2 No 1 (2024): Jurnal Teknologi dan Vokasi
Publisher : ITP Press

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21063/jtv.2024.2.1.92-96

This paper presented and used experimental analysis to examine design that integrates an active heat recovery wheel mechanism into a windcatcher. A rotational thermal heat recovery is incorporated into the windcatcher channel of the proposed system. An experiment was conducted to examine how the heat recovery mechanism affected the windcatcher performance, demonstrating the system ability to provide the necessary fresh air rates. A test room model, measuring 4x4x3 meters and depicting a small classroom, was integrated with the windcatcher model. Ventilation rates managed to supply sufficient ventilation even with the rotational heat recovery wheel blocked. This active recovery has the potential to lessen the demand on space heating systems in addition to providing enough ventilation. The heat in the exhaust airstreams was caught and transferred to the incoming airstream, boosting the temperature between 7-9oC depending on the indoor/outdoor conditions. This indicates that there is a great deal of room for further development of the idea, allowing for larger-scale testing and investigation of the system's heat transfer characteristics.

KARAKTERISTIK SISTEM PEMBANGKIT LISTRIK TENAGA SURYA KAPASITAS 100 WP Madona, Maisyara; Effendi, Asnal; Dasman, Dasman; Alfith, Alfith; Al, Al
Jurnal Teknologi dan Vokasi Vol 2 No 2 (2024): Jurnal Teknologi dan Vokasi
Publisher : ITP Press

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21063/jtv.2024.2.2.22-29

The energy crisis is a major problem in Indonesia, especially the problem of electrical energy. Electrical energy is energy that is important for humanity throughout the world. We can see from people's activities that cannot be separated from the use of electricity, such as the use of devices and technology that are currently used all using electricity. This phenomenon proves that electricity is very important and cannot be separated from community activities. For some time now, experts have changed their views regarding the use of energy resources in Indonesia. Be aware that fossil fuels, the main energy source, will be threatened with scarcity in the coming years. This research method uses a design/prototype method by making equipment and carrying out a series of tests and collecting data. Based on data that has been in sunny and cloudy weather, solar panels can produce the highest voltage of 17.79 which occurs between 12.30 to 16.30. while the lowest voltage produced by solar panels is around 12,6 Volts for the highest temperature of 34ºC for the highest current is 4,4 A and the highest light intensity is 64422 lux.

PERENCANAAN SISTEM KENDALI MODEL REFERENCE Al, Al; Rahmawati, Gusri; Premadi, Aswir; Effendi, Asnal
Jurnal Teknologi dan Vokasi Vol 2 No 2 (2024): Jurnal Teknologi dan Vokasi
Publisher : ITP Press

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21063/jtv.2024.2.2.37-46

The commercial use of drones has increased rapidly in this sector in the last few decades, one of which is the Hexacopter Type Unmanned Aerial Vehicle (UAV). Hexacopter is a flying robot without a pilot that can be controlled manually using a remote control and controlled automatically or on autopilot. The advantage of the hexacopter is its ability to maneuver flexibly, it can move in 8 cardinal directions without needing to turn first. However, despite their advantages, certain hexacopters must continue to fly stably under a variety of changing conditions, such as changing weather, different loads, or changing environmental conditions. For this reason, a control system is needed that is able to adapt to these changes. This condition makes it interesting to carry out experimental and simulation studies, namely designing a hexacopter with Model Referene Adaptive Control (MRAC) control. By using a Model Reference Adaptive Control (MRAC) control system with the main control using PID control, the response given is good and optimal, the system parameters reach the values: rise time (ts) 1.0709 s, delay time (td) 0.99 s, peak time (tp ) 2.6600 s, settling time (ts) 3.9351 s, overshoot (mp) 4.0847 and steady state error 0.0001%. The mathematical analysis of the MRAC control system needs to be studied in more depth so that the MRAC control calculations become more accurate.

SISTEM TRACKING DAN MONITORING MOBIL RENTAL MENGGUNAKAN SENSOR GPS BERBASIS NODEMCU ESP32 Alfith, Alfith; Effendi, Asnal; Al, Al; Maulana, Rizki
Jurnal Teknologi dan Vokasi Vol 2 No 2 (2024): Jurnal Teknologi dan Vokasi
Publisher : ITP Press

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21063/jtv.2024.2.2.84-96

Obtained conditions in which the Neo6 GPS module can detect the Earth's coordinates in the form of latitudes and volumes as well as the speed of the vehicle's movement to its coordinates. The app knows where you are based on the coordinates, speed, and impact of the car. In addition, the app sends speed warning notifications. In addition, the application can detect the correct or incorrect username and password to protect the view form. In addition, for research on a straight road and at a constant speed, the accuracy of the equipment will be tested by collecting GPS speed data and actual speed data if there is a significant change in speed in a short period of time. With four vehicle collision detection positions, testing this system yields an accurate conditional value. If an accident occurs, it will be immediately sent to the application and sent to a vehicle crash site used, as well as to the firebase database.

