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All Journal Conference SENATIK STT Adisutjipto Yogyakarta Jurnal Teknologi Kedirgantaraan (JTK) Jurnal Mahasiswa Dirgantara Indonesian Journal of Aerospace
Sahril Afandi S
Universitas Dirgantara Marsekal Suryadarma
Aerospace Engineering Astronomy Computer Science & IT Control & Systems Engineering Electrical & Electronics Engineering Engineering Environmental Science Industrial & Manufacturing Engineering Materials Science & Nanotechnology Mechanical Engineering Transportation

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The Effect of Cross-section and Elliptical Hole Ratio on Crashworthiness Parameters of Crash-Box Structure Warsiyanto, Budi Aji; Widanto, Muhammad Hadi; Musthofa, Ilham; Maulana, Ichsan; Sitompul, Sahril Afandi; Yuniarti, Endah
Indonesian Journal of Aerospace Vol. 19 No. 1 (2021)
Publisher : BRIN Publishing

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.
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.
EFFECT OF FLAT AND HEMISPHERICALLY ENDED CYLINDER BIRD MODEL WITH FINITE ELEMENT MODELLING OF BIRD STRIKE Yuniarti, Endah; Sitompul, Sahril Afandi
Indonesian Journal of Aerospace Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a3061

Abstract

This research studies influence of bird model on impact pressures during bird strike, namely Hugoniot and Stagnation pressure through initial modelling by numerical simulations using finite element method. Finite element simulation of bird strike have primarily modelled the bird as either a flat or hemispherically ended cylinder. The geometry is simulated with different L/D ratio, 1.4, 1.6, 1.8 and 2.0. Elastic-plastic hydrodynamic material model is used in simulation. Bird model simulation are using lagrangian method and initial velocities are 100, 200 and 300 m/s. Simulation results of hemispherically ended cylinder bird models show variation of L/D ratio provide Hugoniot pressure 10-19 times higher than stagnation pressure in L/D = 1.4, 8-18 times in L/D = 1.6, 9-17 times in L/D = 1.8 and 4-16 times in L/D = 2. The Hugoniot pressure shows a lower value at an L/D ratio of 1.6 compared to other ratios and the Stagnation pressure is higher at L/D ratio 2. As for cylindrical bird model show variation of L/D ratio provide Hugoniot pressure 35-38 times higher than stagnation pressure in L/D = 1.4, 30-47 times in L/D = 1.6, 31-52 times in L/D = 1.8 and 28-48 times in L/D = 2. The Hugoniot pressure shows a lower value at an L/D ratio of 1.4 and 1.6 compared to other ratios and the Stagnation pressure is higher at L/D ratio 2.
Co-Authors AA Sudharmawan, AA Abdul Hanafi Adnan Afrianto, Muhammad Faisal Agus Bayu Aji W, Budi amat chaeroni Andriansyah, Dika Aprila Sakti K Budi Aji Warsiyanto Difa Rasyidah, Azzahra Dwi Juniarsah, Fahri Endah Yuniarti, Endah Enggar Kristian fitriansyah, Rizky Fransisco, Romario Freddy Franciscus H, Simon Shindu Hanafi, Abdul Herwanta, Prastyo Ardi Jauharul Akfiya sudjaelan Laksono, Agung Mark Andrew Maulana, Ichsan Muhamad Jayadi Muhammad Faisal Afrianto Muhammad Hadi Widanto Musthofa, Ilham Nafisa, Siti Nur Nurrohmad, Abian Pramana, Nurhadi Prastyo Ardi Herwanda Rabeta, Bismil Rayhan Zhafrando, Muhammad Riskha Agustianingsih Rizki Fitriansyah Rizky fitriansyah Romario Fransisco Ruslan Salsabila, Unik Hanifah Simon Sindhu Hendradjaja Suryo O, Ari Utama, Agus Bayu