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IMPACT OF ICING ON AIRCRAFT AERODYNAMICS
Abstract:
Icing on aircraft surfaces presents a significant challenge to aviation safety by adversely affecting aerodynamic performance. This study investigates the impact of icing on various aerodynamic parameters, including lift, drag, and stall characteristics. When ice forms on critical surfaces like wings, tailplanes, and control surfaces, it alters the smooth airflow, increasing drag and reducing lift, leading to decreased flight efficiency and heightened risk of accidents. Using computational fluid dynamics (CFD) simulations and wind tunnel experiments, this research examines how different types of ice accretion—such as rime and glaze ice—affect aircraft performance across various weather conditions. The results underscore the importance of efficient de-icing systems and predictive icing models to ensure safer and more reliable aircraft operation. This study contributes to a better understanding of icing phenomena and offers insights for improving ice detection and mitigation technologies in modern aviation.
Table of Contents
Chapter One: Introduction
1.1 Background of the Study
1.2 Statement of the Problem
1.3 Research Objectives
1.4 Research Questions
1.5 Significance of the Study
1.6 Scope and Limitations
1.7 Definition of Key Terms
Chapter Two: Literature Review
2.1 Overview of Aerodynamics in Aircraft
2.2 The Physics of Icing and Ice Formation
2.3 Types of Aircraft Icing: Rime, Glaze, and Mixed Ice
2.4 Impact of Icing on Aircraft Performance: Lift, Drag, and Stall
2.5 Icing Detection and De-Icing Techniques
2.6 Icing and Aviation Safety: Case Studies and Accidents
2.7 Gaps in the Literature
Chapter Three: Research Methodology
3.1 Research Design
3.2 Data Collection Methods
3.2.1 Wind Tunnel Testing
3.2.2 Computational Fluid Dynamics (CFD) Simulations
3.3 Experimental Setup and Procedure
3.4 Data Analysis Techniques
3.5 Reliability and Validity
3.6 Ethical Considerations
Chapter Four: Results and Discussion
4.1 Analysis of Ice Accretion on Aircraft Surfaces
4.2 Impact of Icing on Lift and Drag Coefficients
4.3 Effects on Stall Angle and Aircraft Stability
4.4 Comparison of Rime and Glaze Ice Effects
4.5 Icing Effects Across Different Aircraft Configurations
4.6 Discussion of Findings
Chapter Five: Conclusion and Recommendations
5.1 Summary of Findings
5.2 Implications for Aircraft Design and Safety
5.3 Recommendations for Improved Icing Detection and Mitigation
5.4 Limitations of the Study
5.5 Suggestions for Further Research
References
Chapter One: Introduction
1.1 Background of the Study
The safety and efficiency of aircraft are paramount in the aviation industry, with various environmental factors influencing their performance. One significant factor is icing, which occurs when ice forms on aircraft surfaces during flight, particularly in cold and moist conditions. Ice accumulation can dramatically alter the aerodynamic characteristics of an aircraft, affecting its lift, drag, and overall handling. Understanding the impact of icing on aircraft aerodynamics is crucial for developing effective de-icing strategies and enhancing aviation safety.
The aerodynamics of an aircraft play a crucial role in its overall performance, influencing factors such as lift, drag, and stability. Icing, particularly in flight, poses significant challenges to these aerodynamic properties. When ice accumulates on an aircraft’s wings, tail, or control surfaces, it alters the smooth airflow necessary for optimal performance, leading to increased drag and decreased lift. This phenomenon can severely impair an aircraft’s ability to maneuver, posing risks to safety and efficiency.
Icing can occur in various atmospheric conditions, including clouds, precipitation, and temperature variations, often unexpectedly affecting flight operations. Understanding the impact of icing on aircraft aerodynamics is vital for engineers and pilots to enhance safety protocols and improve design practices. As the aviation industry continues to evolve, the integration of advanced anti-icing technologies and materials becomes increasingly important. This study aims to explore the mechanisms of ice formation on aircraft surfaces, analyze its effects on aerodynamic performance, and evaluate current mitigation strategies. By examining these factors, we can better understand the implications of icing for aircraft design and operational safety, ultimately contributing to the advancement of aviation technology in challenging weather conditions.
