Finite element method on topology optimization applied to laminate composite of fuselage structure
This research applies a numerical study of topology optimization of laminate composite structures by using a finite element method (FEM). In this methodology, the plies orientation is excluded from the optimization. The geometry-based optimization from frames of a MALE UAV fuselage structure is pres...
| Main Authors: | , , , , , , , , , , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
De Gruyter
2023-04-01
|
| Series: | Curved and Layered Structures |
| Subjects: | |
| Online Access: | https://doi.org/10.1515/cls-2022-0191 |
| _version_ | 1797832447405064192 |
|---|---|
| author | Aribowo Agus Adhynugraha Muhammad Ilham Megawanto Fadli Cahya Hidayat Arif Muttaqie Teguh Wandono Fajar Ari Nurrohmad Abian Chairunnisa Saraswati Sherly Octavia Wiranto Ilham Bagus Al Fikri Iqbal Reza Saputra Muhammad Dito |
| author_facet | Aribowo Agus Adhynugraha Muhammad Ilham Megawanto Fadli Cahya Hidayat Arif Muttaqie Teguh Wandono Fajar Ari Nurrohmad Abian Chairunnisa Saraswati Sherly Octavia Wiranto Ilham Bagus Al Fikri Iqbal Reza Saputra Muhammad Dito |
| author_sort | Aribowo Agus |
| collection | DOAJ |
| description | This research applies a numerical study of topology optimization of laminate composite structures by using a finite element method (FEM). In this methodology, the plies orientation is excluded from the optimization. The geometry-based optimization from frames of a MALE UAV fuselage structure is presented. The minimum strain energy with an optimization constraint of 20% of weight reduction is used in the objective function. Before the primary analysis, benchmark studies of topology optimization without considering orientations from previously published literature are performed. The convergence studies were taken to acquire the appropriate mesh size in the FEM technique, which utilized a four-noded shell element. The finite element analysis and optimization results showed that the structural design of the newly framed composite fuselage MALE UAV meets the structural strength requirements specified in the airworthiness standard STANAG 4671. |
| first_indexed | 2024-04-09T14:07:58Z |
| format | Article |
| id | doaj.art-bbe3798e2f8e4089ae5fecd1c95cc3d8 |
| institution | Directory Open Access Journal |
| issn | 2353-7396 |
| language | English |
| last_indexed | 2024-04-09T14:07:58Z |
| publishDate | 2023-04-01 |
| publisher | De Gruyter |
| record_format | Article |
| series | Curved and Layered Structures |
| spelling | doaj.art-bbe3798e2f8e4089ae5fecd1c95cc3d82023-05-06T15:58:55ZengDe GruyterCurved and Layered Structures2353-73962023-04-01101p. 11610.1515/cls-2022-0191Finite element method on topology optimization applied to laminate composite of fuselage structureAribowo Agus0Adhynugraha Muhammad Ilham1Megawanto Fadli Cahya2Hidayat Arif3Muttaqie Teguh4Wandono Fajar Ari5Nurrohmad Abian6Chairunnisa7Saraswati Sherly Octavia8Wiranto Ilham Bagus9Al Fikri Iqbal Reza10Saputra Muhammad Dito11Research Center for Aeronautics Technology, National Research and Innovation Agency (BRIN), Bogor 16350, IndonesiaResearch Center for Aeronautics Technology, National Research and Innovation Agency (BRIN), Bogor 16350, IndonesiaDirectorate of Strengthening and Partnership of Research and Innovation Infrastructure, BRIN, Bogor 16912, IndonesiaResearch Center for Advanced Material, BRIN, Banten 15314, IndonesiaResearch Center for Hydrodynamics Technology, BRIN, Surabaya 60117, IndonesiaResearch Center for Aeronautics Technology, National Research and Innovation Agency (BRIN), Bogor 16350, IndonesiaResearch Center for Aeronautics Technology, National Research and Innovation Agency (BRIN), Bogor 16350, IndonesiaResearch Center for Energy Conversion and Conservation, BRIN, Banten 15314, IndonesiaResearch Center for Process and Manufacturing Industry Technology, BRIN, Banten 15314, IndonesiaResearch