Print Email Facebook Twitter Laminate Blending Demonstrator Title Laminate Blending Demonstrator: A buckling experimental campaign of a physical laminate blending demonstrator Author Mohamed Gomaa Abdulfattah Tolba, Mohamed (TU Delft Aerospace Engineering) Contributor van Campen, J.M.J.F. (mentor) Degree granting institution Delft University of Technology Programme Aerospace Engineering Date 2019-08-23 Abstract The use of fiber-reinforced composites in the aerospace industry has increased over the past couple of decades thanks to their high specific properties. Fiber-reinforced composites also enable engineers to tailor the stacking sequence to satisfy the required stiffness or strength requirements. However, locally optimizing the stacking sequence of composite laminates introduces incompatibilities between the locally optimized sections which jeopardize the structural integrity of the panel. This highlights the importance of “laminate blending” which is a term given to problems that involve the local optimization of laminates while taking into account continuity guidelines to ensure manufacturability. In this work, a constant thickness blended demonstrator of 32 layers and 5x5 sections was designed, manufactured and tested for its stiffness and critical buckling load. The results were compared to a constant stiffness conventional laminate of the same geometry and weight. The critical buckling load of the blending demonstrator was 80.9% higher than that of its conventional counterpart and the stiffness was 93.75% higher. Subject Variable stiffnessCompositesBucklinglaminate blending To reference this document use: http://resolver.tudelft.nl/uuid:2d03dfef-dea6-465f-be8c-8833eba99675 Part of collection Student theses Document type master thesis Rights © 2019 Mohamed Mohamed Gomaa Abdulfattah Tolba Files PDF Final_Blended_Reality_Gra ... 363744.pdf 46.85 MB Close viewer /islandora/object/uuid:2d03dfef-dea6-465f-be8c-8833eba99675/datastream/OBJ/view