1.2 Statement of the Problem
Icing on aircraft poses serious risks, leading to reduced performance and control difficulties. Historical data reveal numerous incidents and accidents attributed to icing, highlighting the need for a comprehensive understanding of its effects on aerodynamics. This study aims to investigate the specific impact of ice formation on various aerodynamic parameters and to assess the implications for flight safety and aircraft design.
1.3 Research Objectives
The primary objectives of this study are as follows:
To analyze the effects of different types of ice (rime, glaze, and mixed) on the aerodynamic performance of aircraft.
To evaluate how ice accretion impacts lift, drag, and stall characteristics.
To identify and discuss the implications of icing on aircraft safety and operational efficiency.
To propose recommendations for improving icing detection and de-icing technologies in aviation.
1.4 Research Questions
This research seeks to answer the following questions:
What are the effects of ice accumulation on the lift and drag coefficients of aircraft?
How does icing influence the stall angle and overall stability of an aircraft?
What are the differences in aerodynamic impact between rime and glaze ice?
What measures can be implemented to mitigate the effects of icing on aircraft performance?
1.5 Significance of the Study
This study is significant for several reasons. First, it contributes to the existing body of knowledge on aircraft aerodynamics and icing phenomena, providing valuable insights for engineers and researchers. Second, it highlights the importance of effective icing management strategies in enhancing aviation safety and operational efficiency. Finally, the findings can inform the development of improved de-icing technologies and policies, ultimately leading to safer flight operations.
1.6 Scope and Limitations
The scope of this study is focused on the aerodynamic effects of icing on fixed-wing aircraft. The research will primarily examine the impact of rime and glaze ice on lift, drag, and stall characteristics through computational fluid dynamics (CFD) simulations and wind tunnel experiments. Limitations include the potential variability in icing conditions and the challenges of replicating all real-world scenarios in a controlled environment.
1.7 Definition of Key Terms
Icing: The accumulation of ice on aircraft surfaces, typically occurring in cold and moist atmospheric conditions.
Lift: The aerodynamic force that directly opposes the weight of an aircraft and supports it in the air.
Drag: The aerodynamic resistance experienced by an aircraft as it moves through the air.
Stall: A condition in which the airflow separates from the wing surface, leading to a sudden loss of lift.
Rime Ice: A rough, opaque ice that forms when supercooled water droplets freeze quickly upon impact with a surface.
Glaze Ice: A smooth, transparent ice that forms when supercooled water droplets freeze slowly, resulting in a layer of clear ice.
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APPRAISAL OF THE COST OF MATERIALS AND THEIR EFFECT TO THE CONSTRUCTION INDUSTRY IN NIGERIA
CHAPTER ONE
Background of the study
The growing need for construction of all types coupled with a tight monetary supply has provided the construction industry with a big challenge to cut cost.
According to Mendelson and Greenfield (1996) the remaining part of the twentieth century would involve corporations, institutions and government in a race to survive. The attendant dwindling economic fortune of nations economies around the World have geared up the participant in these sectors (the client in particular) to take up the challenge of ensuring efficient use of their resources to obtain value for money in terms of performance.
The total cost of construction in normal circumstances is expected to be the sum of the following cost: Materials, Labour, Site Overheads, Equipment/Plant, Head office Cost and Profit but in many parts of the world particularly in Nigeria, there are other costs to be allowed for.
