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All Journal Jurnal Teknosains Mekanika: Majalah Ilmiah Mekanika Indonesian Journal of Aerospace
Adhynugraha, Muhammad Ilham
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Aerospace Engineering Astronomy Biochemistry, Genetics & Molecular Biology Civil Engineering, Building, Construction & Architecture Industrial & Manufacturing Engineering Mechanical Engineering

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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.
A Study on Lug Structure at Fuselage - Wing Joint of an Unmanned Aerial Vehicle Using Finite Element Method Cahya, Fadli; Pramana, Nurhadi; Chairunnisa; Adhynugraha, Muhammad Ilham; Aribowo, Agus; Nurrohmad, Abian
Indonesian Journal of Aerospace Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2023.272

Abstract

Research on structural analysis of an unmanned aerial vehicle (UAV) is carried out. The primary material used in most structures is carbon composite. Having a high aspect ratio wing, the lugs connecting the wing and fuselage are likely to experience maximum forces during flight tests. In predicting the occurrence of deformation and stress, the finite element method is used by applying max./min. strain criteria to evaluate the structural integrity of composite wings due to the load applied on aluminum-based lugs. The evaluation shows that the current wing configuration has good structural integrity. An optimization approach is also carried out to obtain more optimum results.
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 Agus Aribowo Alfikri, Iqbal Reza Budiarti, Dewi Habsari Cahya, Fadli Chairunnisa Chairunnisa Chairunnisa Majid, Nur Cholis Megawanto, Fadli Cahya Muliadi, Jemie Nami, Osen Fili Nurrohmad, Abian Octaviany, Siti Vivi Pramana, Nurhadi Saraswati, Sherly Octavia Wibowo, Singgih Satrio Wiranto, Ilham Bagus