Article Per Year (5 Year)
p-Index From 2021 - 2026
0.408
P-Index
This Author published in this journals
All Journal Warta Ardhia : Jurnal Perhubungan Udara Mesin
Putra, Ichsan Setya
Fakultas Teknik Mesin Dan Dirgantara, Institut Teknologi Bandung
Mechanical Engineering Transportation

Published : 8 Documents Claim Missing Document
Claim Missing Document
Check
Articles

Found 8 Documents
Search

 1 
Karakterisasi Sifat Mekanik Mild Steel St37 dan High Strength Steel CR420LA pada Laju Regangan Menengah Gunawan, Leonardo; Dimas, Agustinus; Jusuf, Annisa; Dirgantara, Tatacipta; Putra, Ichsan Setya
Mesin Vol 25, No 2 (2016)
Publisher : Mesin

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (681.695 KB)

Abstract

Untuk mendapatkan prediksi respon yang cukup akurat dalam analisis tabrakan kendaraan darat, dimana terjadi pembebanan dan deformasi struktur dalam waktu yang cepat, diperlukan data sifat mekanik material pada berbagai laju regangan. Makalah ini menyajikan pengukuran sifat mekanik Mild Steel St37 dan High Strength Steel CR420LA pada kondisi kuasi-statik dengan laju regangan 0.001 s-1 dan pada kondisi dinamik dengan laju regangan 0.1 s-1, 1 s-1, 10 s-1, dan 100 s-1. Dalam pengujian, data beban terhadap waktu direkam menggunakan load cell, sedangkan data perpindahan terhadap waktu diperoleh menggunakan ekstensometer untuk uji kuasi-statik dan menggunakan kamera kecepatan tinggi diikuti dengan perhitungan regangan berdasarkan metode Korelasi Citra Digital (KCD) untuk kondisi dinamik. Hasil pengukuran menunjukan bahwa baja St37 dan CR420LA termasuk ke dalam jenis material yang sensitif terhadap laju regangan, dimana tegangan luluh material meningkat dengan naiknya laju regangan pada material.
Numerical Study of Experiment Setup for Aluminum Foam Sandwich Construction Subjected to Blast Load Pratomo, Arief Nur; Santosa, Sigit Puji; Gunawan, Leonardo; Putra, Ichsan Setya
Mesin Vol 27, No 1 (2018)
Publisher : Mesin

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (1013.764 KB)

Abstract

In the designing an armored fighting vehicle (AFV), blastworthy construction to protect military personnel from landmines explosion is urgently needed. This is due to a large number of fatalities of army personnel in the state conflict zones. To achieve this blastworthy construction, the design of AFV floor structures needs to be able to sustain structural intrusion with lower dynamic acceleration against blast load. The blastworthy structures can be achieved through absorbing the blast impact load by using an aluminum foam sandwich (AFS) construction. During the design iteration process, a good correlation between numerical simulation and blast impact experiment is required. In this study, an experimental setup to assess the AFS construction for blast load performance evaluation was introduced. This study is started with an evaluation of jigs and fixtures structural strength, load cell structure requirement, and data acquisition to record maximum displacement, maximum acceleration, and reaction force in the load cells. From the evaluation, it was found that the jig and fixture structural configuration requires high load retention at the bolt joint location to avoid high stress concentration. For the load cell structure, it is recommended to place the load cell position in the pure axial stress direction so that there is no plastic deformation interference with the instrumentation. The data acquisitions will record the acceleration and reaction force of the AFS construction. The simulation results are also used to design the load cell and to select the accelerometer capability range. This study is expected to provide a robust experimental data during blast impact load testing of blastworthy AFS floor structure. 
Design and Fabrication of Ball Punch Deformation Test of Metallic Sheet Material Asti Rosalia, Citra; Wicaksono, Satrio; Dirgantara, Tatacipta; Basuki, Arif; Setya Putra, Ichsan
Mesin Vol 27, No 1 (2018)
Publisher : Mesin

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (815.283 KB)

Abstract

Predicting the behavior of sheet metal in forming process is very important to avoid material failure. The strain limit of sheet metals before tearing occurs is attainable in Forming Limit Diagram (FLD), which can be obtained experimentally or theoretically. Experimentally, FLD of a sheet metal can be achieved by performing ball punch deformation test. Unfortunately, commercially available ball punch deformation test apparatus is still very expensive. In this paper, the design, fabrication and testing process of more affordable ball punch deformation test apparatus is be presented. The ball punch apparatus has indenter?s diameter of 22.4 mm, which capable to tear 0.2-2.0 mm thick specimen blanks with maximum capacity of 200 kN. The test results are then compared with other commercially available ball punch deformation test apparatus results in the literature, and show very good agreement.
Karakterisasi Sifat Mekanik Mild Steel St37 dan High Strength Steel CR420LA pada Laju Regangan Menengah Leonardo Gunawan; Agustinus Dimas; Annisa Jusuf; Tatacipta Dirgantara; Ichsan Setya Putra
Mesin Vol. 25 No. 2 (2016)
Publisher : Mesin