These costs according to Mbachu and Nkado (2004) have obvious negative implications for the key stakeholders in particular, and the industry in general. To the client, high cost implies added costs over and above those initially agreed upon at the onset, resulting in less returns on investment. To the end user, the added costs are passed on as higher rental / lease costs or prices. To the consultants, it means inability to deliver value – for – money and could tarnish their reputation and result in loss of confidence reposed in them by clients. To the contractor, it implies loss of profit through penalties for non- completion, and negative word of mouth that could jeopardize his/her chances of winning further jobs, if at fault.
The proposed work will investigate and report the other costs to be allowed for, which are the basic factors affecting construction cost in Nigeria and also proffer solutions to how construction cost can be minimized.
1.1 Statement of the Problem
The demand for more construction of all types, coupled with a tight monetary supply has provided the construction industry with a big challenge to cut costs. The problem of high contract costs of all aspects of construction is becoming obvious. Consequently, substantial increases are being observed in projects.
This substantial increase has brought about loss of client confidence in consultants, added investment risks, inability to deliver value to clients, and disinvestment in the construction industry.
1.2 Aim and Objectives of the study
The aim of the study is to find out the factors affecting construction cost in Nigeria and proffer solutions to how construction cost c an be minimized.
The objectives of the study are as follows:
1. To identify the main factors affecting construction cost in Nigeria.
2. To determine the severity rank of the factors amongst clients, consultants and contractors.
3. To determine the agreement ranking factors between clients, consultants and contractors.
4. To proffer solutions on how to minimize construction cost in Nigeria.
1.3 Research Hypotheses
To test the hypothesis:
1 (a). Ho: Contractors and Clients do not generally agree on the severity rank of the factors affecting construction cost in Nigeria
1 (b). H1: Contractors and Clients generally agree on the severity rank of the factors affecting construction cost in Nigeria
2 (a). Ho: Clients and Consultants do not generally agree on the severity rank of the factors affecting construction cost in Nigeria
2. (b) H1: Clients and Consultants do not generally agree on the severity rank of the factors affecting construction cost in Nigeria
3. (a) Ho: Consultants and Contractors do not generally agree on the severity rank of the factors affecting construction cost in Nigeria
3. (b) H1: Consultants and Contractors generally agree on the severity rank of the factors affecting construction cost in Nigeria
1.4 Significance of the study
An assessment of the study would enable Clients, Contractors and Consultants give an economic approach to construction work such that they would be able to identify the dominating factors leading to high construction cost in Nigeria.
The application of the solutions proffered to minimizing construction cost would restore client’s confidence in consultants, reduce investment risks, and generally boost the viability and sustainability of the industry
1.5 Scope and Delimitations
The scope of this research is limited to identification of essential factors affecting construction cost and proffering solutions on how to reduce construction cost in Nigeria. The study is limited to projects in the Lagos metropolis of Nigeria because there is easy access of information in the Lagos metropolis by the researcher.
Target respondents for this study are the principal actors in the construction industry namely: the Client, the Consultant and the Contractor.
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EVALUATING THE BENEFITS AND DRAWBACKS OF USING COMPOSITE MATERIALS IN AIRCRAFT MANUFACTURING COMPARED TO ALUMINIUM
Abstract:
The utilization of composite materials in aircraft manufacturing has garnered significant attention in recent decades due to their potential to offer improved performance, fuel efficiency, and durability compared to traditional aluminum alloys. This paper aims to evaluate the benefits and drawbacks of employing composite materials in aircraft manufacturing as opposed to aluminum. Through a comprehensive review of existing literature, this study explores the mechanical properties, weight savings, corrosion resistance, manufacturing processes, and environmental impacts associated with both composite materials and aluminum in the context of aircraft construction. Additionally, the economic considerations, including initial costs, maintenance expenses, and lifecycle analysis, will be examined to provide a holistic assessment of the feasibility and practicality of adopting composite materials in the aviation industry. By critically analyzing the advantages and challenges of each material, this research seeks to contribute to the ongoing discourse on material selection in aircraft manufacturing and offer insights into the future direction of aerospace engineering.
