Print Email Facebook Twitter Patching a Fuselage Title Patching a Fuselage: Application of Straight Fiber Variable Stiffness Laminates in Large Aerospace Structures Author Roepman, Thore (TU Delft Aerospace Engineering) Contributor van Campen, J.M.J.F. (mentor) Kassapoglou, C. (mentor) Degree granting institution Delft University of Technology Corporate name Delft University of Technology Programme Aerospace Engineering Date 2021-07-02 Abstract Straight fiber variable stiffness laminates use multiple overlapping patches to tailor the fiber orientations in particular regions of the laminate. A novel, automated framework for the design of manufacturable laminate has been developed using different stages. In the first and second stage an optimal stiffness distribution is determined using lamination parameters and converted to stacking sequences on a per region basis. In the third and fourth stages cellular automata and network theory are used to introduce cohesion between regions and comply with current manufacturing standards. Plates in uniaxial compression and cylinders in bending show an increase in buckling performance of 42% and 30% respectively. Such improvements do allow weight savings between 7-11% for these types of structures. When the additional cost of manufacturing and the cost-to-weight ratio for airlines are considered, these laminates already have the potential to significantly reduce the cost of air travel. Subject variable stiffnessBlendingAerospace Composite Structures To reference this document use: http://resolver.tudelft.nl/uuid:19ac3a19-c0b1-4b62-b8f7-8779d7eb5942 Embargo date 2023-07-02 Part of collection Student theses Document type master thesis Rights © 2021 Thore Roepman Files PDF Roepman_Thesis_20210617.pdf 3.78 MB Close viewer /islandora/object/uuid:19ac3a19-c0b1-4b62-b8f7-8779d7eb5942/datastream/OBJ/view