International Research Journal of Innovations in Engineering and Technology - IRJIET International Open Access, Monthly, Peer Reviewed, Reputed Journal ISSN (online): 2581-3048

Impact Factor (2025): 6.9

DOI Prefix: 10.47001/IRJIET

Finite Element Method Analysis on VTP to Determine Initial Crack Location at Nxxx Aircraft using MPC to Distribute Loads

Abstract

In the field of aviation, every aircraft component plays a crucial role in ensuring safety, stability, and optimal performance during flight. One of these components, which plays a critical role, is the Vertical Tail Plane (VTP) or vertical stabilizer. The VTP not only provides vertical stability but also functions as a vital control tool for pilots to maintain the flight path and respond to external changes. Inspection and thickness improvements, along with the application of Multi-Point Constraint (MPC) to the VTP structure, are essential steps in the manufacturing process to prevent production errors that could cause damage to the aircraft. This study aims to determine the location of the initial crack in the VTP structure, which will then be used to calculate the crack propagation rate. If the crack propagation rate is fast, the geometry of the structure needs to be modified. The method used in this analysis is the Finite Element Method (FEM), implemented using MSC PATRAN software. By using FEM, thickness improvements and MPC application can be performed quickly and efficiently, ensuring that the analysis produces a safe and high-quality VTP component.

Country : Indonesia

1 Shofwan Bahar2 Eflita Yohana3 Elroy Efodiarlo Umbu Lolo4 Susilo Adi Widyanto

  1. Department of Mechanical Engineering, Diponegoro University, Semarang, Indonesia
  2. Department of Mechanical Engineering, Diponegoro University, Semarang, Indonesia
  3. Department of Mechanical Engineering, Diponegoro University, Semarang, Indonesia
  4. Department of Mechanical Engineering, Diponegoro University, Semarang, Indonesia

IRJIET, Volume 9, Issue 5, May 2025 pp. 417-422

doi.org/10.47001/IRJIET/2025.905046

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References

  1. Ciliberti, D., Vecchia, P. D., Nicolosi, F., & Marco, A. D. (2017). Aircraft directional stability and vertical tail design: A review of semi-empirical methods. Progress in Aerospace Sciences, 140-172.
  2. Suvin, V., Ooi, E. T., Song, C., & Natarajan, S. (2024). Adaptive scaled boundary finite element method for hydrogen assisted cracking with phase field model. Theoretical and Applied Fracture Mechanics.
  3. Su, P., Chen, J., Yang, R., & Xiang, J. (2024). A New Isogeometric Finite Element Method for Analyzing Structures. CMES - Computer Modeling in Engineering and Sciences, 1883-1905.
  4. Rohini, D., AmarKarthik, A., Abinaya, R., Mathan, A., Midhun, S., & Dhushyanth, D. (2022). Buckling analysis of a commercial aircraft wing box and its structural components using Nastran patran. Materials Today: Proceedings, 895-901.
  5. Sung, D., Hong, S., & Lee, J. (2023). Numerical analysis of the rail surface crack propagation under rail uplift force: A parametric study on initial crack geometry. Engineering Failure Analysis, 153.
  6. Wu, H., Guo, Y., Xu, H., Dong, H., Li, Z., & Ke, Y. (2024). Investigation of angular deformation control for T-joint rib using multi-point constraint method. Journal of Constructional Steel Research, 213.
  7. Daoud, M., Chatelain, J., & Bouzid, A. (2017). Effect of rake angle-based Johnson-Cook material constants on the prediction of residual stresses and temperatures induced in Al2024-T3 machining. International Journal of Mechanical Sciences, 392-404.
  8. Zhang, S. R., Wang, L. J., Du, X. J., Jin, H. L., Zhang, Y. H., Sun, X. Y., . . . Zhang, K. (2021). Research of Fatigue Life Prediction for Optimization of the Gearbox Design Based on MSC.Patran. Strength of Materials , 636–645.
  9. Kusni, M., Widiramdhani, M., & Hadi, B. K. (2023). Composite wing structure optimization with static and buckling constraints using MSC-Nastran. In AIP Conference Proceedings, Vol. 2680, No. 1.
  10. Han, L., He, X., Ning, Y., Zhang, Y., & Zhou, Y. (2024). An aircraft structural risk assessment method considering fatigue crack propagation based on fatigue damage diagnosis and prognosis. International Journal of Fatigue.

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