This document reports on a stress analysis of the sun gear and shaft of a harmonic planetary gear assembly conducted by a student. The assembly was modeled in Inventor software and analyzed under varying loads from 15kN to 25kN. Stress results were recorded and graphs were produced to identify critical stress zones and ensure the design can withstand operational loads. The relationship between stress and load was found to be proportional, meeting design assumptions. Recommendations were made to improve the design based on stress concentrations found.
Eric Schulken's engineering portfolio contains 6 projects demonstrating his skills in various areas including simulation, drafting, 3D modeling, technical writing and automation. The first project involves simulating a vehicle path planning method using MATLAB. The second is designing a dual function gripper for picking and placing lenses in Solidworks. The third is a CAD mockup of an automation cell layout. The fourth is an MRP scheduling tool built in Excel. The fifth analyzes surface area contamination using image analysis. The sixth writing sample details methods for measuring rowing power output using accelerometers on an ergometer.
This document discusses D'Alembert's principle and Klien's construction method for analyzing dynamic forces and determining velocity and acceleration in machines. It contains the following key points:
1) D'Alembert's principle states that a moving body can be analyzed as if in static equilibrium by introducing an inertia force equal and opposite to the product of mass and acceleration. This allows dynamic problems to be analyzed as static problems.
2) Klien's construction uses similar triangles to determine velocity and acceleration diagrams for reciprocating parts in engines without separate diagrams. It graphs velocity and acceleration vectors based on crank position.
3) Klien's acceleration diagram specifically graphs radial and tangential acceleration components of
This document discusses Ritterhaus's construction and Klein's acceleration diagram for analyzing the velocity and acceleration of reciprocating parts in engines. It explains how to use Ritterhaus's construction to draw the velocity diagram triangle OCM and acceleration diagram quadrilateral CQNO. These diagrams allow analysis of the velocity and acceleration of a point on the piston based on its position along the line of stroke.
This document discusses Bennett's construction and Klein's acceleration diagram for analyzing the velocity and acceleration of reciprocating parts in engines. It contains the following key points:
1) Bennett's construction involves drawing perpendicular lines from various positions of the crank and connecting rod to analyze velocity.
2) Klein's acceleration diagram is similar to Bennett's and involves drawing perpendicular lines to analyze acceleration.
3) Bennett's construction results in a velocity diagram, while Klein's produces an acceleration diagram, both of which are used to study reciprocating motion in engines.
This document discusses vehicle testing and data analysis for aerodynamic parameters. It begins with introductions to key aerodynamic principles like drag, lift, and boundary layer separation. It then describes the methodology for simulator testing of different wing angles of attack. Results and analysis are presented on coefficients of drag, lift, and lap performance for varying setups. The document concludes with recommendations for wing parameters and directions for further work.
This document summarizes two computational studies of flow over an Ahmed body, a simplified car model. Case study 1 compares RANS and hybrid RANS-LES turbulence models in simulations of 25 and 35 degree rear slant angles. It finds that hybrid models overpredict drag coefficient compared to experiments. Case study 2 describes a grid-dependence study of three mesh sizes to accurately predict drag coefficient, finding the medium grid provides the best balance of accuracy and computational cost. The document concludes the Ahmed body is a useful benchmark for studying vehicle aerodynamics and quantifying drag, with rear slant angle being a major factor influencing overall drag coefficient.
This document summarizes a numerical study of airflow over an Ahmed body using RANS turbulence models. It finds that the k-ε-v2 model more accurately predicts separation and reattachment compared to other models. The study simulates flow over an Ahmed body with a 35 degree rear angle using various turbulence models and investigates the effects of grid layout and differencing schemes on the results. Numerical results agree well with experimental data on the wake structure and turbulent kinetic energy distribution behind the body.