Table of Contents:
Introduction
1.1 Background
1.2 Statement of the Problem
1.3 Research Objectives
1.4 Scope of the Study
Literature Review
2.1 Overview of Composite Materials in Aircraft Manufacturing
2.2 Properties of Composite Materials vs. Aluminum Alloys
2.3 Weight Savings and Structural Performance
2.4 Corrosion Resistance and Durability
2.5 Manufacturing Processes and Techniques
2.6 Environmental Considerations
Comparison of Composite Materials and Aluminum
3.1 Mechanical Properties
3.2 Weight Reduction and Fuel Efficiency
3.3 Corrosion Resistance and Maintenance
3.4 Manufacturing Complexity and Costs
3.5 Environmental Impact
Economic Analysis
4.1 Initial Costs and Return on Investment
4.2 Operational Expenses and Maintenance Costs
4.3 Lifecycle Analysis and Total Cost of Ownership
Conclusion
5.1 Summary of Findings
5.2 Implications for Aircraft Manufacturing
5.3 Recommendations for Future Research
References
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EVALUATING THE BENEFITS AND DRAWBACKS OF USING COMPOSITE MATERIALS IN AIRCRAFT MANUFACTURING COMPARED TO ALUMINIUM
Abstract:
Disaster management plays a crucial role in safeguarding lives, protecting property, and ensuring the resilience of communities in the face of natural and man-made disasters. In Nigeria, the National Emergency Management Agency (NEMA) serves as the primary institution responsible for coordinating disaster response and mitigation efforts across the country. This paper provides a comprehensive appraisal of NEMA’s role and effectiveness in disaster management within the Nigerian context.
The appraisal begins with an overview of the historical evolution of NEMA, tracing its establishment and subsequent evolution in response to the growing challenges posed by disasters in Nigeria. The paper examines NEMA’s mandate, organizational structure, and key responsibilities in disaster preparedness, response, recovery, and mitigation.
Drawing upon empirical data and case studies, the appraisal evaluates NEMA’s performance in disaster management, highlighting both successes and challenges encountered in its operations. Factors contributing to NEMA’s effectiveness, such as collaboration with other stakeholders, capacity-building initiatives, and technological advancements, are analyzed alongside systemic constraints and areas for improvement.
Furthermore, the paper explores the socio-economic and environmental factors shaping the landscape of disaster management in Nigeria, including rapid urbanization, climate change, socio-political instability, and resource constraints. The impact of these factors on NEMA’s operational capacity and the overall resilience of Nigerian communities is critically examined.
Through a comparative analysis of NEMA’s practices with international standards and best practices in disaster management, the paper identifies lessons learned and opportunities for enhancing NEMA’s effectiveness and efficiency. Recommendations are provided for policy-makers, practitioners, and stakeholders to strengthen NEMA’s institutional capacity, improve coordination mechanisms, and enhance community resilience to disasters in Nigeria.
In conclusion, this appraisal offers valuable insights into the role of NEMA and the broader landscape of disaster management in Nigeria. By critically examining NEMA’s performance and identifying areas for improvement, this paper contributes to ongoing efforts to build a more resilient and disaster-ready nation, capable of effectively addressing the multifaceted challenges of disaster risk reduction and response in the 21st century.
Chapter 1: Introduction
Background of the Study
Statement of the Problem
Objectives of the Study
Scope and Limitations
Significance of the Study
Definition of Terms
Chapter 2: Literature Review
Overview of Aircraft Manufacturing Materials
Properties of Aluminum in Aircraft Construction
Properties of Composite Materials in Aircraft Construction
Advantages of Composite Materials over Aluminum
Disadvantages of Composite Materials compared to Aluminum
Previous Studies and Research in Aircraft Material Selection
Chapter 3: Methodology
Research Design
Data Collection Methods
Sampling Techniques
Data Analysis Procedures
Operational Definitions of Variables
Limitations of the Study
Chapter 4: Comparative Analysis of Composite Materials and Aluminum in Aircraft Manufacturing
Strength-to-Weight Ratio Comparison
Durability and Fatigue Characteristics
Manufacturing Costs and Processes
Maintenance and Repair Considerations
Environmental Impact and Sustainability
Case Studies of Aircraft Models Using Composite Materials and Aluminum
Chapter 5: Discussion and Conclusion
Summary of Findings
Implications of the Study
Recommendations for Aircraft Manufacturers
Future Research Directions
Conclusion and Closing Remarks
References.