Center for Process and Manufacturing Industry Technology, BRIN, Banten 15314, IndonesiaResearch Center for Process and Manufacturing Industry Technology, BRIN, Banten 15314, IndonesiaAerospace Engineering, KTH Royal Institute of Technology, Brinellvägen 8, Stockholm 11428, SwedenThis research applies a numerical study of topology optimization of laminate composite structures by using a finite element method (FEM). In this methodology, the plies orientation is excluded from the optimization. The geometry-based optimization from frames of a MALE UAV fuselage structure is presented. The minimum strain energy with an optimization constraint of 20% of weight reduction is used in the objective function. Before the primary analysis, benchmark studies of topology optimization without considering orientations from previously published literature are performed. The convergence studies were taken to acquire the appropriate mesh size in the FEM technique, which utilized a four-noded shell element. The finite element analysis and optimization results showed that the structural design of the newly framed composite fuselage MALE UAV meets the structural strength requirements specified in the airworthiness standard STANAG 4671.https://doi.org/10.1515/cls-2022-0191topology optimizationfuselage structuremale uavfinite element method |
| spellingShingle | Aribowo Agus Adhynugraha Muhammad Ilham Megawanto Fadli Cahya Hidayat Arif Muttaqie Teguh Wandono Fajar Ari Nurrohmad Abian Chairunnisa Saraswati Sherly Octavia Wiranto Ilham Bagus Al Fikri Iqbal Reza Saputra Muhammad Dito Finite element method on topology optimization applied to laminate composite of fuselage structure Curved and Layered Structures topology optimization fuselage structure male uav finite element method |
| title | Finite element method on topology optimization applied to laminate composite of fuselage structure |
| title_full | Finite element method on topology optimization applied to laminate composite of fuselage structure |
| title_fullStr | Finite element method on topology optimization applied to laminate composite of fuselage structure |
| title_full_unstemmed | Finite element method on topology optimization applied to laminate composite of fuselage structure |
| title_short | Finite element method on topology optimization applied to laminate composite of fuselage structure |
| title_sort | finite element method on topology optimization applied to laminate composite of fuselage structure |
| topic | topology optimization fuselage structure male uav finite element method |
| url | https://doi.org/10.1515/cls-2022-0191 |
| work_keys_str_mv | AT aribowoagus finiteelementmethodontopologyoptimizationappliedtolaminatecompositeoffuselagestructure AT adhynugrahamuhammadilham finiteelementmethodontopologyoptimizationappliedtolaminatecompositeoffuselagestructure AT megawantofadlicahya finiteelementmethodontopologyoptimizationappliedtolaminatecompositeoffuselagestructure AT hidayatarif finiteelementmethodontopologyoptimizationappliedtolaminatecompositeoffuselagestructure AT muttaqieteguh finiteelementmethodontopologyoptimizationappliedtolaminatecompositeoffuselagestructure AT wandonofajarari finiteelementmethodontopologyoptimizationappliedtolaminatecompositeoffuselagestructure AT nurrohmadabian finiteelementmethodontopologyoptimizationappliedtolaminatecompositeoffuselagestructure AT chairunnisa finiteelementmethodontopologyoptimizationappliedtolaminatecompositeoffuselagestructure AT saraswatisherlyoctavia finiteelementmethodontopologyoptimizationappliedtolaminatecompositeoffuselagestructure AT wirantoilhambagus finiteelementmethodontopologyoptimizationappliedtolaminatecompositeoffuselagestructure AT alfikriiqbalreza finiteelementmethodontopologyoptimizationappliedtolaminatecompositeoffuselagestructure AT saputramuhammaddito finiteelementmethodontopologyoptimizationappliedtolaminatecompositeoffuselagestructure |