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Marta, Aryandi
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Aerospace Engineering Astronomy Automotive Engineering Chemical Engineering, Chemistry & Bioengineering Control & Systems Engineering Electrical & Electronics Engineering Energy Materials Science & Nanotechnology Mechanical Engineering

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Crashworthiness Performance Study of 3D-Printed Multi-Cell Tubes Hybridized with Aluminum Under Axial Quasi-Static Testing Ardiansyah, Riki; Indriani, Fitri Karina; Hidayat, Dony; Tjahjono, Arif; Nurrohmad, Abian; Marta, Aryandi
Automotive Experiences Vol 7 No 3 (2024)
Publisher : Automotive Laboratory of Universitas Muhammadiyah Magelang in collaboration with Association of Indonesian Vocational Educators (AIVE)

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.31603/ae.12247

Abstract

This study investigates the crashworthiness performance of 3D-printed hybrid tubes, fabricated using PLA and PACF filaments with varying shell thicknesses (1, 1.5, and 2 mm). The hybrid tubes, composed of a shell, aluminum, and multi-cell structure, were subjected to axial quasi-static testing. Results indicate that both shell thickness and filament type significantly influence crashworthiness. PLA specimens with a shell thickness of 2 mm absorbed 504 J of energy, whereas PACF specimens with the same thickness absorbed only 342.9 J. The deformation mode analysis revealed mixed deformation patterns, including diamond, fracture, and fragmented modes. The study also evaluated specific energy absorption (SEA) and crushing force efficiency (CFE). The PLA specimen with a 2 mm shell thickness exhibited the highest SEA value of 18.61 J/g among all specimens. In contrast, the PACF specimen with the same shell thickness demonstrated the highest CFE value of 0.82 among the tested specimens. Overall, this research contributes insights into the design optimization of 3D-printed hybrid tubes for enhanced crashworthiness.
Effect Of Rubber Damper Stiffness And Tire Pressure To Reduce Ground Reaction Load Factor On Main Landing Gear Using Multi-Body Simulation (MBS) Rigid Model Hidayat, Dony; Istiyanto, Jos; Marta, Aryandi; Hidayat, Kurnia; Sumarsono, Danardono Agus
Indonesian Journal of Aerospace Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a3131

Abstract

Landing Gear Drop Test (LGDT) utilizes the apparatus requiring a substantial time and cost. Virtual LGDT (vLGDT) using MSC ADAMS software is one of the solutions for initial stage to testing landing gear. From simulation with vsink 1.7 m/s and load 22000 N obtained contact/impact force that ensue in MSC ADAMS was 73650 N, while from experimental was 73612 N. The difference between vLGDT and LGDT result is 0.05 %. To obtain ground reaction load factor below 3 in vsink = 3.05 m/s, the rubber damper should have stiffness in the range of 1900 - 2100 N/mm and for the tire pressure of 60 - 65 psi.
INVESTIGASI GAYA KONTAK/IMPAK PADA MAIN LANDING GEAR PESAWAT KOMUTER DENGAN PENDEKATAN MULTI-BODY SIMULATION (MBS) RIGID MODELS Hidayat, Dony; Istiyanto, Jos; Sumarsono, Danardono Agus; Marta, Aryandi
Indonesian Journal of Aerospace Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2017.v15.a2529

Abstract

Pengujian landing gear yang bertujuan untuk mengetahui karakteristik gaya kontak/impak yang terjadi saat touchdown landing telah dilakukan. Pengujian eksperimental menggunakan apparatus membutuhkan waktu yang lama dan biaya yang besar. Vitual Landing Gear Drop Test (vLGDT) menggunakan perangkat lunak MSC ADAMS merupakan salah satu alternatif untuk pengujian tahap awal landing gear. Dari simulasi menggunakan vLGDT diperoleh nilai k = 5.0e5 N/m dan cmax = 1600 N.detik/m. Gaya kontak/impak yang terjadi pada simulasi menggunakan vLGDT sebesar 75996 N, sedangkan dari eksperimental sebesar 73612 N. Hasil vLGDT lebih besar 3.14% dibandingkan eksperimental.
Ahmad Alsahlani and Thurai Rahulan, 2017, Composite Structural Analysis of a High Altitude, Solar Powered Unmanned Aerial Vehicle, International Journal of Mechanical Engineering and Robotics Research Vol. 6, No. 1, January 2017 Atik Bintoro, 2016, Lend Marta, Aryandi; Bintoro, Atik
Indonesian Journal of Aerospace Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2018.v16.a2962

Abstract

The characteristic model of MUS-01 wing structure testing has been performed. Planned, this model will be used as an unmanned wing of the LSU-03NG. The test model is made of composite type e-glass. At the time of testing the structure test model is loaded according to MTOW weight. This research method also involves the unmanned aircraft mission, especially on the model test structure, model dimension, and direct experiment in the form of loading on the test model. The result of characterization of the test model during test, showed that the indicated test model has the characteristics as a test model that is unable to accept the unmanned operational load of LSU-03NG series aircraft. So it can not be used as a consideration for the structure of the unmanned aircraft.
RANCANG BANGUN SISTEM PENGUJIAN MOTOR BRUSHLESS UNTUK APLIKASI SOLAR-LAPAN SURVEILLANCE UAV BERBASIS LABVIEW (DESIGN OF BRUSHLESS MOTOR PERFORMANCE TESTING SYSTEM FOR SOLAR-LAPAN SURVEILLANCE UAV APPLICATION BASED ON LABVIEW) Sugiarto, Tommy; Setyadewi, Imas Tri; Marta, Aryandi; P., Gunawan Setyo
Indonesian Journal of Aerospace Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

Tantangan terbesar dalam pengembangan pesawat tanpa awak adalah keterbatasan energi. Salah satu solusi masalah tersebut adalah dengan menggunakan energi alternatif diantaranya sel surya. Aplikasi pesawat tanpa awak dengan sel surya membutuhkan analisa perhitungan kebutuhan daya pesawat saat terbang, analisa tersebut akan berguna untuk menentukan spesifikasi komponen yang akan digunakan pada pesawat. Penelitian ini akan membahas rancang bangun sistem pengujian kinerja motor brushless untuk aplikasi pada Solar LAPAN Surveillance UAV (LSU) menggunakan perangkat lunak LabVIEW. Dari hasil pengujian sistem ini mampu melakukan pengukuran dengan galat sebesar 1.27%,0.61%, dan 5.65% masing masing untuk pengukuran RPM, tegangan dan arus pada baterai.
Co-Authors Bintoro, Atik Hidayat, Dony Hidayat, Dony Hidayat, Kurnia Indriani, Fitri Karina Jos Istiyanto Nurrohmad, Abian P., Gunawan Setyo Riki Ardiansyah, Riki Setyadewi, Imas Tri Sugiarto, Tommy Sumarsono, Danardono Agus Tjahjono, Arif