STUDI ALIRAN 3-D NEAR ENDWALL PADA INTERAKSI AIRFOIL DAN PLAT DATAR Rachman, Arfidian; Yuana Dewi, Arfita; Effendi, Asnal
Jurnal Teknologi dan Vokasi Vol 2 No 2 (2024): Jurnal Teknologi dan Vokasi
Publisher : ITP Press

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21063/jtv.2024.2.2.106-112

Studies of the existence of these secondary flow structures are based on the effect of the emergence of secondary flows in the wing-body configuration on aircraft, i.e. the presence of wingtip-vortex on the tip region and the creation of several elements of the vortex flow on the endwall region, both of which together will cause the blockage of the main flow. The existence of this blockage effect will affect the aerodynamic characteristics of the lift and drag, where it directly affects the effectiveness and efficiency of the wing. In the endwall area the phenomenon can be observed is the shift of the position of the saddle point towards the pressure side. Whereas from the isobar contour the movement of the minimum pressure point on the upper surface is found to be closer to the leading edge, and the area of maximum pressure on the lower surface moves towards the press side. The research will be conducted experimentally on a wing geometry variation modeled on a flat plate with an angle of attack variation (α) = 0o.

PERANCANGAN SISTEM KENDALI HEXACOPTER MENGGUNAKAN FUZZY LOGIC CONTROL Al, Al; Saputra, Arifwindi; Premadi, Aswir; Effendi, Asnal; Dasman, Dasman
Jurnal Teknologi dan Vokasi Vol 3 No 1 (2025): Jurnal Teknologi dan Vokasi
Publisher : ITP Press

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21063/jtv.2025.3.1.87-95

The development of hexacopters has progressed significantly in both hardware and software, leading to increased complexity. Despite these advancements, several challenges remain. The nonlinear, multivariable, and dynamic nature of hexacopter systems often results in flight instability, suboptimal precision in movements, and reduced flight duration. To address these issues, this study proposes the implementation of a fuzzy logic control (FLC) system to enhance the performance and stability of hexacopters during flight. The control system aims to minimize rise time, settling time, and overshoot. The research methodology involves developing a mathematical model of the open-loop system using the System Identification Toolbox in MATLAB, optimizing PID values through the PID Tuner, and designing the fuzzy control system based on error and delta error. The open-loop system demonstrates performance metrics of rise time (Tr) 4.60 s, delay time (Td) 2.76 s, peak time (Tp) 6.50 s, settling time (Ts) 5.91 s, and overshoot (Mp) 1.29%. With PID control, the performance improves to rise time (Tr) 3.24 s, delay time (Td) 1.85 s, peak time (Tp) 10.00 s, settling time (Ts) 9.55 s, and overshoot (Mp) 0%. Furthermore, the fuzzy logic controller achieves superior results with rise time (Tr) 3.19 s, delay time (Td) 1.53 s, peak time (Tp) 4.64 s, settling time (Ts) 3.37 s, and overshoot (Mp) 0%.

STUDI NUMERIK ALIRAN 3D INTERAKSI AIRFOIL DAN PLAT DATAR Rachman, Arfidian; Yuana Dewi, Arfirta; Effendi, Asnal
Jurnal Teknologi dan Vokasi Vol 3 No 1 (2025): Jurnal Teknologi dan Vokasi
Publisher : ITP Press

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21063/jtv.2025.3.1.101-107

The effect of secondary flows in the wing-body configuration on aircraft—that is, the presence of wingtip-vortex on the tip region and the creation of multiple elements of the vortex flow on the endwall region—is the basis for studies of the existence of these secondary flow structures. These two factors combined will obstruct the main flow. The presence of this blocking effect will have an impact on the lift and drag aerodynamics, which directly impacts the wing's efficacy and efficiency. The saddle point's position shifting toward the pressure side is a phenomenon that can be seen in the endwall area. On the other hand, the area of maximum pressure on the lower surface travels towards the press side, and the movement of the minimum pressure point on the upper surface is found to be closer to the leading edge based on the isobar contour. The study will be carried out experimentally on a flat plate model with a wing shape change with an angle of attack variation (α) = 0o.

Title

Found 25 Documents
Search

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Title Search

Found 25 Documents Search

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Title

Found 25 Documents
Search