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All Journal Jurnal Fisika Unand Jurnal Teknologi Dirgantara Jurnal Teknologi Kedirgantaraan (JTK) Bubungan Tinggi: Jurnal Pengabdian Masyarakat Prosiding Seminar Nasional Ilmu Teknik Dan Aplikasi Industri Fakultas Teknik Universitas Lampung Jurnal Mahasiswa Dirgantara
Budi Aji Warsiyanto
Universitas Dirgantara Marsekal Suryadarma
Aerospace Engineering Chemical Engineering, Chemistry & Bioengineering Civil Engineering, Building, Construction & Architecture Computer Science & IT Control & Systems Engineering Earth & Planetary Sciences Electrical & Electronics Engineering Energy Engineering Environmental Science Industrial & Manufacturing Engineering Materials Science & Nanotechnology Mechanical Engineering Physics Social Sciences Transportation Other

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Journal : Jurnal Teknologi Dirgantara

 1 
The Effect of Cross-section and Elliptical Hole Ratio on Crashworthiness Parameters of Crash-Box Structure Budi Aji Warsiyanto
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3408

Abstract

The thin-walled column structure or crash-box with metal material and consisting of multi-cell were found to be much more efficient in energy absorption than single-cell under axial impact loads. In this study, a numerical analysis was performed using the Abaqus finite element method for the cross-section differences in thin-walled column structures. The cross-section differences are compared to get a configuration that complies with the indicator parameters using the complex proportional assessment (COPRAS) method. The chosen cross-section configuration is further enhanced by creating elliptical holes with different diameter ratios. The results show that the thin-walled column structure with nine-cell cross-section accompanied by an elliptical hole ratio of 0.3 indicates the potential corresponding to the indicator parameters for the crashworthiness application.
Dynamic response of the wing during UAV collision Budi Aji Warsiyanto
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3514

Abstract

An airborne collision between civil Unmanned Aerial Vehicles (UAVs) and manned aircraft is a potential threat to aircraft operation safety. In this paper, the UAV collision test was performed on a commuter aircraft wing section to investigate the dynamic response of this primary operation component. The projectile was a 735 g drone named ‘Mavic’. Explicit dynamic code ABAQUS was employed to simulate the collision process based on the difference of collision scenarios to assess the hazard. The results showed that 735 g drone impact at the aircraft maximum approach flap and cruising speed could cause some damage on the wing front spar and the situation is more serious than 910 g bird strike in which the hardness of drone components rather than kinetic energy is a decisive factor. The lithium-ion battery penetrated the airframe which may be a potential source of ignition.
The effect of Impact Angle on Dynamic Response of 19 Passenger Commuter Aircraft Windshield against Bird Strike Budi Aji Warsiyanto
Jurnal Teknologi Dirgantara Vol 19, No 2 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

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.
Co-Authors A B Utama A Nurrohmad* amat chaeroni Ayu Martina Endah Yuniarti, Endah Fairuza, Syarifah Freddy, Franciscus muftiarifin Muhammad Hadi Widanto Pangihutan Tambunan R Fitriansyah Rafika Arum Sari Rizky fitriansyah S A Sitompul Sitompul, Sahril Afandi