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PENGARUH JARAK LASER HEAD TERHADAP DIAMETER SPOT PADA PEMOTONGAN POLYMETHYL METHACRYLATE MENGGUNAKAN MESIN LASER CUTTING Prihadianto, Braam Delfian; Nugroho, Gesang
Infotekmesin Vol 9, No 01 (2018): Infotekmesin, Januari 2018
Publisher : Politeknik Negeri Cilacap

Laser cutting is one of the processes used as an alternative to conventional machinery that has goodcutting qualities and minimizes product damage. The workings of laser cutting is to direct the output of high laser power on the material to be cut, the material then melts, burns, evaporates by gas, and produces edges with a good quality surface. This study aims to determine the effect of laser head distance from the laser cutting machine on the spot diameter produced on the polymethyl methacrylate (PMMA) material. This study used a laser machine with 60 watts of power and variation of laser head distance with an interval of 1 mm at a distance of 1-28 mm. Spot diameter value was gained measurement from using stereo zoom microscope with 30 X magnification and mapping. The result shows that the spot diameter was 0,229 - 0,990 mm. The factors that affect the value of spot diameter is the laser power used and laser head distance from the material.

Design, manufacture and performance analysis of an automatic antenna tracker for an unmanned aerial vehicle (UAV) Nugroho, Gesang; Dectaviansyah, Dicky
Journal of Mechatronics, Electrical Power and Vehicular Technology Vol 9, No 1 (2018)
Publisher : Research Centre for Electrical Power and Mechatronics, Indonesian Istitutes of Sciences

In conducting a disaster monitoring mission, an unmanned aerial vehicle (UAV) has to travel a long distance to cover the region that is hited by a disaster. In the monitoring mission, Air Data and Attitude Heading Reference System (ADAHRS) data are very important to always be displayed on the ground control station (GCS). Unfortunately, the area of monitoring mission is very wide, whereas the usage of an omnidirectional antenna in the disaster monitoring mission is limited to the UAV maximum range. Therefore, a high gain directional antenna is needed. However, the directional antenna has a disadvantage of always being directed to the target. To solve this problem, antenna tracker is made to track the UAV continuously so that the directional antenna can always be directed to the flying UAV. An antenna tracker using a 32-bit microcontroller and GPS with two degrees-of-freedom was developed. It is able to move 360 degrees on azimuth axis (yaw) and 90 degrees on elevation axis (pitch). Meanwhile, the directional antenna is three elements yagi type with a radiation capability of 6 dBi. By using the antenna tracker, larger UAV range was obtained and the connection between the UAV and the GCS could always be maintained with a minimum fluctuation of RSSI signal, compared to those without using antenna tracker.

Development of a Fixed Wing Unmanned Aerial Vehicle (UAV) for Disaster Area Monitoring and Mapping Nugroho, Gesang; Taha, Zahari; Nugraha, Tedy Setya; Hadsanggeni, Hatyo
Journal of Mechatronics, Electrical Power and Vehicular Technology Vol 6, No 2 (2015)
Publisher : Research Centre for Electrical Power and Mechatronics, Indonesian Istitutes of Sciences

The development of remote sensing technology offers the ability to perform real-time delivery of aerial video and images. A precise disaster map allows a disaster management to be done quickly and accurately. This paper discusses how a fixed wing UAV can perform aerial monitoring and mapping of disaster area to produce a disaster map. This research was conducted using a flying wing, autopilot, digital camera, and data processing software. The research starts with determining the airframe and the avionic system then determine waypoints. The UAV flies according to the given waypoints while taking video and photo. The video is transmitted to the Ground Control Station (GCS) so that an operator in the ground can monitor the area condition in real time. After obtaining data, then it is processed to obtain a disaster map. The results of this research are: a fixed wing UAV that can monitor disaster area and send real-time video and photos, a GCS equipped with image processing software, and a mosaic map. This UAV used a flying wing that has 3 kg empty weight, 2.2 m wingspan, and can fly for 12-15 minutes. This UAV was also used for a mission at Parangtritis coast in the southern part of Yogyakarta with flight altitude of 150 m, average speed of 15 m/s, and length of way point of around 5 km in around 6 minutes. A mosaic map with area of around 300 m x 1500 m was also obtained. Interpretation of the mosaic led to some conclusions including: lack of evacuation routes, residential area which faces high risk of tsunami, and lack of green zone around the shore line.

MOLD DESIGN AND FLOW ANALYSIS FOR PRODUCT PROPELLER APC SF 11X4.7 WITH MINIMUM SHRINKAGE AND WARPAGE Sahputra, Wahyu Puji; Budiyantoro, Cahyo; Nugroho, Gesang; Adam, Muhammad Kevin
Jurnal Rekayasa Mesin Vol. 15 No. 2 (2024)
Publisher : Jurusan Teknik Mesin, Fakultas Teknik, Universitas Brawijaya

