Investigation on laser shock peening capability by FE simulation

Laser shock peening is a technique similar to shot peening that imparts compressive residual stresses in materials for improving fatigue resistance. The ability to use a high energy laser pulse to generate shock waves, inducing a compressive residual stress field in metallic materials, has applications in multiple fields such as turbo-machinery, airframe structures, and medical appliances. The transient nature of the LSP phenomenon and the high rate of the laser's dynamic make real time in-situ measurement of laser/material interaction very challenging. For this reason and for the high cost of the experimental tests, reliable analytical methods for predicting detailed effects of LSP are needed to understand the potential of the process. Aim of this work has been the prediction of residual stress field after Laser Peening process by means of Finite Element Modeling. The work has been carried out in the Stress Methods department of Airbus Operations GmbH (Hamburg) and it includes investigation on compressive residual stresses induced by Laser Shock Peening, study on mesh sensitivity, optimization and tuning of the model by using physical and numerical parameters, validation of the model by comparing it with experimental results. The model has been realized with Abaqus/Explicit commercial software starting from considerations done on previous works. FE analyses are “Mesh Sensitive”: by increasing the number of elements and by decreasing their size, the software is able to probe even the details of the real phenomenon. However, these details, could be only an amplification of real phenomenon. For this reason it was necessary to optimize the mesh elements' size and number. A new model has been created with a more fine mesh in the trough thickness direction because it is the most involved in the process deformations. This increment of the global number of elements has been paid with an "in plane" size reduction of the elements far from the peened area in order to avoid too high computational costs. Efficiency and stability of the analyses has been improved by using bulk viscosity coefficients, a merely numerical parameter available in Abaqus/Explicit. A plastic rate sensitivity study has been also carried out and a new set of Johnson Cook's model coefficient has been chosen. These investigations led to a more controllable and reliable model, valid even for more complex geometries. Moreover the study about the material properties highlighted a gap of the model about the simulation of the surface conditions. Modeling of the ablative layer employed during the real process has been used to fill this gap. In the real process ablative layer is a super thin sheet of pure aluminum stuck on the masterpiece. In the simulation it has been simply reproduced as a 100µm layer made by a material with a yield point of 10MPa. All those new settings has been applied to a set of analyses made with different geometry models to verify the robustness of the model. The calibration of the model with the experimental results was based on stress and displacement measurements carried out on the surface and in depth as well. The good correlation between the simulation and experimental tests results proved this model to be reliable.

Measurement of LSP-induced residual stresses and fatigue life on thin-walled aluminium alloys specimens

This thesis work encloses activities carried out in the Laser Center of the Polytechnic University of Madrid and the laboratories of the University of Bologna in Forlì. This thesis focuses on the superficial mechanical treatment for metallic materials called Laser Shock Peening (LSP). This process is a surface enhancement treatment which induces a significant layer of beneficial compressive residual stresses underneath the surface of metal components in order to improve the detrimental effects of the crack growth behavior rate in it. The innovation aspect of this work is the LSP application to specimens with extremely low thickness. In particular, after a bibliographic study and comparison with the main treatments used for the same purposes, this work analyzes the physics of the operation of a laser, its interaction with the surface of the material and the generation of the surface residual stresses which are fundamentals to obtain the LSP benefits. In particular this thesis work regards the application of this treatment to some Al2024-T351 specimens with low thickness. Among the improvements that can be obtained performing this operation, the most important in the aeronautic field is the fatigue life improvement of the treated components. As demonstrated in this work, a well-done LSP treatment can slow down the progress of the defects in the material that could lead to sudden failure of the structure. A part of this thesis is the simulation of this phenomenon using the program AFGROW, with which have been analyzed different geometric configurations of the treatment, verifying which was better for large panels of typical aeronautical interest. The core of the LSP process are the residual stresses that are induced on the material by the interaction with the laser light, these can be simulated with the finite elements but it is essential to verify and measure them experimentally. In the thesis are introduced the main methods for the detection of those stresses, they can be mechanical or by diffraction. In particular, will be described the principles and the detailed realization method of the Hole Drilling measure and an introduction of the X-ray Diffraction; then will be presented the results I obtained with both techniques. In addition to these two measurement techniques will also be introduced Neutron Diffraction method. The last part refers to the experimental tests of the fatigue life of the specimens, with a detailed description of the apparatus and the procedure used from the initial specimen preparation to the fatigue test with the press. Then the obtained results are exposed and discussed.

Numerical evaluation of material model and thickness effect on LSP induced residual stresses

Laser Shock Peening (LSP) is a technological process used to improve mechanical properties in metallic components. When a short and intense laser pulse irradiates a metallic surface, high pressure plasma is generated on the treated surface; elasto-plastic waves, then, propagate inside the target and create plastic strain. This surface treatment induces a deep compressive residual stresses field on the treated area and through the thickness; such compressive residual stress is expected to increase the fatigue resistance, and reduce the detrimental effects of corrosion and stress corrosion cracking.

Installazione del navigation stack su rover terrestre e applicazione del kinect nello human-robot interaction.

Progetto SHERPA. Installazione e configurazione del Navigaton Stack su Rover terrestre. Utilizzo e configurazione di LMS151 Sick. Utilizzo e configurazione di Asus Xtion Pro. Progettazione di software per la localizzazione e l'inseguimento di persone tramite camera di profondita.

Studio del comportamento meccanico e tribologico della lega AlSi10Mg prodotta mediante Laser-based Powder Bed Fusion sottoposta ad un ciclo tecnologico ottimizzato

AlSi10Mg alloy is one of the most widely used alloys for producing structural components by Laser-based Powder Fusion (L-PBF) technology due to the high mechanical and technological properties. The present work aims to characterize mechanically and tribologically the L-PBF AlSi10Mg alloy subjected to both heat treatment and surface modification cycles. Specifically, the effects of three heat treatments on the tribological and mechanical properties of the alloy were analyzed: T5 (artificial aging at 160 °C for 4 h), T6 rapid solution heat treatment (solution heat treatment at 510 °C for 1h and aging at 160 °C for 6 h), and T6 benchmark (solution heat treatment at 540 °C for 1h and aging at 160 °C for 4 h), the latter used as a benchmark. The study highlighted how the better balance between strength and ductility properties induced by the introduction of heat treatments leads to lower wear resistance and not significant variations in the friction coefficient of the alloy. The tribological and mechanical behavior of the alloy coated with two different coating structures, consisting of (i) chemical Ni (Ni-P) and (ii) Ni-P + DLC, was also evaluated. The goal was the identification of a deposition cycle such as to guarantee the optimization of the mechanical and tribological behavior of the alloy. The Ni-P coating provided good wear resistance but an increase in the coefficient of friction. In contrast, using the DLC top coating resulted in excellent tribological performance in wear resistance and friction coefficient. The samples characterized by the Ni-P + DLC multilayer coating were subsequently subjected to mechanical characterization. The results obtained highlighted problems of adhesion and incipient breaking of the material due to the different mechanical behavior of the coating, considerably reducing the mechanical performance of the alloy coated with Ni-P+DLC multilayer solution compared to the specimens in the un-coated condition.