Non-linear analysis of piezolaminated structures

In the recent years the study of smart structures has attracted significant researchers, due to their potential benefits in a wide range of applications, such as shape control, vibration suppression, noise attenuation and damage detection. The applications in aerospace industry are of great relevance, such as in active control of airplane wings, helicopter blade rotor, space antenna. The use of smart materials, such as piezoelectric materials, in the form of layers or patches embedded and/or surface bonded on laminated composite structures, can provide structures that combine the superior mechanical properties of composite materials and the capability to sense and adapt their static and dynamic response, becoming adaptive structures. The piezoelectric materials have the property of generate electrical charge under mechanical load or deformation, and the reverse, applying an electrical field to the material results in mechanical strain or stresses.

Les ressources de pouvoir et l’influence sur les politiques publiques : le cas des associations patronales de l’industrie aérospatiale au Québec.

Cette recherche vise à mieux comprendre la mobilisation des ressources de pouvoir, par les associations patronales, dans le but d’influencer les politiques publiques, plus précisément dans le secteur de l’aérospatiale. Dans un premier temps, cette recherche tente de répondre à notre première question de recherche qui s’attarde à l’impact de la logique de représentation sur la détermination du champ d’intervention en matière de politiques publiques. Dans un deuxième temps, notre seconde question de recherche tente de cerner comment les associations patronales utilisent leurs ressources de pouvoir dans le but d’influencer les politiques publiques. D’un angle théorique, cette recherche s’inscrit dans le courant des travaux néo-institutionnalistes. Tout d’abord, les associations patronales sont perçues comme étant des «entrepreneurs institutionnels» capables d’influencer leur environnement institutionnel (Campbell, 2004 ; Streeck et Thelen, 2005 ; Crouch, 2005). Plus précisément, nous constatons également que les employeurs et leurs associations sont en mesure de mobiliser plusieurs leviers de pouvoir pour influencer, à leur avantage, les développements politiques et économiques des sociétés capitalistes (Traxler et Huemer, 2007). D’un angle empirique, notre recherche vise trois objectifs : cerner les logiques de représentation des associations patronales; identifier quels types de ressources sont à la disposition des associations patronales; analyser comment s’exerce le lien entre les ressources de pouvoir (internes et externes) et l’influence potentielle sur les politiques publiques (commerciales et du travail). Afin de rencontrer nos objectifs de recherche, nous avons utilisé la technique de l’étude de cas. Cette méthode qualitative est l’un des meilleurs moyens pour analyser un phénomène inconnu car elle fournit des données en profondeur. Cette recherche suit les recommandations de Merriem (1998) qui propose de mener la recherche en trois grandes étapes : la préparation, la collecte des données et l’interprétation. Nous avons recueilli nos données à l’aide d’entrevues semi-dirigées, conduites à l’hiver 2012. Ces entrevues ont été menées auprès de représentants des associations patronales du secteur de l’aérospatiale. Nous avons effectué une analyse qualitative des données en fonction de notre revue de littérature et nos propositions de recherche. Dans cette perspective, nous avons utilisé la technique de l’appariement logique de Yin (1994) qui consistait à comparer nos observations avec nos propositions de recherche. Enfin, il faut mentionner que cette méthode de recherche (étude de cas) comporte une importante limite de recherche : la généralisation. Effectivement, nous pouvons difficilement généraliser les résultats de notre recherche à une autre population, considérant les nombreuses particularités du secteur de l’aérospatiale. Toutefois, cette recherche a tout de même contribué à enrichir les connaissances sur l’acteur patronal organisé au Canada.

Lean Enterprise Transformation: Measuring and Accelerating the transition to lean.

PowerPoint presentation that showcases: • Research Objectives • Strategic Value of the Lean Enterprise • Multi-Stakeholder Value Optimization • Lean Enterprise Self-Assessment Tool (LESAT) • Leading and Lagging Indicators of Lean Enterprise Transformation • Empirical Results in the Aerospace Industry • Accelerating the Lean Transformation - Linking LESAT to Strategic Objectives • Summary and Questions

Summary of Inventory Pilot Project March 1993 - December 1994

The Lean Aircraft Initiative began in the summer of 1992 as a “quick look” into the feasibility of applying manufacturing principles that had been pioneered in the automobile industry, most notably the Toyota Production System, to the U.S. defense aircraft industry. Once it was established that “lean principles” (the term coined to describe the new paradigm in automobile manufacturing) were indeed applicable to aircraft manufacturing as well, the Initiative was broadened to include other segments of the defense aerospace industry. These consisted of electronics/avionics, engines, electro-mechanical systems, missiles, and space systems manufacturers. In early 1993, a formal framework was established in which 21 defense firms and the Air Force formed a consortium to support and participate in the Initiative at M.I.T.

