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All Journal Warta Ardhia : Jurnal Perhubungan Udara Jurnal Teknologi Kedirgantaraan (JTK) Automotive Experiences Indonesian Journal of Aerospace
Nurrohmad, Abian
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Aerospace Engineering Astronomy Automotive Engineering Chemical Engineering, Chemistry & Bioengineering Control & Systems Engineering Electrical & Electronics Engineering Energy Engineering Environmental Science Materials Science & Nanotechnology Mechanical Engineering Transportation

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Journal : Indonesian Journal of Aerospace

 1 
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.
The effect of Impact Angle on Dynamic Response of 19 Passenger Commuter Aircraft Windshield against Bird Strike Warsiyanto, Budi Aji; Nurrohmad, Abian; Fitriansyah, Rizky; Utama, Agus Bayu; Sitompul, Sahril Afandi; Yuniarti, Endah
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3560

Abstract

This paper's objective was to determine the dynamic response of a 19 passenger commuter aircraft windshield to impact angle variations. The phenomenon was performed using the finite element method, and the smoothed particle hydrodynamics (SPH) was chosen as a method for modeling bird material. The elastic-plastic polymethyl methacrylate (PMMA) material with the maximum principal strain failure criterion was used to model the windshield's dynamic response. The variation of the impact angle consists of 15°, 0°, -8°, and -15°, which are measured of the longitudinal axis of the aircraft. The simulation result showed that the impact angle that causes the windshield's dynamic response in the elastic, plastic deformation, and the greatest failure is the angle -15°. The upper end of the windshield (fixed) is the weakest part due to the stress concentration.
NUMERICAL INVESTIGATION ON THE FUSELAGE AIRFRAME OF LSU 05 NG AIRCRAFT Hafid, M.; Nurrohmad, Abian; Ramadhan, Redha Akbar
Indonesian Journal of Aerospace Vol. 18 No. 2 Desember (2020): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2020.v18.a3327

Abstract

In this paper, numerical investigation on the fuselage structure of LSU 05 NG was carried out. This fuselage is designed to carry the payload up to 30 kg. Statical numerical analysis using finite element method was done using Simulia Abaqus. The fuselage structure that has been design consists of frame, longeron, and skin that can also be semi-monocoque structure. This airframe use combination of balsa and GFRP type of composite as the material. There are three load case: take-off condition, cruise condition, and landing condition. Tsai-hill failure criteria is used to investigate the strength of the composite structure due to the load that applied. Maximum stress from this calculation is 48 Mpa at the ground condition (take-off and landing) while the cruise stress analysis is 16 Mpa. The maximum tsai-hill criterion is 0,83. With such simulation results it can be said that the fuselage structure is still safe when operated and can also be optimized for several components so that the weight of the aircraft can be reduced.
Co-Authors A. Sitompul, Sahril Adhynugraha, Muhammad Ilham Antares, Quincy Aribowo, Agus Budi Aji Warsiyanto Cahya, Fadli Chairunnisa Endah Yuniarti, Endah fitriansyah, Rizky Hafid, M. Hidayat, Dony Ilham Maulana Indriani, Fitri Karina Marta, Aryandi Nugroho, Afid Nuranto, Awang Rahmadi Pramana, Nurhadi Rabeta, Bismil Ramadhan, Redha Akbar Riki Ardiansyah, Riki Sitompul, Sahril Afandi Tjahjono, Arif Utama, Agus Bayu