Garuda - Garba Rujukan Digital

Desain Iterasi Dudukan Pelat Pengukur Gaya Pada RIG Alat Uji Jatuh Bebas Menggunakan Optimasi Topology Maulana, Ilham; A. Sitompul, Sahril; Rabeta, Bismil; Fitriansyah, Rizky; Nurrohmad, Abian
Jurnal Teknologi Kedirgantaraan Vol 7 No 2 (2022): Jurnal Teknologi Kedirgantaraan
Publisher : FTK UNSURYA

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35894/jtk.v7i2.56

Abstract -. This research was conducted based on data obtained during testing at LAPAN (Lembaga Antariksa dan Penerbangan Nasional), where there was a case that became a concern. The test is about the free fall test, which results in a deflection that is considered too large. From these results it was decided to investigate further. This free fall test uses impact testing where a material is measured for its shock load resistance. Impact testing simulates the operating conditions of a material where the loading that occurs is not only in static conditions but also occurs in dynamic conditions. In the free fall test, a test was carried out to measure and see the resistance of the landing gear and crash box in receiving dynamic loads, when the aircraft landed. The main purpose of simulating this tool is for research and development of the free fall test equipment itself, as well as the design of the landing gear of the LSU (Lapan Survaillance UAV) drone in the future. The impact platform on the free fall test equipment plays an important role in impact testing, where the deformation of the plate holder will be converted by the load cell, into a signal received by the acquisition system. So it is designed to fit the existing needs. In this test equipment, the test object is given a load (50 kg and 200 kg), height (4.72 m and 1,204 m), so that it reaches a velocity (9,623 m/s and 4,861 m/s) with impactor crash box geometry and main landing gear as well as plate holder design based tools in the field. Based from testing, impact, and analysis using the finite element method in this study, it was found that the deflection value was 1.771 mm which reduced 94.61% for the crash box case and the deflection value was 2.696 mm with a reduction value of 87.85 % for the main landing gear case from the existing initial design. Keywords: Free fall test equipment, impact platform, landing gear, plate mount, main landing gear, crash box, finite element method, LSU.

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.

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

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.

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.

A Study on Lug Structure at Fuselage - Wing Joint of an Unmanned Aerial Vehicle Using Finite Element Method Cahya, Fadli; Pramana, Nurhadi; Chairunnisa; Adhynugraha, Muhammad Ilham; Aribowo, Agus; Nurrohmad, Abian
Indonesian Journal of Aerospace Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2023.272

Research on structural analysis of an unmanned aerial vehicle (UAV) is carried out. The primary material used in most structures is carbon composite. Having a high aspect ratio wing, the lugs connecting the wing and fuselage are likely to experience maximum forces during flight tests. In predicting the occurrence of deformation and stress, the finite element method is used by applying max./min. strain criteria to evaluate the structural integrity of composite wings due to the load applied on aluminum-based lugs. The evaluation shows that the current wing configuration has good structural integrity. An optimization approach is also carried out to obtain more optimum results.

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

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.

NUMERICAL INVESTIGATION ON THE FUSELAGE AIRFRAME OF LSU 05 NG AIRCRAFT Hafid, M.; Nurrohmad, Abian; Ramadhan, Redha Akbar
Indonesian Journal of Aerospace Vol. 18 No. 2 Desember (2020): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2020.v18.a3327

In this paper, numerical investigation on the fuselage structure of LSU 05 NG was carried out. This fuselage is designed to carry the payload up to 30 kg. Statical numerical analysis using finite element method was done using Simulia Abaqus. The fuselage structure that has been design consists of frame, longeron, and skin that can also be semi-monocoque structure. This airframe use combination of balsa and GFRP type of composite as the material. There are three load case: take-off condition, cruise condition, and landing condition. Tsai-hill failure criteria is used to investigate the strength of the composite structure due to the load that applied. Maximum stress from this calculation is 48 Mpa at the ground condition (take-off and landing) while the cruise stress analysis is 16 Mpa. The maximum tsai-hill criterion is 0,83. With such simulation results it can be said that the fuselage structure is still safe when operated and can also be optimized for several components so that the weight of the aircraft can be reduced.

Title

Found 7 Documents
Search

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Title Search

Found 7 Documents Search

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Abstract

Title

Found 7 Documents
Search