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]]>BEFORE YOU READ THE ABSTRACT OR CHAPTER ONE OF THE PROJECT TOPICS BELOW, PLEASE READ THE INFORMATION BELOW.THANK YOU!
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IMPLEMENTATION OF LEAN MANUFACTURING PRINCIPLES IN A PRODUCTION FACILITY
ABSTRACT
The immediate impact of the economic downturn and challenging market condition on manufacturing companies and businesses is an urgent demand to implement the effective resource utilization and processing system that will improve productivity. Effective adaptation to the highly competitive environment entails integrating different thought concepts and inventive ideas into the manufacturing companies processes to reduce manufacturing costs, wastes and improve quality. This paper explores the use of lean concept in COMPANIES to improve productivity by reducing operator motion distances, processing time and cost of energy supply. The project reviewed productivity improvement opportunities in Campus bread factory Nsukka using lean principle. The problems in the existing layout were carefully delineated through direct observation of production processes and detailed work study. The resulting data were analyzed to enable the proposal of pertinent modifications in the process. When compared with the existing methods, the new developed method revealed at least 15.62% reduction opportunity in the distance travelled by the operator and decreased the process time by 13.09%. The results also showed that 35.99% reduction of cost of power generation is achievable. A new layout is proposed based on the research realities.
TABLE OF CONTENTS
CERTIFICATION PAGE
DEDICATION
ACKNOWLEDGEMENT
ABSTRACT
TABLE OF CONTENTS
INTRODUCTION
REVIEW OF RELATED LITERATURE
CHAPTER THREE
DATA COLLECTION PRESENTATION AND ANALYSIS
CHAPTER FIVE
5.1 CONCLUSION
5.2 DISCUSSION
5.3 REFERENCES
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EVALUATING THE BENEFITS AND DRAWBACKS OF USING COMPOSITE MATERIALS IN AIRCRAFT MANUFACTURING COMPARED TO ALUMINIUM
Abstract:
Disaster management plays a crucial role in safeguarding lives, protecting property, and ensuring the resilience of communities in the face of natural and man-made disasters. In Nigeria, the National Emergency Management Agency (NEMA) serves as the primary institution responsible for coordinating disaster response and mitigation efforts across the country. This paper provides a comprehensive appraisal of NEMA’s role and effectiveness in disaster management within the Nigerian context.
The appraisal begins with an overview of the historical evolution of NEMA, tracing its establishment and subsequent evolution in response to the growing challenges posed by disasters in Nigeria. The paper examines NEMA’s mandate, organizational structure, and key responsibilities in disaster preparedness, response, recovery, and mitigation.
Drawing upon empirical data and case studies, the appraisal evaluates NEMA’s performance in disaster management, highlighting both successes and challenges encountered in its operations. Factors contributing to NEMA’s effectiveness, such as collaboration with other stakeholders, capacity-building initiatives, and technological advancements, are analyzed alongside systemic constraints and areas for improvement.
Furthermore, the paper explores the socio-economic and environmental factors shaping the landscape of disaster management in Nigeria, including rapid urbanization, climate change, socio-political instability, and resource constraints. The impact of these factors on NEMA’s operational capacity and the overall resilience of Nigerian communities is critically examined.