SAIF ALDIN ALI MADIN
سيف الدين علي ماضي
S96aif@gmail.com
Torsion tesd
MECHANICS OF MATERIALS
The objective of this experiment is to study the linearly elastic behavior
of metallic material under a torsion test. Torsion test measures the
strength of any material against maximum twisting forces. During this
experiment, a failure testing is done to our testing material which is a
steel. This failure testing involves twisting the material until it breaks
which helps demonstrates how materials undergo during testing
condition by measuring the applied torque with respect to the angle of
twist, the shear modulus, shear stress
At the limit of proportionality. The shear modulus of elasticity G and
Poisson's Ratio are determined for the specimen using torsional stressstrain relationship from the data collected during the experiment. The
fraction surface of our material at the end of the experiment is used to
stablish characteristics of the material,
Eric Schulken's engineering portfolio contains 6 projects demonstrating his skills in various areas including simulation, drafting, 3D modeling, technical writing and automation. The first project involves simulating a vehicle path planning method using MATLAB. The second is designing a dual function gripper for picking and placing lenses in Solidworks. The third is a CAD mockup of an automation cell layout. The fourth is an MRP scheduling tool built in Excel. The fifth analyzes surface area contamination using image analysis. The sixth writing sample details methods for measuring rowing power output using accelerometers on an ergometer.
This document discusses D'Alembert's principle and Klien's construction method for analyzing dynamic forces and determining velocity and acceleration in machines. It contains the following key points:
1) D'Alembert's principle states that a moving body can be analyzed as if in static equilibrium by introducing an inertia force equal and opposite to the product of mass and acceleration. This allows dynamic problems to be analyzed as static problems.
2) Klien's construction uses similar triangles to determine velocity and acceleration diagrams for reciprocating parts in engines without separate diagrams. It graphs velocity and acceleration vectors based on crank position.
3) Klien's acceleration diagram specifically graphs radial and tangential acceleration components of
This document discusses Ritterhaus's construction and Klein's acceleration diagram for analyzing the velocity and acceleration of reciprocating parts in engines. It explains how to use Ritterhaus's construction to draw the velocity diagram triangle OCM and acceleration diagram quadrilateral CQNO. These diagrams allow analysis of the velocity and acceleration of a point on the piston based on its position along the line of stroke.
This document discusses Bennett's construction and Klein's acceleration diagram for analyzing the velocity and acceleration of reciprocating parts in engines. It contains the following key points:
1) Bennett's construction involves drawing perpendicular lines from various positions of the crank and connecting rod to analyze velocity.
2) Klein's acceleration diagram is similar to Bennett's and involves drawing perpendicular lines to analyze acceleration.
3) Bennett's construction results in a velocity diagram, while Klein's produces an acceleration diagram, both of which are used to study reciprocating motion in engines.
This document discusses vehicle testing and data analysis for aerodynamic parameters. It begins with introductions to key aerodynamic principles like drag, lift, and boundary layer separation. It then describes the methodology for simulator testing of different wing angles of attack. Results and analysis are presented on coefficients of drag, lift, and lap performance for varying setups. The document concludes with recommendations for wing parameters and directions for further work.
This document summarizes two computational studies of flow over an Ahmed body, a simplified car model. Case study 1 compares RANS and hybrid RANS-LES turbulence models in simulations of 25 and 35 degree rear slant angles. It finds that hybrid models overpredict drag coefficient compared to experiments. Case study 2 describes a grid-dependence study of three mesh sizes to accurately predict drag coefficient, finding the medium grid provides the best balance of accuracy and computational cost. The document concludes the Ahmed body is a useful benchmark for studying vehicle aerodynamics and quantifying drag, with rear slant angle being a major factor influencing overall drag coefficient.
This document summarizes a numerical study of airflow over an Ahmed body using RANS turbulence models. It finds that the k-ε-v2 model more accurately predicts separation and reattachment compared to other models. The study simulates flow over an Ahmed body with a 35 degree rear angle using various turbulence models and investigates the effects of grid layout and differencing schemes on the results. Numerical results agree well with experimental data on the wake structure and turbulent kinetic energy distribution behind the body.