Summary of Research Conducted by the Manufacturing Systems Team 1994-2002

The Manufacturing Systems team was one of the research teams within the Lean Aerospace Initiative (LAI) whose goal was to document, analyze and communicate the design attributes and relationships that lead to significant performance improvements in manufacturing systems in the defense aerospace industry. This report will provide an integrated record of this research using the Production Operations Transition to Lean Roadmap as its organizing framework.

Lean Transition of Emerging Industrial Capability (LeanTEC)

Lean Transition of Emerging Industrial Capability (LeanTEC) program was a cooperative agreement between the Boeing Company and AFRL conducted from January 1998 to January 2002. The results of this program are documented in the Manual for Effective Technology Transition Processes included as an attachment to this report. This manual provides processes, procedures, and tools for greatly improving technology transition in the aerospace industry. Methodology for the implementation of these improvements is given along with methods for customizing the various processes, procedures, and tools for a given company or business unit. The indicated methodology was tested by the LeanTEC team and results are documented in the report.

Simulation of interlaminar and intralaminar damage in polymer-based composites for aeronautical applications under impact loading

La aplicación de materiales compuestos de matriz polimérica reforzados mediante fibras largas (FRP, Fiber Reinforced Plastic), está en gradual crecimiento debido a las buenas propiedades específicas y a la flexibilidad en el diseño. Uno de los mayores consumidores es la industria aeroespacial, dado que la aplicación de estos materiales tiene claros beneficios económicos y medioambientales. Cuando los materiales compuestos se aplican en componentes estructurales, se inicia un programa de diseño donde se combinan ensayos reales y técnicas de análisis. El desarrollo de herramientas de análisis fiables que permiten comprender el comportamiento mecánico de la estructura, así como reemplazar muchos, pero no todos, los ensayos reales, es de claro interés. Susceptibilidad al daño debido a cargas de impacto fuera del plano es uno de los aspectos de más importancia que se tienen en cuenta durante el proceso de diseño de estructuras de material compuesto. La falta de conocimiento de los efectos del impacto en estas estructuras es un factor que limita el uso de estos materiales. Por lo tanto, el desarrollo de modelos de ensayo virtual mecánico para analizar la resistencia a impacto de una estructura es de gran interés, pero aún más, la predicción de la resistencia residual después del impacto. En este sentido, el presente trabajo abarca un amplio rango de análisis de eventos de impacto a baja velocidad en placas laminadas de material compuesto, monolíticas, planas, rectangulares, y con secuencias de apilamiento convencionales. Teniendo en cuenta que el principal objetivo del presente trabajo es la predicción de la resistencia residual a compresión, diferentes tareas se llevan a cabo para favorecer el adecuado análisis del problema. Los temas que se desarrollan son: la descripción analítica del impacto, el diseño y la realización de un plan de ensayos experimentales, la formulación e implementación de modelos constitutivos para la descripción del comportamiento del material, y el desarrollo de ensayos virtuales basados en modelos de elementos finitos en los que se usan los modelos constitutivos implementados.

The effect of cure cycle heating rate on the fibre/matrix interface

Development of civil aerospace composites is key to future “greener” aircraft. Aircraft manufacturers must improve efficiency of their product and manufacturing processes to remain viable. The aerospace industry is undergoing a materials revolution in the design and manufacture of composite airframes. The Airbus A350 and Boeing 787 (both due to enter service in the latter part of this decade) will push utilisation levels of  composite materials beyond 50% of the total airframe by weight. This  change requires massive investment in materials technology, manufacturing capability and skills development. The Quickstep process provides the ability to rapidly cure aerospace standard composite materials whilst providing enhanced mechanical properties. Utilising fluid to transfer heat to the   composite component during the curing process allows far higher heat rates than with conventional cure techniques. The rapid heat-up rates reduce the viscosity of the resin system greatly to provide a longer processing window introducing greater flexibility and removing the need for high pressure during cure. Interlaminar fracture toughness (Mode I) and Interfacial Shear Strength of aerospace standard materials cured using Quickstep have been    compared to autoclave cured laminates. Results suggest an improvement in fibre-matrix adhesion.

Corrosion of magnesium alloy ZE41 – The role of microstructural features

Magnesium alloy ZE41, used extensively in the aerospace industry, possesses excellent mechanical properties albeit poor corrosion resistance. This paper investigates the mechanism of corrosion and the interaction between the grain boundary intermetallic phases, the Zr-rich regions within the grains and the bulk Mg-rich matrix. The results of optical and scanning electron microscopy (SEM) together with energy-dispersive X-ray (EDX) and atomic force microscopy (AFM) potential map measurements have shown the importance of the microstructure in the initiation and propagation of corrosion in an aqueous environment, indicating that the Zr-rich regions play a distinct role in the early stages of corrosion in this alloy.