Through a comparative analysis of NEMA’s practices with international standards and best practices in disaster management, the paper identifies lessons learned and opportunities for enhancing NEMA’s effectiveness and efficiency. Recommendations are provided for policy-makers, practitioners, and stakeholders to strengthen NEMA’s institutional capacity, improve coordination mechanisms, and enhance community resilience to disasters in Nigeria.
In conclusion, this appraisal offers valuable insights into the role of NEMA and the broader landscape of disaster management in Nigeria. By critically examining NEMA’s performance and identifying areas for improvement, this paper contributes to ongoing efforts to build a more resilient and disaster-ready nation, capable of effectively addressing the multifaceted challenges of disaster risk reduction and response in the 21st century.
Chapter 1: Introduction
Background of the Study
Statement of the Problem
Objectives of the Study
Scope and Limitations
Significance of the Study
Definition of Terms
Chapter 2: Literature Review
Overview of Aircraft Manufacturing Materials
Properties of Aluminum in Aircraft Construction
Properties of Composite Materials in Aircraft Construction
Advantages of Composite Materials over Aluminum
Disadvantages of Composite Materials compared to Aluminum
Previous Studies and Research in Aircraft Material Selection
Chapter 3: Methodology
Research Design
Data Collection Methods
Sampling Techniques
Data Analysis Procedures
Operational Definitions of Variables
Limitations of the Study
Chapter 4: Comparative Analysis of Composite Materials and Aluminum in Aircraft Manufacturing
Strength-to-Weight Ratio Comparison
Durability and Fatigue Characteristics
Manufacturing Costs and Processes
Maintenance and Repair Considerations
Environmental Impact and Sustainability
Case Studies of Aircraft Models Using Composite Materials and Aluminum
Chapter 5: Discussion and Conclusion
Summary of Findings
Implications of the Study
Recommendations for Aircraft Manufacturers
Future Research Directions
Conclusion and Closing Remarks
References.
HOW TO RECEIVE PROJECT MATERIAL (S)
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BANK ACCOUNTS
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OR
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Account Number: 3139283609
Bank: FIRST BANK
FOR MORE INFORMATION, CALL:
08068231953 or 08168759420
]]>BEFORE YOU READ THE ABSTRACT OR CHAPTER ONE OF THE PROJECT TOPICS BELOW, PLEASE READ THE INFORMATION BELOW.THANK YOU!
INFORMATION:
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CARBON FIBRE LAMINATES WITH ENGINEERED FRACTURE BEHAVIOUR
A new bio-inspired microstructure design approach was developed to improve the translaminar toughness and damage tolerance of Carbon Fibre Reinforced Plastic (CFRP) structures. The microstructure designs take inspiration from the microstructures of biological composites by adopting the most important toughening mechanisms, and applying them to CFRP laminates. Carefully placed patterns of laser-engraved micro-cuts are inserted in the microstructure of the laminate during the manufacturing process. These micro-cuts change the crack propagation path during translaminar fracture, hence allowing to engineer the fracture behaviour of the composite. The microstructure design approach led to remarkable improvements in the maximum tensile load (up to 189%) and translaminar work of fracture (up to 460%) during Compact Tension test for CFRP laminates with Cross-Ply and Quasi-Isotropic (QI) layups when compared with the corresponding un-modified laminates. Furthermore, a significant improvement in the damage resistance under indentation test was demonstrated for a QI laminate with engineered microstructure. These results demonstrate that microstructure design holds the potential to improve the damage tolerance of CFRP structures in industrially-relevant applications. A semi-analytical Fibre Bundle Model (FBM) was developed to investigate the role of dynamic stress concentrations, and of fracture mechanics-driven failure, on the longitudinal tensile strength of fibre-reinforced composites. In particular, the investigation was focused on the size effect: a decrease in the bundle strength with an increase in the number of fibres. To the knowledge of the author, it is the first attempt in the literature to investigate these two physical mechanisms in a FBM. It was shown that, although the dynamic stress concentrations significantly decrease the predicted bundle strength, do not allow to predict the right trend of the size effect shown by the experimental results. On the contrary, including fracture mechanics-driven failure in the bundle simulation allowed to predict the right trend of the size effects on the bundle strength. These results suggest that fracture mechanics is a physical mechanism which might be necessary to consider to correctly predict the longitudinal tensile strength in large composite bundles.