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21776/jrm.v15i2.1669

Making molds in the injection molding manufacturing process is one of the basic steps that functions to prevent product defects during the production process. The product defects that most often occur in this manufacturing process include shrinkage and warpage defects. This research will discuss the mold design for the APC SF 11x4.7 propeller product with a twist variation of 45o and minimum shrinkage and warpage values. Glass Fiber Reinforced Polypropylene (GFRPP) will be used as the propeller product material. The entire design process to testing will be carried out using software assistance. The Taguchi method with an L9 orthogonal array matrix (34) was used in this research. where L9 explains that the experiment will be carried out nine times, and 34 means there are three levels and four main factors. The four main factors consist of packing pressure, packing time, melting temperature and injection pressure. The Taguchi method is used with the aim of making it easier to find the variation value that produces the lowest shrinkage and warping defects in the product. The simulation results show that the variation with the smallest shrinkage value produces a value of 7.9% and the variation with the smallest warpage value produces a value of 1.051 mm

Investigation of Dorsal Fin Effects on the Aerodynamic Performance of Inverted-V Empennage VTOL Unmanned Aerial Vehicle Bramantya, Muhammad Agung; Nugroho, Gesang
Machine : Jurnal Teknik Mesin Vol 11 No 2 (2025): Machine : Jurnal Teknik Mesin
Publisher : Jurusan Teknik Mesin Fakultas Sains dan Teknik Universitas Bangka Belitung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.33019/1sy9sm72

Unmanned Aerial Vehicles (UAVs) are becoming essential tools in precision agriculture, enabling real-time monitoring, improved land management, and more efficient use of resources. Among them, Vertical Takeoff and Landing (VTOL) UAVs are ideal for operating in confined and uneven agricultural terrains. However, UAVs equipped with inverted-V empennages suffer from aerodynamic drawbacks, including directional instability and adverse yaw under sideslip conditions. This paper advances the state of the art by optimizing the aerodynamic performance of inverted-V tail configurations through the integration of a dorsal fin. Using Computational Fluid Dynamics (CFD), we assess multiple dorsal fin designs on a UAV platform with a maximum takeoff weight of 10 kg, 2 kg payload, 2-hour endurance, 10 m/s stall speed, and a 5 km² operational range. We analyze key aerodynamic metrics—lift and drag coefficients, lift-to-drag ratio, yaw moment coefficient—as well as flow behavior via pressure contours and vorticity plots. Results confirm that sideslip angles degrade aerodynamic efficiency, but a properly designed dorsal fin, particularly variation 2, significantly reduces adverse yaw at higher angles of attack and sideslip. This modification enhances UAV stability and flight performance, marking a meaningful improvement in VTOL UAV design for agricultural applications.

MOLD DESIGN AND FLOW ANALYSIS FOR PRODUCT PROPELLER APC SF 11X4.7 WITH MINIMUM SHRINKAGE AND WARPAGE Sahputra, Wahyu Puji; Budiyantoro, Cahyo; Nugroho, Gesang; Adam, Muhammad Kevin
Jurnal Rekayasa Mesin Vol. 15 No. 2 (2024)
Publisher : Jurusan Teknik Mesin, Fakultas Teknik, Universitas Brawijaya

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.21776/jrm.v15i2.1669

Making molds in the injection molding manufacturing process is one of the basic steps that functions to prevent product defects during the production process. The product defects that most often occur in this manufacturing process include shrinkage and warpage defects. This research will discuss the mold design for the APC SF 11x4.7 propeller product with a twist variation of 45o and minimum shrinkage and warpage values. Glass Fiber Reinforced Polypropylene (GFRPP) will be used as the propeller product material. The entire design process to testing will be carried out using software assistance. The Taguchi method with an L9 orthogonal array matrix (34) was used in this research. where L9 explains that the experiment will be carried out nine times, and 34 means there are three levels and four main factors. The four main factors consist of packing pressure, packing time, melting temperature and injection pressure. The Taguchi method is used with the aim of making it easier to find the variation value that produces the lowest shrinkage and warping defects in the product. The simulation results show that the variation with the smallest shrinkage value produces a value of 7.9% and the variation with the smallest warpage value produces a value of 1.051 mm

The Analysis of Target Drone Wing Sweep Angle on Dynamic Stall Condition with Pitch Rate Variation using Computational Fluid Dynamics Bramantya, Muhammad Agung; Nugroho, Gesang
TEKNIK Vol 46, No 3 (2025): Juli 2025
Publisher : Diponegoro University

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.14710/teknik.v46i3.54148

A target drone is a type of Unmanned Aerial Vehicle (UAV) with a special mission as a shooting target in the military field. Target drones must be able to fly at high speeds and be agile. This study discusses the influence of the wing sweep angle on the aerodynamic performance of a target drone during dynamic stall conditions. Banshee Whirlwind-like model is used as a research object in this study with the adjustment of the empennage design to a V-Tail configuration. Furthermore, the wing sweep angle was varied to determine its effect on dynamic stall conditions using Computational Fluid Dynamics (CFD) in transient conditions. The wing sweep angle variations used were 5°, 20°, 35°, and 50°, whereas the dynamic stall condition was varied using pitch rates of 3.6°/s, 6°/s, and 18°/s. The aerodynamic performance discussed relates to the lift force, drag force, efficiency, stall angle, lateral stability, and stall development phase. The results of this study indicate that a wing sweep angle of 50° is the most optimal design in terms of stall condition, stability, and maneuverability.

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