SAIF ALDIN ALI MADIN
سيف الدين علي ماضي
S96aif@gmail.com
Torsion tesd
MECHANICS OF MATERIALS
The objective of this experiment is to study the linearly elastic behavior
of metallic material under a torsion test. Torsion test measures the
strength of any material against maximum twisting forces. During this
experiment, a failure testing is done to our testing material which is a
steel. This failure testing involves twisting the material until it breaks
which helps demonstrates how materials undergo during testing
condition by measuring the applied torque with respect to the angle of
twist, the shear modulus, shear stress
At the limit of proportionality. The shear modulus of elasticity G and
Poisson's Ratio are determined for the specimen using torsional stressstrain relationship from the data collected during the experiment. The
fraction surface of our material at the end of the experiment is used to
stablish characteristics of the material,
The document is an assignment submitted by a student for a course in computer applications in geological engineering. It contains 8 chapters analyzing different aspects of slope stability, geological structures, weathering processes, and soil deposits. The assignment involves determining the failure mode of a slope using stereonet analysis, discussing the contributions of engineering geologists, and outlining investigation stages and engineering problems associated with different soil types. Diagrams, tables and references are included.
The document is a project report on parametric design and optimization of propellers using Grasshopper. It discusses using Grasshopper to build a parametric model of the Wageningen B-screw propeller series. The report reviews literature on ship propellers and propulsion. It then analyzes the geometry and performance characteristics of the Wageningen B-screw series. The main body of the report describes realizing a parametric model of the propeller series in Grasshopper that allows modifying the geometry and calculating performance based on parameters. The model is then tested and potential further work is discussed.
Modeling and Structural Analysis of a Wing [FSI ANSYS&MATLAB]BahaaIbrahim10
MODELING AND STRUCTURAL ANALYSIS OF A WING
WITH HISTORICAL PERSPECTIVE.
In our study, analyzing aircraft’s wing with the old assumptions will not give an exact solution but
this solution (total deformation) changes according to the geometry of the cross-section of the beam, so
the total deformation of the beam may be greater or lower than the exact solution. In these two cases,
the solution is not acceptable as in the first case which the deformation is greater than the exact solution
will make more weight and cost, and Engineers design aircraft at minimum weight and less cost. But in
the second case which will make lower deformation than exact solution will be much risky as the aircraft
could be fail at any time, and this case much dangerous because it threatens life of people.
The document summarizes the design of a two-stage planetary gearbox with an overall gear ratio of 10:1 for a 1 HP 3600 RPM NEMA C face motor. Key aspects of the design include:
- Choosing a modular value of 1 and ring gear diameter of 160mm for the first stage.
- Calculating gear ratios, sizes, and speeds for each stage using standard gear equations.
- Performing stress analysis, force calculations, and shaft/bearing design using equations from references.
- Creating 3D CAD models and performing FEA in SolidWorks to validate stress calculations and ensure proper function.
- Producing engineering drawings of the design for manufacturing.
The analytical
This thesis investigates noise from a lift-offset coaxial helicopter configuration using computational modeling. Key findings include:
- Constructive and destructive interference occurs for coaxial thickness noise depending on observer location.
- Blade crossings and blade-vortex interactions are important sources of coaxial loading noise.
- Coaxial thickness noise is generally lower than a single rotor helicopter, especially at forward flight speeds.
- Reducing rotor tip speed through lower RPM provides significant noise reduction potential for coaxial rotors.
- Alternative blade designs like dual-swept tips and curved sweeping can further reduce coaxial thickness noise.