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BOUNDARY LAYER RECEPTIVITY TO FREESTREAM DISTURBANCES
Transition of fluid flow from a laminar to turbulent state has been studied extensively for over a century, beginning with experiments carried out by Osborne Reynolds in 1883. Theoretical, experimental and numerical techniques have advanced and ever more accurate measurements of the transition process have taken place; however, there still remains much to understand regarding the origins of boundary-layer instabilities – in other words, the ‘receptivity’ of the boundary layer to initial perturbations. The present work considers experimentally the receptivity process for the Blasius boundary layer formed over a flat plate at zero incidence. Two types of interaction are studied, both forced by a two-dimensional harmonic disturbance within the freestream. The first considers the receptivity of the boundary layer to the excitation of Tollmien-Schlichting waves at localised roughness while the second considers the excitation of streaky structures within the boundary layer at high-amplitudes of the freestream forcing. Two-dimensional Tollmien-Schlichting waves are shown to be excited only in the presence of a roughness element placed on the plate surface. Results of previous experiments regarding Tollmien-Schlichting wave excitation at localised roughness are corroborated and theoretical works are further validated. Although the forcing does not resemble the ‘optimal perturbations’ for exciting streaks within boundary layers, it is found that streaks are excited within the boundary layer for forcing amplitudes in excess of 0.5% and their growth and characteristics are found and compared with other experimental and theoretical results. It is shown that TS waves, once excited, cause transition at much smaller amplitudes but that they are noticeably more difficult to excite than streaks within the boundary layer.
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BOUNDARY ELEMENT PLATE FORMULATIONS FOR DYNAMIC FRACTURE AND ULTRASONIC GUIDED-WAVE STRUCTURAL HEALTH MONITORING
In this thesis, new boundary element formulations based on first-order plate theories are developed for dynamic fracture problems and Lamb-wave based structural health monitoring. The boundary integral equations are formulated in the complex frequency domain (Laplace-transform domain), which avoids domain integrals due to the inertial terms. In these plate formulations, only line elements are required for the discretization of membrane and bending problems. The dual boundary element method (DBEM) provides a general and computationally efficient way to model cracks. A new boundary element formulation for the Kane-Mindlin theory, a first-order theory for extensional motion of plates, is proposed for modelling the fundamental symmetric (S0) Lamb wave mode. The formulation is demonstrated to enable efficient and accurate modelling of the S0 mode over a wide frequency range. New fundamental solutions for such formulation are derived for the first time. The above-mentioned formulation is extended to a dual boundary element formulation to solve dynamic crack problems. The traction boundary integral equation utilized for this dual formulation is derived for the first time as well as their corresponding fundamental solutions. An out-of-plane fracture mode and the influence of plate thickness on dynamic stress intensity factors are analysed using such formulation, and the studies of the S0-mode wave scattering by a crack are also carried out. The cracked plate structures subjected to dynamic bending loads are investigated using a new Laplace-transform dual boundary element formulation which is developed for the Mindlin theory, a first-order shear deformable plate theory. The singular behaviours of the Laplace-transform fundamental solutions are re-examined and corrected. The dynamic fracture analysis of Mindlin plates is carried out using this formulation, which also allows to analyse the interaction between the fundamental antisymmetric Lamb wave (A0 mode) and the crack. The original fundamental solutions are modified slightly to represent the dispersion characteristic of the A0 mode more accurately. Piezoelectric actuators and sensors are incorporated into the above-mentioned boundary element plate formulations to simulate the Lamb wave excitation and sensing respectively, which provides an alternative numerical tool for the Lamb-wave based structural health monitoring (SHM). A new actuator model, called an equivalent pin-force model, is proposed, which makes the numerical implementation efficient and simple. This BEM model is able to provide data accurately and efficiently as input for damage detection algorithms to localize crack in a plate. Three-dimensional finite element simulation and experiments are carried out to validate the BEM-simulated results. Finally, spectral elements are introduced into a two-dimensional Laplace-transform BEM to solve high-frequency elastodynamic problems. It is shown that the computational efficiency can be improved significantly using the spectral elements, which indicates that it is well worth introducing the spectral elements into the proposed boundary element plate formulations for ultrasonic guided-wave SHM applications in the future.
