The goal of this research project is to prepare a series of analytical formulations to be used by a sizing tool for composite airplane fuselage frames. This tool verifies a series of failure modes related to a frame and calculates their respective margins of safety. The tool follows an iterative process until the optimal frame is reached according to user defined parameters.
The failure modes taken into account by the sizing tool are the composite material failure, local buckling, crippling, lateral buckling and global buckling. Each phenomenon is associated with its own mathematical formulations, assumptions and limitations. Existing formulations for the margin of safety calculations of each failure phenomenon was found from a literature review. Also, new formulations were developed within the current project for local and lateral buckling. In particular, an analytical formulation and an approximation method based on results obtained from finite element have been developed. Those two methods, combined, allow the estimation of the lateral buckling load of a fuselage composite frame. Finally, the current project required to create some secondary tools used during the development of the methodology for lateral buckling. Those tools are also presented in this thesis.
| Date | 10 Jul 2014 |
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| Original language | French |
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| Awarding Institution | - École de technologie supérieure
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| Supervisor | Martine Dubé (Supervisor) |
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Sauvé, J. (Author),
Dubé (Supervisor),
10 Jul 2014Student thesis: Master's thesis › Master in Engineering: Mechanical Engineering