Final thesis numerical simulation of gyroscopic effects in ansys 11.10Akashdeep Brijpuriya
This master's thesis examines the numerical simulation of gyroscopic effects in ANSYS. Natural frequency and transient response analyses are performed in ANSYS on a simple rotor model and the results are verified with analytical solutions. The structural response of a floating wind turbine is also analyzed, comparing parked and operational conditions. While gyroscopic effects introduce additional forces and vibrations in the wind turbine tower, these forces are much smaller than those generated by wave motion. The tendencies observed in the thesis are consistent with previous research.
This document presents the design and analysis of a scramjet engine. The author uses quasi-one-dimensional equations to model the compressible flow and combustion within the engine. Performance is estimated using computational modeling of the inlet, combustor, and nozzle. Initial results show a thrust of nearly 405 kN and specific impulse of 174 seconds. Further analysis of the combustion chamber and boundary layers is recommended.
This thesis aims to expand an existing pneumatic breaker model created in Dymola to include additional interacting systems using Hopsan NG simulation software. The author builds Hopsan models of the breaker with both fixed and floating hitting points. Validation is done by comparing model results to measurements from the real breaker and Dymola simulations. The Hopsan models are able to analyze factors like feed force on the operator and vibrations transmitted, improving understanding of the breaker's internal processes.
This document presents a numerical lifting line model and blade element model to model the aerodynamic effects of a propeller slipstream on a finite wing. The lifting line model uses a numerical vortex lattice method to predict lift distributions across a wing based on 2D airfoil data and known upstream flow conditions. The blade element model uses momentum theory and blade element analysis to model propeller performance and generate upstream velocity profiles. The combined models are expected to be useful for modeling tail-sitting VTOL aircraft where the propeller slipstream affects wing performance. Results are presented comparing the models to experimental data.
The document is a thesis report submitted by Ng Jun Jie to the Department of Mechanical Engineering at the National University of Singapore in partial fulfillment of the requirements for a Bachelor of Engineering degree. The report analyzes and aims to improve the jacking systems used for lifting offshore jack-up rigs by studying the fatigue life of the rack and pinion mechanism and proposing ways to reduce stress through modeling and simulation.
Development of controller for electric racing motorcycleShih Cheng Tung
Globally, electric motors are considered to be one of the solutions that could reduce environmental issues. Numerous applications involve electric motors, for example, electric and hybrid vehicles. In order to increase the stability and efficiency of applications, there has been a growing development of controllers for electric motors. In addition, electric motors could provide high reliability and power density in collaboration with the appropriate controller. Thus, it is essential to develop a dedicated control system for high-performance vehicles such as an electric racing motorcycle. This project focuses on the torque control system for an electric racing motorcycle that will allow it to reach the maximum performance of acceleration in a straightline. However, the instantaneous torque produces a great acceleration and also increases the risk of injures, for example, back-flip of the motorcycle. In order to assist the launch of the high-powered electric motor, the torque should be regulated by the torque control system. This allows the control system to process the maximum output of powertrain in a safe amount. The electric motor is commanded by the torque control with effective methods that use an established database. Through the simulation of motorcycle acceleration models, a customised lookup table is generated. In addition, the results are compared to the performance of the human-driver and torque control. The differences will then be discussed and conclusions drawn. The torque control system will be attached to an electric racing motorcycle constructed at Kingston University for further work to complete a practical test and optimisation.
Nonlinear Simulation of Rotor-Bearing System DynamicsFrederik Budde
This document summarizes a student project investigating nonlinear dynamics of rotor-bearing systems through numerical simulation. Key points:
- Simulations are performed using a 2-DOF rigid disc model and a 72-DOF flexible rotor finite element model to analyze the effects of unbalance and initial perturbations.
- Both models exhibit subsynchronous instabilities around 0.45x and 0.5x the rotational speed due to cross-coupled bearing stiffness and unbalance-induced nonlinearity. Increasing unbalance can suppress the lower instability.
