A Finite Element Comparison of Monocoque and Semi-Monocoque Aerospace Shell Structures

Author

Benazir, Mr. G. Gopinath, Mr. A. Sai Kumar, Dr. Anoop Kumar Shukla


Abstract

 The fuselage is one of the primary structural components of an aircraft, providing strength and support to the overall airframe. Monocoque and semi-monocoque structures are commonly used in aircraft fuselage construction, in which the outer skin carries external loads and internal pressurization loads, while the semi-monocoque structure is further reinforced using stringers, frames, and bulkheads. Nowadays, reducing structural weight has become an important consideration in aircraft design due to increasing manufacturing costs and the need for improved performance. Conventional aircraft fuselages are generally manufactured using metallic alloys, while advanced materials are being explored to reduce structural weight and improve service life. Sandwich-structured composites are a special class of composite materials consisting of two thin, stiff outer skins bonded to a lightweight and relatively thick core. Although the core material generally has lower strength, its greater thickness provides high bending stiffness while maintaining a low overall density. In the present work, sandwich composite structures are considered for monocoque and semi-monocoque aircraft fuselage configurations to evaluate their structural performance under different loading conditions. Different core materials, such as balsa wood, synthetic foam, and honeycomb, are considered for the comparative study. The three-dimensional models are developed using CATIA V5 R20. Static structural and modal analyses are carried out using ANSYS 14.5 to evaluate the strength, deformation, and vibration characteristics of the proposed structures.


Keywords

Aircraft Fuselage, Monocoque and Semi-Monocoque Structures, Sandwich Composite Materials, CATIA V5, Static Structural and Modal Analysis (ANSYS 14.5).



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References


  1. Vishal Sagar, H. Rao, and A. Purushotham, “Design and vibration analysis of fuselage structure using SolidWorks and ANSYS,” vol. 1, no. 3, Sep. 2014.
  2. Cheng, “Preliminary fuselage structural configuration of a flying-wing type airliner,” M.Sc. by Research thesis, Cranfield University, Academic Year 2011–2012.
  3. Rust and M. Kracht, “Recent experiences in load analysis of aircraft fuselage panels,” vol. 1, no. 2, Dec. 2013.
  4. M. Nadakatti and V. B. Melmari, “A review on stress analysis of the fuselage structure and study of the effect of overload on fatigue crack growth,” Jan. 2014.
  5. L. Giles, “Design-oriented analysis of aircraft fuselage structure,” NASA Langley Research Center, Hampton, VA, USA.
  6. Rust, M. Kracht, and J. Overberg, “Experiences with ANSYS in ultimate-load analyses of aircraft fuselage panels,” Jan. 2009.
  7. Yusuf, Y. Nukman, S. Z. Dawal, D. Chandra, and N. Sofia, “Conceptual design of fuselage structure of very light jet aircraft,” Latest Trends on Theoretical and Applied Mechanics, Fluid Mechanics and Heat & Mass Transfer.
  8. -M. Huang and C.-C. Chen, “Optimal design of dynamic absorbers on vibration and noise control of the fuselage,” Computers & Structures, vol. 76, no. 6, pp. 691–702.
  9. Dey and M. K. Singha, “Dynamic stability analysis of composite skew plates subjected to periodic in-plane load,” Thin-Walled Structures, vol. 44, pp. 937–942.
  10. Li and P. Xia, “Aeroelastic stability of full-span tiltrotor aircraft model in forward flight,” Chinese Journal of Aeronautics, vol. 30, no. 6, pp. 1885–1894.
  11. Garicano-Mena, E. Ferrer, S. Sanvido, and E. Valero, “A stability analysis of the compressible boundary layer flow over indented surfaces,” Computers & Fluids, vol. 160, pp. 14–25.
  12. Qu, Y. Li, H. Xu, D. Zhang, and G. Yuan, “Aircraft nonlinear stability analysis and multidimensional stability region estimation under icing conditions,” Chinese Journal of Aeronautics, vol. 30, no. 3, pp. 976–982.
  13. A. Rossi and S. F. M. de Almeida, “Design and analysis of a composite fuselage,” in Proc. Brazilian Symposium on Aerospace Engineering and Applications, 2009.
  14. Prem Chand and K. Krishna Veni, “Weight and strength optimization of airplane fuselage structure for different materials,” International Journal of Mechanical Engineering Research and Technology, vol. 1, no. 2, Nov. 2015.
  15. L. Fasanella, K. E. Jackson, Y. T. Jones, G. Frings, and T. Vu, “Crash simulation of a Boeing 737 fuselage section vertical drop test.”
  16. Shilpa, M. Venkateshwar Reddy, and A. Siva Kumar, “Design and analysis of fuselage structure using SolidWorks and ANSYS,” International Journal of Engineering Sciences & Research Technology, vol. 3, no. 9, Sep. 2014.
  17. Yusuf, Y. Nukman, S. Z. Dawal, D. Chandra, and N. Sofia, “Conceptual design of fuselage structure of very light jet aircraft,” in Proc. Latest Trends on Theoretical and Applied Mechanics, Fluid Mechanics and Heat & Mass Transfer.
  18. -G. Son, D. Kumar, Y.-B. Park, J.-H. Kweon, and J.-H. Choi, “Structural design and analysis of composite aircraft fuselage used to develop AFP technology,” in Proc. Aerospace and Informatics Engineering, Japan, Feb. 21–23

 

 

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