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Optimization of Double Hole Composite Plate on the Floater Compartment of Amphibious Aircraft Using Taguchi Method Nurrohmad, Abian; Antares, Quincy; Nuranto, Awang Rahmadi; Nugroho, Afid
WARTA ARDHIA Vol 49, No 2 (2023)
Publisher : Badan Kebijakan Transportasi, Kementerian Perhubungan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.25104/wa.v49i2.520.87-95

A floater or pontoon is one of the most important components of amphibious aircraft to assist the take-off and landing operation. The inner structure of the floater consists of compartments to carry some payload and to reinforce the structural strength due to water and aerodynamic load that occurred during the aircraft operation. The composite material is chosen instead of metal to reduce the weight of the floater. One of the problems on the composite panel is the existence of some holes due to joint with another part or also to minimize its weight. In this study, the optimization of the composite plate with the existence of a double hole is done using the Taguchi Method. The objective of this optimization is to minimize the stress that happens due to the tensile load. The Finite Element Method is used to calculate the maximum stress and stress distribution on the plate. Tsai-Hill failure criterion is used to make sure that the optimum design does not fail. This optimization considers open hole configuration, the ratio between diameter, and hole distance, as well as the fiber orientation as the control factors. The Taguchi L9 Orthogonal Array is used to make 9 design variations from 3 control factors and 3 levels. This process also considers the thickness of the lamina and material strength as noise factors. The optimization process results in the optimum composite design as follows: 1st double hole configuration (in line with the load direction), the ratio between diameter and hole distance is 0.5, and the fiber direction is [0/90/45/-45]s. The maximum in-plane stress of the optimum design is 39.56 MPa with the Tsai-Hill value is 0.23, so the design does not fail. This optimum configuration of the composite plate can be used to make design considerations for an amphibious aircraft floater compartment.

DETEKSI CACAT PADA CARBON FIBER REINFORCED POLYMER BERDASARKAN KOEFISIEN KORELASI PEARSON DARI SINYAL ECHO ULTRASONIK Yusuf Giri Wijaya; Suprijanto, Suprijanto; Nugroho, Afid; Hijazi, Rhakamerta; Adhika, Damar Rastri
Scientific Journal of Mechanical Engineering Kinematika Vol 9 No 2 (2024): SJME Kinematika Desember 2024 (ongoing -Full)
Publisher : Mechanical Engineering Department, Faculty of Engineering, Universitas Lambung Mangkurat

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.20527/sjmekinematika.v9i2.322

Carbon fiber reinforced polymer (CFRP) adalah material komposit yang sering digunakan dalam industri penerbangan, otomotif, dan kelautan karena kekuatannya yang tinggi dan beratnya yang ringan. Namun, keandalan CFRP dapat terganggu oleh cacat internal yang terjadi selama proses manufaktur atau penggunaan. Penelitian ini bertujuan untuk mendeteksi adanya cacat pada CFRP berdasarkan koefisien korelasi Pearson dari sinyal echo ultrasonik. Metode ini menggunakan gelombang ultrasonik untuk mengidentifikasi cacat berdasarkan perubahan pola sinyal. Sinyal referensi diperoleh dengan merata-ratakan sinyal dari beberapa lokasi bebas cacat. Perubahan pola sinyal terhadap sinyal referensi dikuantifikasi menggunakan koefisien korelasi Pearson untuk mengklasifikasikan daerah bebas cacat dan yang memiliki cacat. Sampel uji berupa plat tipis CFRP dengan cacat buatan dari material teflon berbentuk lingkaran dengan jari-jari 15 mm yang diletakkan pada dua kedalaman berbeda. Hasil penelitian menunjukkan bahwa koefisien korelasi Pearson efektif membedakan antara area bebas cacat dan yang memiliki cacat. Area bebas cacat menunjukkan korelasi dalam rentang 0,97 sampai 1, sementara area dengan cacat menunjukkan korelasi rendah dalam rentang 0 sampai 0,36.

Optimization of Double Hole Composite Plate on the Floater Compartment of Amphibious Aircraft Using Taguchi Method Nurrohmad, Abian; Antares, Quincy; Nuranto, Awang Rahmadi; Nugroho, Afid
WARTA ARDHIA Vol. 49 No. 2 (2023)
Publisher : Sekretariat Badan Kebijakan Transportasi, Kementerian Perhubungan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.25104/wa.v49i2.520.87-95

A floater or pontoon is one of the most important components of amphibious aircraft to assist the take-off and landing operation. The inner structure of the floater consists of compartments to carry some payload and to reinforce the structural strength due to water and aerodynamic load that occurred during the aircraft operation. The composite material is chosen instead of metal to reduce the weight of the floater. One of the problems on the composite panel is the existence of some holes due to joint with another part or also to minimize its weight. In this study, the optimization of the composite plate with the existence of a double hole is done using the Taguchi Method. The objective of this optimization is to minimize the stress that happens due to the tensile load. The Finite Element Method is used to calculate the maximum stress and stress distribution on the plate. Tsai-Hill failure criterion is used to make sure that the optimum design does not fail. This optimization considers open hole configuration, the ratio between diameter, and hole distance, as well as the fiber orientation as the control factors. The Taguchi L9 Orthogonal Array is used to make 9 design variations from 3 control factors and 3 levels. This process also considers the thickness of the lamina and material strength as noise factors. The optimization process results in the optimum composite design as follows: 1st double hole configuration (in line with the load direction), the ratio between diameter and hole distance is 0.5, and the fiber direction is [0/90/45/-45]s. The maximum in-plane stress of the optimum design is 39.56 MPa with the Tsai-Hill value is 0.23, so the design does not fail. This optimum configuration of the composite plate can be used to make design considerations for an amphibious aircraft floater compartment.

