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All Journal Jurnal Teknosains Majalah Ilmiah Pengkajian Industri Mekanika: Majalah Ilmiah Mekanika
Megawanto, Fadli Cahya
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Aerospace Engineering Biochemistry, Genetics & Molecular Biology Chemical Engineering, Chemistry & Bioengineering Civil Engineering, Building, Construction & Architecture Engineering Industrial & Manufacturing Engineering Mechanical Engineering Transportation

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KAJIAN TEKNIS MODIFIKASI SENJATA LARAS PANJANG UNTUK PRAJURIT TNI Megawanto, Fadli Cahya
Majalah Ilmiah Pengkajian Industri Vol 11, No 3 (2017): Majalah Ilmiah Pengkajian Industri
Publisher : BPPT

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (622.215 KB) | DOI: 10.29122/mipi.v11i3.2249

Abstract

Rekayasa alutsista melalui modifikasi teknis (re-engineering) dengan kemampuan mandiri merupakan salah satu upaya untuk meningkatkan kemampuan penguasaan teknologi industri pertahanan nasional. Memodifikasi senjata api M-16 sebagai senjata serbu ringan laras panjang, berkaliber 5.56 mm menjadi senjata laras pendek untuk pertempuran jarak pendek di kapal dapat menginisiasi rancang bangun senjata untuk prajurit TNI AL. Dalam kajian pertempuran di dalam ruang kapal, penggunaan senjata laras panjang standar TNI tipe M-16 dirasa kurang optimal. Ruang gerak prajurit yang sempit dengan jarak tembak relatif dekat, maka senjata serbu laras pendek akan lebih baik. Berkaitan dengan hal tersebut senjata serbu M-16 milik TNI AL  dicoba dimodifikasi dengan cara pemendekan laras maupun penggantian laras sesuai postur dan misi tempur prajurit TNI. Dalam kajian disini ditelaah hasil modifikasi senjata laras panjang M16 yang sesuai untuk digunakan prajurit TNI namun tetap mempunyai kinerja penembakan yang optimal..
EXHAUST TEMPERATURE ANALYSIS OF UAV PROPELLER MATERIALS Mukti, Suherman; Megawanto, Fadli Cahya; Arthaa, Hari
Majalah Ilmiah Pengkajian Industri Vol. 14 No. 2 (2020): Majalah Ilmiah Pengkajian Industri
Publisher : Deputi TIRBR-BPPT

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.29122/mipi.v14i2.4036

Abstract

This paper presents an exhaust temperature analysis of a UAV Propeller Material to maintain the performance of the propulsion system during operation, especially in a long-range condition. A pusher Propeller experiences direct contact with heat from the exhaust gas. In this study, a Beechwood material with a protective layer of corrosion prevention is used as a propeller blade that works at a range of high temperatures. An experimental methodology was carried out to analyse the strength and propeller deformation. The results of this experimental study show that conservatively the propeller will be heated to 32.9°C. Since this is below the temperature limit, the exhaust gas to pusher propeller on UAV does not affect the propeller performance.Key Words: Exhaust; Temperature; UAV; Propeller; Wood
Male uav longitudinal stability determination using wind tunnel data Adhynugraha, Muhammad Ilham; Megawanto, Fadli Cahya; Octaviany, Siti Vivi; Budiarti, Dewi Habsari; Muliadi, Jemie; Nami, Osen Fili; Wibowo, Singgih Satrio
Jurnal Teknosains Vol 14, No 1 (2024): December
Publisher : Universitas Gadjah Mada

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.22146/teknosains.89420

Abstract

Unmanned aerial systems have been increasing in demand for a wide range of operations, including the rapid growth of advanced navigation and communication. One of the most important things in designing an Unmanned Aerial System (UAS) is to ensure the system's stability, such as the UAS itself. This study was conducted on an in-house medium altitude long endurance (MALE) UAS aircraft. It is focused on analyzing the longitudinal stability of MALE UAS. A mathematical approach was used to analyze the longitudinal stability.  A series of wind tunnel tests using a scaled model of the MALE UAS is done to produce several sets of data containing longitudinal stability derivatives for various configurations. A few sets of data are chosen to obtain the stability derivatives needed. These stability derivatives are utilized to determine the longitudinal motion characteristic of the aircraft. The analysis of certain derivatives and the phugoid and short-period mode shows that the aircraft is statically and dynamically stable in longitudinal motion. The results indicated that a weight change prompted an altercation in the natural frequency of the short-period mode. The response also showed that reaching a new equilibrium state takes a rather long period after an arbitrary perturbation is initiated. The time required to subdue oscillation in axial and average velocities is more than 100 seconds. The stability in the pitch rate is reached in around 65 seconds. The time to reach stability in pitch angle response is around 65 seconds.
Effect of Boundary Condition on Numerical Study of UAV Composite Skin Panels Under Dynamic Impact Loading Wiranto, Ilham Bagus; Saraswati, Sherly Octavia; Alfikri, Iqbal Reza; Chairunnisa, Chairunnisa; Megawanto, Fadli Cahya; Adhynugraha, Muhammad Ilham; Majid, Nur Cholis
Mekanika: Majalah Ilmiah Mekanika Vol 23, No 1 (2024): MEKANIKA: Majalah Ilmiah Mekanika
Publisher : Universitas Sebelas Maret

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.20961/mekanika.v23i1.77875

Abstract

In this study, a dynamic impact loading using Finite Element Analyses (FEA) was applied to an Unmanned Aerial Vehicle (UAV) composite skin panel. Two types of boundary condition panels were investigated (Fixed and Pinned). The composite UAV skin panel consists of upper panel and stiffener which have a thickness of 3 mm and 2 mm, respectively. The material properties used in this study was referring to Hexcel W3G282-F593 technical data sheet. A hemispherical steel indenter with 70 mm diameter and 120 kg of mass was used to crush the panel with a velocity of 4.43 m/s. The finite element analyses were performed using dynamic explicit solver in ABAQUS 6.23. At the beginning of study, the mesh convergence study was conducted to choose the proper mesh for main analysis. The convergence study was simulated using 20 kg mass to shorten computational time. The mesh size of 10 mm was chosen for the main analysis due to convergent result and short computational time compared to others mesh size. The impact deformation, contact force-displacement plot, and contact force-time plot was used to show the differences of using those boundary condition. The results show that fixed and pinned boundary condition reaches its contact force peak with the value of 29.2 kN and 22.8 kN, respectively.
Co-Authors Adhynugraha, Muhammad Ilham Alfikri, Iqbal Reza Arthaa, Hari Budiarti, Dewi Habsari Chairunnisa Chairunnisa Majid, Nur Cholis Mukti, Suherman Muliadi, Jemie Nami, Osen Fili Octaviany, Siti Vivi Saraswati, Sherly Octavia Wibowo, Singgih Satrio Wiranto, Ilham Bagus