Abstract An important aspect of additive manufacturing is reducing the weight while maintaining the mechanical properties of the material. While the properties of the additive manufactured specimen depend on the type of the materials used for the filament, the settings of printing also affect the properties of specimen. Consequently, this work is about the investigation of the effect of 3D printing settings on the weight reduction and the mechanical properties of the specimen between two different filament materials and to achieve an optimum compromise between the two. The infill density and the build orientation and pattren of the printed layers are the variables being considered while all other setting remain constant in all tests. Experiments are performed using two different filaments materials types; PLA Carbon fiber and PETG Carbon fiber composites. Ahmed Abdulrahman Said King Abdulaziz University Email: ahmad.a.alsayed@hotmail.com

Objective: Surface patterning strategy was proposed to facilitate the formation of adhesive ligaments using pulsed CO2laser irradiation, in order to enhance fracture toughness and arrest the crack propagation within adhesively bonded composite joints. Methods: Arrest regions (highlighted in green in the video), with higher interfacial strength but lower fracture toughness than the uniformly laser ablated (LA) baseline surface, are alternatively placed on the top and bottom CFRP/adhesive interface. Mode I fracture toughness was assessed through the double cantilever beam (DCB) configuration. Results: The proposed patterning strategy is promising to trigger adhesive ligaments and hold the separating arms, promoting a R-curve-like response of the bonded joint, where the energy release rate keeps increasing as the crack propagates. The proposed patterning strategy shed light to the design of reliable and safety adhesively bonded CFRP joints.

WHAT IS RTP? The term refers to a multilayer pipe construction where at least one layer is acting as reinforcement. APPLICATION OVERVIEW & REQUIREMENTS ONSHORE TESTING & VALIDATION –HOW CAN WE SHORTEN TIME TO MARKET? COMPOSITE LAY-UP OPTIMIZATION COMPOSITE FAILURE CRITERIA Tsai-Hill Failure Criterion (TH) Hashin’sfailure criteria (HF) Fiber failure criteria (FF) ANALYSIS OF BURST PRESSURE ANALYSIS OF MINIMUM BENDING RADIUS ANALYSIS OF LONG-TERM DESIGN LIFE RESULTS

Enhanced composite T-joint energy dissipation using laser patterning strategy M. Hashem, A. Wagih, G. Lubineau Introduction Internal aircraft structures such as ribs, spars and stringers are required to be connected and must be able to transfer loads to the skin. Metallic joints require bolts and rivets which cause weight penalties and stress concentration. Composite T-joints allows the connection of structural components while maintaining low weight and high toughness. Objectives â ¢Investigate the efficacy of a novel CO_2 laser pre-treatment on the toughness of CFRP T-joints. â ¢Understand the failure mechanisms in toughened CFRP T-joints considering different surface ply orientations.   Methods CFRP T-joints were manufactured by using unidirectional carbon fiber prepregs composed of toughened epoxy resin and carbon fibers. After a general peel-ply treatment, the adherents experienced CO_2 laser treatment. We applied laser treatment with two different energy, low and high, to create laser pattern of cleaning, LC, and ablation, LA, treatment as shown in Fig. 1.  Upon the laser treatments the stiffeners and skins were secondary bonded using an Araldite 420 A/B adhesive and mechanical tested using pull-off tests. The baseline joint, where peel ply treatment was applied is nominated as â PPâ . The laser patterned joint, where the alternative high and low laser power was applied, is nominated as â B5G5â . Results High surface roughness profile fluctuations were noticed at LC treated regimes, but low profiles were observed at LA regimes. SEM shows how the high fluence LA treatment exposed fully the fibers as compared to LC which minorly removed contaminants from the surface. PP baseline resulted in catastrophic failure at low extensions (4 mm). However, the laser treated T-joints showed progressive failure with improved toughness and extensions. The maximum load and extension for B5G5 joint reach 1712 N and 17.8 mm, respectively, compared to  805 N and 4 mm for PP joint. Discussion The enhancement observed for B5G5 T-joints was related with the creation of adhesive ligaments between the top and bottom adhesive layers (Fig. 5). The adhesive ligaments were generated at the transition between LA and LC treatment due to the difference in roughness between both treatments as shown in Fig. 2, which arrest the crack propagation at one interface allowing crack migration to the other interface. The effect of laser patterning was optimised when a 0° ply fiber direction was placed at the interface.   Owing to the crack migration, the ligament formation and breakage during testing, progressive failure occurred in B5G5 T-joints with larger improvements in the energy dissipation (toughness) reaching 12 times larger than the conventional PP treatment. Conclusions   â ¢Laser pre-treatment provided enhanced toughness and energy dissipation as compared to PP.   â ¢Laser patterning resulted in up to ~12x enhanced energy dissipation by the activation of non-local damage mechanisms which produced progressive failure indicating safter joints.