Shear strength comparison of single lap and joggle lap adhesive joints in carbon fiber composites manufactured via vacuum-assisted resin infusion Pratama, Mikhael Gilang Pribadi Putra; Abdurohman, Kosim; Pratomo, Rezky Agung; Hidayat, Ryan; Ramadhan, Redha Akbar; Aritonang, Rian Suari; Nurtiasto, Taufiq Satrio; Ardiansyah, Riki; Nugroho, Afid; Nuranto, Awang Rahmadi; Wandono, Fajar Ari; Targani, Dudi; Ula, Nur Mufidatul
Jurnal Polimesin Vol 22, No 5 (2024): October
Publisher : Politeknik Negeri Lhokseumawe

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30811/jpl.v22i5.5437

The extensive utilization of composite materials has spurred the advancement of diverse joining techniques suitable for components constructed from such materials. This study focuses on the examination of two specific types of joints: single lap and joggle lap joints. The specimens utilized were composed of unidirectional carbon fiber composite combined with vinyl ester resin, manufactured via the vacuum-assisted resin infusion method. Vinyl ester adhesives were employed in the bonding process, with the joint surfaces undergoing sanding treatment prior to testing. Mechanical testing was conducted on the specimens according to ASTM D5868 standard, employing a constant crosshead speed until failure occurred. The test results reveal that the shear strength of single lap joints surpasses that of joggle lap joints. Within the single lap joint configuration, a mixed failure mode comprising both adhesive and cohesive failure is observed. Conversely, in joggle lap joints, substrate delamination is prevalent, suggesting the predominance of peel stress during loading.

Properties Comparison of Open Hole and Non-Hole Carbon UD-Lycal Composite with Vacuum Bagging Manufacturing Method Isna, Lathifa Rusita; Nugroho, Afid; P, Rezky Agung; R, Redha Akbar
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.a3494

Carbon fiber reinforce polymer is one of some composite materials that has the high strength with light weight material. To apply this composite to the amphibious airplane structure, it should through the experimental tensile test to know the tensile strength and modulus of elasticity of the composite. In this experiment, we use Carbon UD fiber and Lycal resin as the composite material that manufactured with Vacuum Bagging Method. Specimens and testing process refer to ASTM D3039 for non-hole specimen, and ASTM D5766 for open hole specimen of tensile test standard for composite matrix polymers. The result of the experimental test shows that the tensile modulus of elasticity for non-hole composite is 34.92 ± 0.13 GPa, with the Ultimate Tensile Strength of this composite is 1081± 0.03 MPa, and the modulus of elasticity for open hole composite is 41.87± 0.02 GPa, with the Ultimate Tensile Strength of this composite is 899.04± 0.02 MPa. The simulation yields nearly same stress-strain graph with the result of experiment. The result shows that, the open hole composite has the ultimate tensile strength lower than non-hole composite, it’s due to the open hole composite has a trigger failure that may decreasing the tensile strength value.

Investigation of the Mechanical Properties of Vinyl ester Carbon Composites Through Immersion in Seawater and Freshwater Using the VARI (Vacuum Assisted Resin Infusion) Method Muzayadah, Nurul Lailatul; Nurtiasto, Taufiq Satrio; Abdurrahman, Kosim; Nugroho, Afid; Wandono, Fajar Ari; Ula, Nur Mufidatul; P, Rezky Agung; Ramadhan , Redha Akbar; Hendrawan, Rozi
Indonesian Journal of Aerospace Vol. 20 No. 1 (2022): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2022.v20.a3579

The carbon-vinyl ester composites have made for the development of the base material for Amphibious floats. The properties of this composite have strength, lighter weight and resistant to corrosion. This study was aimed to report the effect of two different water immersion treatment namely seawater and freshwater on the mechanical properties of composite made from fiber twill and vinyl ester resin using the vacuum assisted resin infusion (VARI) method. Experiments were carried out on tensile, compressive, and shear tests. The specimens were immersed in seawater and freshwater for ten days. The results have shown that Ultimate Tensile Strength of the composite with seawater immersion declined 1.27% compare with the composite without immersion treatment, while the composite in freshwater got greater 3.56%. The decrement of compressive and shear strength was more significant than tensile strength. The compressive strength declined 17.89% and 16.7% for freshwater and seawater treatment, respectively.Â The shear strength decreased 27.87 % and 25.77% for freshwater and seawater treatment, respectively

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