ANALISIS DAN PERANCANGAN STRUKTUR MULTI SPAR KONVENSIONAL KOMPOSIT PADA SAYAP PESAWAT TEMPUR DENGAN METODE ELEMEN HINGGA
This undergraduate thesis present a topic about “Design and Analysis of Multi Spar Conventional Composite Wing using Finite Element Method”. With the usage of composite material trend going up in the recent days in the field of aircraft, the computational analysis is needed in term to know the capab...
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| Format: | Final Project |
| Language: | Indonesia |
| Online Access: | https://digilib.itb.ac.id/gdl/view/34077 |
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| Institution: | Institut Teknologi Bandung |
| Language: | Indonesia |
| Summary: | This undergraduate thesis present a topic about “Design and Analysis of Multi Spar Conventional Composite Wing using Finite Element Method”. With the usage of composite material trend going up in the recent days in the field of aircraft, the computational analysis is needed in term to know the capability of fully composite structure to replace metalic structure on aircraft wing, especially fighter aircraft wing. Material that is used in this thesis is G40-800 carbon fibre with 5276-1 resin epoxy, then the fibers orientation and stacking sequence are fixed in the [0/45/-45/90]s, so that it will be a quasi – isotropic laminate. The modeling of wing structure is detailed using Catia software with some simplification, some of them are the joint section between wing and fuselage, also the connection between ribs, spar, and skin. In regard to sizing of structure, distributed load will be applied in which the load acquired from another division’s experiment. The results of parametric design study with the Patran and Nastran software will be validated by using maximum strain failure criterion so that the results will determine the size of each component. The outcome compared to the anisogrid design of the same wing resulting in a maximum difference of 30% less in total mass of structure. |
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