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After paying the appropriate amount (#5,000) into our bank Account below, send the following information to
08068231953 or 08168759420
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Account Name: AMUTAH DANIEL CHUKWUDI
Account Number: 0046579864
Bank: GTBank.
OR
Account Name: AMUTAH DANIEL CHUKWUDI
Account Number: 3139283609
Bank: FIRST BANK
FOR MORE INFORMATION, CALL:
08068231953 or 08168759420
BEFORE YOU READ THE ABSTRACT OR CHAPTER ONE OF THE PROJECT TOPICS BELOW, PLEASE READ THE INFORMATION BELOW.THANK YOU!
INFORMATION:
YOU CAN GET THE COMPLETE PROJECT OF THE TOPIC BELOW. THE FULL PROJECT COST N5,000 ONLY. THE FULL INFORMATION ON HOW TO PAY AND GET THE COMPLETE PROJECT IS AT THE BOTTOM OF THIS PAGE. OR
YOU CAN CALL: 08068231953, 08137701720
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BOUNDARY ELEMENT METHODS FOR COHESIVE THERMO-MECHANICAL DAMAGE AND MICRO-CRACKING EVOLUTION
In this thesis, Boundary Element Methods (BEM) are developed for micro-mechanic cohesive non linear problems. Modelling of intergranular and transgranular damage and micro-cracking evolution in polycrystalline materials is presented for different physical engineering problems and loading conditions: mechanical and thermo-mechanical applications are considered in the context of micromechanics. Throughout the thesis the different models are based on a multi-region boundary element approach combined with the dual boundary element formulation. The polycrystalline microstructures are generated with Voronoi tessellations, which well represent statistically the morphology of multi-grain materials; the formulation is able to consider the stochastic effect of each grain’s crystal anisotropy within the whole aggregate. Linear cohesive laws are used for assessing initiation and propagation of damage on intergranular and transgranular surfaces; moreover different physical assumptions on the cohesive models are investigated in order to guarantee energetic independence between mode I and II of fracture as well as inter- and trans-granular damage. Transgranular surfaces are introduced during the numerical simulation, so that the benefits of BEM are maintained and any internal damage propagation is not affected by initial discretization: the nucleation is based on a stress criterion. Upon cohesive failure, non linear frictional contact analysis is introduced. The effect of thermal loading is then introduced to model stress generation and damage propagation due to steady state and transient thermal loading. The cohesive model is updated to take into account the new thermal fields. Damage dependent Fourier’s law is implemented to model cohesive surfaces as heat barriers. Investigations on the effect of grain size, critical fracture energies and loading conditions are done. The presented formulations are shown to provide efficient modelling of the aforementioned engineering applications and their accuracy is compared throughout the thesis with analytical, numerical and experimental findings, where available.
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After paying the appropriate amount (#5,000) into our bank Account below, send the following information to
08068231953 or 08168759420
(1) Your project topics
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(3) Payment Name
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Account Name: AMUTAH DANIEL CHUKWUDI
Account Number: 0046579864
Bank: GTBank.
OR
Account Name: AMUTAH DANIEL CHUKWUDI
Account Number: 3139283609
Bank: FIRST BANK
FOR MORE INFORMATION, CALL:
08068231953 or 08168759420