Development of Anisogrid Lattice Composite Structures for Fighter Wing Applications
This paper presents research on the use of anisogrid lattice structures in fighter wing applications. While the anisogrid lattice structure has been widely used in spacecraft structures, its implementation in main aircraft structures is still limited. The study is aimed at investigating the feasibil...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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Wiley
2024-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2024/6667586 |
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| _version_ | 1832553095088832512 |
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| author | Muhammad Kusni Bambang Kismono Hadi Leonardo Gunawan Hendri Syamsudin |
| author_facet | Muhammad Kusni Bambang Kismono Hadi Leonardo Gunawan Hendri Syamsudin |
| author_sort | Muhammad Kusni |
| collection | DOAJ |
| description | This paper presents research on the use of anisogrid lattice structures in fighter wing applications. While the anisogrid lattice structure has been widely used in spacecraft structures, its implementation in main aircraft structures is still limited. The study is aimed at investigating the feasibility of utilizing an anisogrid lattice structure in fighter wing design. The analysis and optimization focus on determining the optimal weight of the composite wing structure, considering static, buckling, and flutter failure constraints. Various lift distributions, including triangular, Schrenk, and constant, are applied to evaluate the structure’s response to static failure caused by aerodynamic loads. The anisogrid structure design incorporates inclined lattice elements between ribs and spars, with spar arrangement in the wing box featuring an anisogrid configuration. The anisogrid lattice structure is expected to produce higher bending and torsional stiffness compared to conventional orthogonal structures, producing better flutter and buckling characteristics. The optimized wing structure successfully meets static, buckling, and flutter load requirements at speeds below 500 m/s. The study showcases triangular, Schrenk, and constant load distributions resulting in half-wing masses of 504, 571, and 707 kg, respectively. The results show that flutter and buckling loads are no longer the critical loads in wing structural design but static load. |
| format | Article |
| id | doaj-art-f674430f062a43e4b2659608479a85a2 |
| institution | Kabale University |
| issn | 1687-5974 |
| language | English |
| publishDate | 2024-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-f674430f062a43e4b2659608479a85a22025-02-03T05:56:55ZengWileyInternational Journal of Aerospace Engineering1687-59742024-01-01202410.1155/2024/6667586Development of Anisogrid Lattice Composite Structures for Fighter Wing ApplicationsMuhammad Kusni0Bambang Kismono Hadi1Leonardo Gunawan2Hendri Syamsudin3Mechanics of Solid and Lightweight Structures Research GroupMechanics of Solid and Lightweight Structures Research GroupMechanics of Solid and Lightweight Structures Research GroupMechanics of Solid and Lightweight Structures Research GroupThis paper presents research on the use of anisogrid lattice structures in fighter wing applications. While the anisogrid lattice structure has been widely used in spacecraft structures, its implementation in main aircraft structures is still limited. The study is aimed at investigating the feasibility of utilizing an anisogrid lattice structure in fighter wing design. The analysis and optimization focus on determining the optimal weight of the composite wing structure, considering static, buckling, and flutter failure constraints. Various lift distributions, including triangular, Schrenk, and constant, are applied to evaluate the structure’s response to static failure caused by aerodynamic loads. The anisogrid structure design incorporates inclined lattice elements between ribs and spars, with spar arrangement in the wing box featuring an anisogrid configuration. The anisogrid lattice structure is expected to produce higher bending and torsional stiffness compared to conventional orthogonal structures, producing better flutter and buckling characteristics. The optimized wing structure successfully meets static, buckling, and flutter load requirements at speeds below 500 m/s. The study showcases triangular, Schrenk, and constant load distributions resulting in half-wing masses of 504, 571, and 707 kg, respectively. The results show that flutter and buckling loads are no longer the critical loads in wing structural design but static load.http://dx.doi.org/10.1155/2024/6667586 |
| spellingShingle | Muhammad Kusni Bambang Kismono Hadi Leonardo Gunawan Hendri Syamsudin Development of Anisogrid Lattice Composite Structures for Fighter Wing Applications International Journal of Aerospace Engineering |
| title | Development of Anisogrid Lattice Composite Structures for Fighter Wing Applications |
| title_full | Development of Anisogrid Lattice Composite Structures for Fighter Wing Applications |
| title_fullStr | Development of Anisogrid Lattice Composite Structures for Fighter Wing Applications |
| title_full_unstemmed | Development of Anisogrid Lattice Composite Structures for Fighter Wing Applications |
| title_short | Development of Anisogrid Lattice Composite Structures for Fighter Wing Applications |
| title_sort | development of anisogrid lattice composite structures for fighter wing applications |
| url | http://dx.doi.org/10.1155/2024/6667586 |
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