Study of phase transformation and work hardening phenomenon during drilling of Ti-5553 and Ti-64

Titanium 5553 is a recently developed modification of Russian near-β titanium alloy VT-22 which has applications and potential particularly in the aerospace industry for such key components as landing gear. However, indications are that Ti-5553 has poorer machinability characteristics than other Ti alloys and a comprehensive and far-reaching analysis is a necessary research imperative. This paper presents the result of phase transformation and work hardening during drilling of Ti-5553 compared with Ti-64. The aim of this research work is to optimise the machining condition for Ti-5553, in which the β to a phase transformation, together with material work hardening could be fully understood. Analysis of machinability indicators, such as subsurface micrograph and hardness of drilled samples and drilling forces and torques, demonstrated that Ti-5553 generally has poorer machinability characteristics than Ti-64 and to some extent this variation has been quantified to allow for further and more detailed investigation.

Deformation induced phase transformation during machining of Ti-5553

Ti-5553 is a relatively new titanium alloy with applications particularly in the aerospace industry for such key structural components as landing gear. However, during machining of Ti-5553, the elevated temperature and high strain at tool-workpiece interface may alter workpiece microstructure and result in ß to a phase transformation. During phase transformation, some intermediated phase such as w phase may form which is brittle and hard to machine, and it could reduce the fatigue life of machined components. The aim of this research work is to optimize the machining condition for Ti-5553, in which its hot deformation behavior in terms of ß to a phase transformation could be fully understood. Analysis of variables such as micrographs of phase components and cutting zone temperature demonstrates that the cutting temperature governs the formation of final phase components and to some extent this variation has been quantified to allow for further and more detailed investigation.

An integrated approach to shape and topology optimisation of mechanical structures

In mechanical engineering, simulation and optimisation methods have become indispensable. The thesis looks into a novel way to combine shape and topology optimisation approaches. The proposed method - named IST for Integrated Shape And Topology Optimisation - proves to be beneficial for many application in the automotive and aerospace industry.

Corrosion of mg alloy ZE41 and its mitigation using ionic liquids

Magnesium alloy ZE41 (Mg-Zn-RE-Zr), which is used extensively in the aerospace industry, possesses excellent mechanical properties albeit poor corrosion resistance. This work investigates the mechanism of corrosion, and the interaction between the grain boundary intermetallic phases, the zirconium (Zr)-rich regions within the grains and the bulk Mg rich matrix in both the as-cast and heat-treated conditions. The results of optical and scanning electron microscopy (SEM) show the importance of the microstructure in the initiation and propagation of corrosion in an aqueous environment. The Zr-rich regions play a distinct role in the early stages of corrosion with this alloy. The second part of this work investigates the interaction of two different ionic liquids (ILs) with the surface of the ZE41 alloy. ILs based on trihexyltetradecylphosphonium (P 6,6,6,14) coupled with either diphenylphosphate (DPP) or bis(trifluoromethanesulfonyl) amide (Tf 2N) have been shown to react with Mg alloy surfaces, leading to the formation of a surface film that can improve the corrosion resistance of the alloy. The interaction of the ILs with the ZE41 surface has been investigated by optical microscopy and SEM. Surface characterization has been performed using Time of Flight-Secondary Ion Mass Spectrometry (ToF-SIMS) and X-ray Photoelectron Spectroscopy (XPS). The surface characterization and microscopy revealed the preferential interaction with the grain boundaries and grain boundary phases. Thus the morphology and microstructure of the Mg surface seems critical in determining the nature of the interaction with the IL. The corrosion protection of the IL films formed on the ZE41 surface was investigated by SEM and potentiodynamic polarisation.

A preliminary assessment of machinability of titanium alloy Ti 6Al 4V during thin wall machining using trochoidal milling

Titanium alloys are of great demand in the aerospace and biomedical industries. Most the titanium products are either cast or sintered to required shape and finish machined to get the appropriate surface texture to meet the design requirements. Ti-6Al-4V is often referred as work horse among the titanium alloys due to its heavy use in the aerospace industry. This paper is an attempt to investigate and improve the machining performance of Ti-6Al-4V. Thin wall machining is an advance machining technique especially used in machining turbine blades which can be done both in a conventional way and using a special technique known as trochoidal milling. The experimental design consists of conducting trials using combination of cutting parameters such as cutting speed (vc), 90 and 120 m/min; feed/tooth (fz) of 0.25 and 0.35 mm/min; step over (ae) 0.3 and 0.2; at constant depth of cut (ap) 20mm and using coolant. A preliminary assessment of machinability of Ti-6Al-4V during thin wall machining using trochoidal milling is done. A correlation established using cutting force, surface texture and dimensional accuracy.

Forming behaviour analysis and constitutive modelling of Ti-6Al-4V at room temperature.

 A constitutive model was proposed in this thesis and a promising approach for accurate prediction of forming behaviour of high strength titanium alloy sheet metal forming at room temperature is presented. Outcomes showed a potential solution of cold roll forming of this material for aerospace and automotive structural applications.