Advanced modelling and virtual testing for innovative high performance composite aerospace structures
- Autores: Jordi Torres Quintana
- Directores de la Tesis: Jose Norberto Blanco Villaverde (dir. tes.), Mª de la Encarnacion Olmo Castillejos (codir. tes.)
- Lectura: En la Universitat de Girona ( España ) en 2015
- Idioma: español
- Tribunal Calificador de la Tesis: José María Pintado Sanjuanbenito (presid.), Josep Costa i Balanzat (secret.), José Luis Pérez Aparicio (voc.)
- Materias:
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- Resumen
Composite material structures of polymeric matrix are prevailing in aerospace applications because of the combination of lightness and high structural properties. However, the complexity in the analysis and modelling of these materials requires the utilization of computational tools in order to characterize their structural performance.
The objective of this thesis is to develop methodologies of modelling and virtual testing for two promising structural products in composite material. The simulations tools generated may reduce the costs incurred by the industry in terms of time and resources during the processes of design, optimization and verification of these innovative products.
In the first part of the thesis a design and optimization methodology of the composite stiffened panels under compression loading is developed. These types of stiffened panels are used for aircraft and helicopters fuselages. The virtual testing tool is based on a set of stability and strength criterion, used as design variable. The stability is assessed by means of the buckling critical load, together with displacement indicators in order to monitor the local buckling and global bending. The strength is determined by means of the intralaminar failure criterion LaRC-03.
The second part of the thesis is focused on the development of a virtual testing tool for the design of structures in ¿grid-stiffened¿ and ¿lattice¿ configuration for Payload Adapters of space launchers.
The innovative manufacturing technology Advanced Fibre Placement (AFP), permits replacing the traditional monolithic and sandwich concepts for high performance products as ¿grid-stiffened¿ and ¿lattice¿ designs. These news products offer a significant reduction of the weight of structural elements highly demanded as Payload Adapters of space launchers.
First, the virtual testing is focused in the study of viability of these new designs, studying the accomplishment of the weight, frequency, buckling and strength requirements. In the second chapter, the influence of the different design variables in the frequency of cylindrical structures in configuration ¿lattice¿ is analysed. Finally, a virtual testing methodology to determine the performance of a technology demonstrator is developed. The technology demonstrator is defined by means of the results obtained in the previous chapters.
The development of the virtual testing tools for both innovative products has permitted the gathering of partial results which represent a direct aid for the industry and for future researches. These tools can be applied for the design of structural elements of composite materials with different characteristics than those defined in the scope of this thesis.
