| Autor: |
Wandono, Fajar Ari, Nuranto, Awang Rahmadi, Nurrohmad, Abian, Hafid, M., Bintoro, Atik |
| Předmět: |
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| Zdroj: |
AIP Conference Proceedings; 2023, Vol. 2941 Issue 1, p1-10, 10p |
| Abstrakt: |
In this paper, a finite element model for the amphibious aircraft spreader bar using a composite structure will be presented. The initial spreader bar cross-section is an ellipse with an overall thickness of 3.8 mm and an additional thickness on the minor axis. The spreader bar using a composite structure is proposed to replace the initial spreader bar using aluminium. Composite Toray-TCA T700S-12K-50C#2510 Plain Weave Fabric will be used to replace aluminium 6061-T6. The composite spreader bar cross-section is similar to the initial design by applying ply drop-off to vary the thickness of its cross-section. There are 44 plies for the thick zone and 18 for the thin zone. For stacking sequences, all zones use symmetric layers. Model verification has been performed by comparing the spreader bar cross-section from the computer-aided design and finite element model. The spreader bar is modeled with a 2D shell element to obtain the failure index and margin of safety using Tsai-Wu failure criteria. The side load while landing will be used in this paper because it is a critical load during the flight. The side load generates tension, compression, shear, roll moment, yaw moment, and torsion in the spreader bar structure. The spreader bar structure using composite material is 42.8% lighter than using aluminium. The margin of safety of spreader bar structure using aluminium and composite material are -0.37 and 1.54, respectively. This results mean that composite structure can be used as an amphibious aircraft spreader bar, which is safer than aluminium in terms of strength, but not better in terms of stiffness due to its lower elastic modulus than aluminium. [ABSTRACT FROM AUTHOR] |
| Databáze: |
Complementary Index |
| Externí odkaz: |
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