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

Abstract

Untuk mendapatkan prediksi respon yang cukup akurat dalam analisis tabrakan kendaraan darat, dimana terjadi pembebanan dan deformasi struktur dalam waktu yang cepat, diperlukan data sifat mekanik material pada berbagai laju regangan. Makalah ini menyajikan pengukuran sifat mekanik Mild Steel St37 dan High Strength Steel CR420LA pada kondisi kuasi-statik dengan laju regangan 0.001 s-1 dan pada kondisi dinamik dengan laju regangan 0.1 s-1, 1 s-1, 10 s-1, dan 100 s-1. Dalam pengujian, data beban terhadap waktu direkam menggunakan load cell, sedangkan data perpindahan terhadap waktu diperoleh menggunakan ekstensometer untuk uji kuasi-statik dan menggunakan kamera kecepatan tinggi diikuti dengan perhitungan regangan berdasarkan metode Korelasi Citra Digital (KCD) untuk kondisi dinamik. Hasil pengukuran menunjukan bahwa baja St37 dan CR420LA termasuk ke dalam jenis material yang sensitif terhadap laju regangan, dimana tegangan luluh material meningkat dengan naiknya laju regangan pada material.
Numerical Study of Experiment Setup for Aluminum Foam Sandwich Construction Subjected to Blast Load Arief Nur Pratomo; Sigit Puji Santosa; Leonardo Gunawan; Ichsan Setya Putra
Mesin Vol. 27 No. 1 (2018)
Publisher : Mesin

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

Abstract

In the designing an armored fighting vehicle (AFV), blastworthy construction to protect military personnel from landmines explosion is urgently needed. This is due to a large number of fatalities of army personnel in the state conflict zones. To achieve this blastworthy construction, the design of AFV floor structures needs to be able to sustain structural intrusion with lower dynamic acceleration against blast load. The blastworthy structures can be achieved through absorbing the blast impact load by using an aluminum foam sandwich (AFS) construction. During the design iteration process, a good correlation between numerical simulation and blast impact experiment is required. In this study, an experimental setup to assess the AFS construction for blast load performance evaluation was introduced. This study is started with an evaluation of jigs and fixtures structural strength, load cell structure requirement, and data acquisition to record maximum displacement, maximum acceleration, and reaction force in the load cells. From the evaluation, it was found that the jig and fixture structural configuration requires high load retention at the bolt joint location to avoid high stress concentration. For the load cell structure, it is recommended to place the load cell position in the pure axial stress direction so that there is no plastic deformation interference with the instrumentation. The data acquisitions will record the acceleration and reaction force of the AFS construction. The simulation results are also used to design the load cell and to select the accelerometer capability range. This study is expected to provide a robust experimental data during blast impact load testing of blastworthy AFS floor structure. 
Design and Fabrication of Ball Punch Deformation Test of Metallic Sheet Material Citra Asti Rosalia; Satrio Wicaksono; Tatacipta Dirgantara; Arif Basuki; Ichsan Setya Putra
Mesin Vol. 27 No. 1 (2018)
Publisher : Mesin

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

Abstract

Predicting the behavior of sheet metal in forming process is very important to avoid material failure. The strain limit of sheet metals before tearing occurs is attainable in Forming Limit Diagram (FLD), which can be obtained experimentally or theoretically. Experimentally, FLD of a sheet metal can be achieved by performing ball punch deformation test. Unfortunately, commercially available ball punch deformation test apparatus is still very expensive. In this paper, the design, fabrication and testing process of more affordable ball punch deformation test apparatus is be presented. The ball punch apparatus has indenter's diameter of 22.4 mm, which capable to tear 0.2-2.0 mm thick specimen blanks with maximum capacity of 200 kN. The test results are then compared with other commercially available ball punch deformation test apparatus results in the literature, and show very good agreement.
Analisis Perkiraan Umur Struktur Center Wing Box pada Pesawat Hercules C-130H Akibat Beban Lelah Ali Aziz; Annisa Jusuf; Bambang Rahardjo; Ichsan Setya Putra; Hery Setiawan; Achmad Sugiono
WARTA ARDHIA Vol 48, No 1 (2022)
Publisher : Badan Kebijakan Transportasi, Kementerian Perhubungan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.25104/wa.v48i1.442.43-52

