| People | Locations | Statistics |
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| Naji, M. |
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| Motta, Antonella |
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| Aletan, Dirar |
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| Mohamed, Tarek |
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| Ertürk, Emre |
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| Taccardi, Nicola |
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| Kononenko, Denys |
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| Petrov, R. H. | Madrid |
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| Alshaaer, Mazen | Brussels |
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| Bih, L. |
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| Casati, R. |
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| Muller, Hermance |
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| Kočí, Jan | Prague |
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| Šuljagić, Marija |
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| Kalteremidou, Kalliopi-Artemi | Brussels |
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| Azam, Siraj |
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| Ospanova, Alyiya |
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| Blanpain, Bart |
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| Ali, M. A. |
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| Popa, V. |
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| Rančić, M. |
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| Ollier, Nadège |
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| Azevedo, Nuno Monteiro |
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| Landes, Michael |
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| Rignanese, Gian-Marco |
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Hühne, Christian
in Cooperation with on an Cooperation-Score of 37%
Topics
Publications (27/27 displayed)
- 2024Increased accuracy of service life prediction for fiber metal laminates by consideration of the manufacturing-induced residual stress statecitations
- 2024Bolt-bearing behavior of hybrid CFRP-steel laminates at low temperaturecitations
- 2024STRUCTURAL PART STIFFNESS TEST IN COMPARISON TO THE FE-PREDICTION. A TEST COMBINING CONTINUOUS STRUCTURE WITH COMPLEX INTERFACES
- 2024Equivalent plate formulation of Double-Double laminates for the gradient-based design optimization of composite structurescitations
- 2024Local Surface Toughening – A boltless crack stopping technology for aerospace structures
- 2024Validation of static residual strength analyses of fiber composite bonded joints
- 2023Steigerung der Robustheit von strukturellen Klebungen mittels Surface Toughening am Beispiel HAP
- 2023Anisotropic flexure hinges: Manufacturing and mechanical characterization forapplication in pressure-actuated morphing structures
- 2023THERMAL CONDUCTIVITY CHARACTERIZATION OF A CFRP SINGLE-LAP JOINT
- 2023Curvature Analysis of asymmetric Specimes for the residual stress quantification in fiber metal laminates
- 2023Comparison of Continuum Shell and Solid Element-Based Modeling Strategies for Mesoscale Progressive Damage Analysis of Fiber Compositescitations
- 2023Investigations on Guided Ultrasonic Wave Dispersion Behavior in Fiber Metal Laminates Using Finite Element Eigenvalue Analysiscitations
- 2023Anisotropic flexure hinges: Manufacturing and mechanical characterization for application in pressure-actuated morphing structurescitations
- 2023Gradient-based Design Optimization of Composite Structures using Double-Double Laminates
- 2023Aeroelastic Analysis of Actuated Adaptive Wingtips Based on Pressure-Actuated Cellular Structures
- 2023Effect of low temperature on mode I and mode II interlaminar fracture toughness of CFRP-steel hybrid laminatescitations
- 2022Polyetherimide-Reinforced Smart Inlays for Bondline Surveillance in Composites
- 2022In-situ quantification of manufacturing-induced strains in fiber metal laminates with strain gages
- 2022Applicability of Asymmetric Specimens for Residual Stress Evaluation in Fiber Metal Laminatescitations
- 2020Surface toughening - An industrial approach to increase the robustness of pure adhesive joints with film adhesivescitations
- 2019Decision Tree-based Machine Learning to Optimize the Laminate Stacking of Composite Cylinders for Maximum Buckling Load and Minimum Imperfection Sensitivity
- 2016Degradation analysis of fibre-metal laminates under service conditions to predict their durability
- 2016Experimental investigations on residual stresses during the fabrication of intrinsic CFRP-steel laminates
- 2013Effective lightweight design of a rocket interstage ring through mixed-integer optimization
- 2012Experimental identification of process parameters inducing warpage of autoclave-processed CFRP partscitations
- 2011A semi-analytical simulation strategy and its application to warpage of autoclave-processed CFRP partscitations
- 2005Robuster Entwurf beulgefährdeter, unversteifter Kreiszylinderschalen aus Faserverbundwerkstoff ; Robust Design of Unstiffened Cylindrical Shells made of Composite Material
Places of action
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document
Steigerung der Robustheit von strukturellen Klebungen mittels Surface Toughening am Beispiel HAP
Abstract
In the HAP (High Altitude Platform) project, the German Aerospace Center (DLR) is developing a solar-powered long-range aircraft, various payloads for Earth observation missions, the ground control station and operating concept. The mission conditions and objectives pose major challenges to the aircraft structure, especially with respect to lightweight design.From the point of manufacturing, the 27m long wing has to be manufactured in separate 1.2m long sub segments. The load carrying structure builds a round tube spar. In order to achieve the required degree of lightweight design, adhesively bonded joints are provided for the primary structure made of fiber composite material. The extremely thin structures with simultaneous highly rigid laminate orientations induce failure-triggering stress concentrations in the bonded scarf joint, which can lead to total failure of the structure during months of continuous operation.With the help of local Surface Toughening, the stress concentrations in the adhesive layer can be significantly reduced as FEA simulations show. Complementing the simulations, the concept is validated at coupon level and then transferred to the semi-automated production of the round tube spars using the winding process. Finally thespar joint is tested on element level.