Abstract

Failure of aircraft structural components has fatal consequences, namely the plane crash and will cause loss of life. There are many types of failures in aircraft structures, one of which is fatigue failure, which is often the leading cause of aircraft structural failures. Therefore, this study will determine the age of the center wing box (CWB) structure on the Hercules C-130H aircraft for the case of multiple-site damage crack propagation in the lower skin when experiencing fatigue loads. This research will be divided into four stages of analysis. The first stage is to determine the aerodynamic load received by the wing. Then followed by the second stage is to determine the stress distribution on the CWB structure using finite element analysis. Next, the third stage, namely making a stress spectrum based on the aircraft's flight history and analyzing crack propagation in the fourth stage. The analysis found that the maximum age of the CWB structure was 27,065 flight times or 50,070 flight hours. The age of the structure as a result of this analysis is of higher value than the statement by the aircraft manufacturing company, which is 40,000 flight hours.Kegagalan komponen struktur pesawat terbang memiliki konsekuensi yang sangat fatal, yakni kecelakaan pesawat tersebut dan akan menyebabkan hilangnya nyawa. Banyak jenis kegagalan pada struktur pesawat yang mempengaruhi keselamatan transportasi udara, salah satunya adalah kegagalan lelah (fatigue), yang seringkali merupakan penyebab utama terjadinya kegagalan struktur pesawat. Oleh karena itu, pada penelitian ini akan dilakukan penentuan umur dari struktur center wing box (CWB) pada pesawat Hercules C-130H untuk kasus perambatan retak jenis multiple-site damage di skin bawah ketika mengalami beban lelah. Penelitian ini akan terbagi menjadi empat tahap analisis. Tahap pertama adalah menentukan beban aerodinamik yang diterima sayap, kemudian tahap kedua menentukan distribusi tegangan pada struktur CWB menggunakan analisis elemen hingga. Dilanjutkan dengan tahap ketiga yaitu membuat stress spectrum berdasarkan riwayat penerbangan pesawat, dan yang terakhir pada tahap keempat adalah melakukan analisis perambatan retak. Setelah melakukan analisis didapatkan bahwa umur maksimal struktur CWB adalah 27.065 kali terbang atau 50.070 jam terbang. Umur struktur hasil analisis ini bernilai lebih besar jika dibandingkan dengan pernyataan perusahaan manufaktur pesawat terbang tersebut yaitu sebesar 40.000 jam terbang.
Analisis Perkiraan Umur Struktur Center Wing Box pada Pesawat Hercules C-130H Akibat Beban Lelah Aziz, Ali; Jusuf, Annisa; Rahardjo, Bambang; Putra, Ichsan Setya; Setiawan, Hery; Sugiono, Achmad
WARTA ARDHIA Vol. 48 No. 1 (2022)
Publisher : Sekretariat Badan Kebijakan Transportasi, Kementerian Perhubungan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.25104/wa.v48i1.442.43-52

Abstract

Failure of aircraft structural components has fatal consequences, namely the plane crash and will cause loss of life. There are many types of failures in aircraft structures, one of which is fatigue failure, which is often the leading cause of aircraft structural failures. Therefore, this study will determine the age of the center wing box (CWB) structure on the Hercules C-130H aircraft for the case of multiple-site damage crack propagation in the lower skin when experiencing fatigue loads. This research will be divided into four stages of analysis. The first stage is to determine the aerodynamic load received by the wing. Then followed by the second stage is to determine the stress distribution on the CWB structure using finite element analysis. Next, the third stage, namely making a stress spectrum based on the aircraft's flight history and analyzing crack propagation in the fourth stage. The analysis found that the maximum age of the CWB structure was 27,065 flight times or 50,070 flight hours. The age of the structure as a result of this analysis is of higher value than the statement by the aircraft manufacturing company, which is 40,000 flight hours.Kegagalan komponen struktur pesawat terbang memiliki konsekuensi yang sangat fatal, yakni kecelakaan pesawat tersebut dan akan menyebabkan hilangnya nyawa. Banyak jenis kegagalan pada struktur pesawat yang mempengaruhi keselamatan transportasi udara, salah satunya adalah kegagalan lelah (fatigue), yang seringkali merupakan penyebab utama terjadinya kegagalan struktur pesawat. Oleh karena itu, pada penelitian ini akan dilakukan penentuan umur dari struktur center wing box (CWB) pada pesawat Hercules C-130H untuk kasus perambatan retak jenis multiple-site damage di skin bawah ketika mengalami beban lelah. Penelitian ini akan terbagi menjadi empat tahap analisis. Tahap pertama adalah menentukan beban aerodinamik yang diterima sayap, kemudian tahap kedua menentukan distribusi tegangan pada struktur CWB menggunakan analisis elemen hingga. Dilanjutkan dengan tahap ketiga yaitu membuat stress spectrum berdasarkan riwayat penerbangan pesawat, dan yang terakhir pada tahap keempat adalah melakukan analisis perambatan retak. Setelah melakukan analisis didapatkan bahwa umur maksimal struktur CWB adalah 27.065 kali terbang atau 50.070 jam terbang. Umur struktur hasil analisis ini bernilai lebih besar jika dibandingkan dengan pernyataan perusahaan manufaktur pesawat terbang tersebut yaitu sebesar 40.000 jam terbang.
Co-Authors AA Sudharmawan, AA Achmad Sugiono Agustinus Dimas Ali Aziz Annisa Jusuf Annisa Jusuf Annisa Jusuf, Annisa Arief Nur Pratomo Aziz, Ali Bambang Rahardjo Bambang Rahardjo Cakranegara, Pandu Adi Citra Asti Rosalia Dimas, Agustinus Gunawan, Leonardo Hery Setiawan Hery Setiawan, Hery Leonardo Gunawan Leonardo Gunawan Leonardo Gunawan, Leonardo Pratomo, Arief Nur Santosa, Sigit Puji Satrio Wicaksono Satrio Wicaksono Sugiono, Achmad Tatacipta Dirgantara, Tatacipta