- Qualitative analysis using bifurcation diagrams, phase planes, frequency spectra and Poincaré maps characterizes various motions like quasi-periodicity and chaos, with evidence of period-dou
[Phys 6006][Ben Williams][Inertial Confinement Fusion]Ben Williams
This document summarizes Ben Williams' investigation into the parameters affecting the performance of inertial confinement fusion. Specifically, it explores gain, defined as the ratio of energy released to energy delivered, and hydrodynamic instabilities caused by imperfections in the capsule surface. The relationship between these parameters is analyzed. Classical and ablative Rayleigh-Taylor instability growth rates are derived. Plots are replicated to show the accuracy of the author's research into how factors like the in-flight aspect ratio affect instability growth and maximum gain. Reducing growth through pulse shaping techniques is also discussed.
This document contains an examination for the International General Certificate of Secondary Education in Physics. It consists of multiple choice and written response questions covering various topics in physics, including:
- Measuring the acceleration of a trolley and determining its mass.
- Calculating power ratings using pulleys and ropes.
- Pressure and volume changes of gases with depth in liquids.
- Electrical circuits and components including resistors, batteries and transformers.
- Wave properties including wavelength, frequency and speed.
- Refraction of light in optical fibers.
- Radioactive decay and half-life calculations.
- Thermionic emission in cathode ray tubes.
- Phase changes and specific heat capacity.
The exam
This thesis analyzes the effect of N2 vibrational energy on flow characteristics in high-speed flight using computational fluid dynamics (CFD). The author validates relaxation models for N2 vibrational energy transfer and compares results with and without including vibrational energy effects. A key finding is that including N2 vibrational energy shows different thermal energy redistribution over a blunt body, with significant impacts on pressure and temperature profiles.
This document presents the results of a feasibility study for upgrading the Canada-France-Hawaii Telescope (CFHT) to create a next generation CFHT (ngCFHT). The study evaluated reusing the existing telescope and enclosure structures, developed feasible optical designs including single, double, and triple mirror configurations, and a fiber-fed spectrograph. It also examined the aero-thermal performance and estimated costs. The study found that upgrading key systems is feasible and reusing the existing structures could reduce costs significantly compared to a new build. The resulting ngCFHT would provide a powerful wide-field spectroscopic facility for the next 20 years.
The document describes a numerical simulation of flow through a centrifugal pump impeller. Hassan Adel Talaat El-Sheshtawy conducted 3D CFD simulations using ANSYS/CFX to analyze the flow field and evaluate the slip factor. The simulation results agreed well with the design performance curve, especially near the best efficiency point. Several empirical slip factor correlations were compared to the numerically obtained slip factor. The effects of adding splitters and increasing the number of blades on slip factor, head rise and hydraulic efficiency were also investigated. It was found that while slip factor improved with more blades or longer splitters, hydraulic efficiency did not always increase due to additional losses.
This document is a semester thesis submitted by Jesús Ignacio Maldonado Covarrubias to ETH Zurich in June 2011. The thesis investigates the dimensioning of an access panel for the fixed leading edge of a commercial aircraft. The objectives are to analyze an initial access panel design using finite element analysis, evaluate it against criteria such as strength and stability, and perform optimizations to reduce the panel's mass. The work is broken down into tasks such as creating CAD and FE models, analyzing different stiffener configurations, and conducting a design improvement study. The document outlines the problem definition, reviews relevant literature, describes the analytical and FE modeling approaches, and presents the results and conclusions of the study.
SAIL VERSUS HULL FORM PARAMETER CONFLICTS IN YACHT DESIGNBoyang Wang
The document describes a student project that aims to analyze the influence of sail and hull form parameters on yacht performance. It will generate a series of hull forms by modifying parameters of an initial YD-40 hull. Resistance and stability of the hulls will be calculated and their performance tested using sailing simulation software for different sail configurations. The document reviews methods for hull form modification, section mapping, resistance prediction, and stability analysis that will be used in the project.
The document describes a project to improve region transition for a 5 MW floating offshore wind turbine using simulation. The goal is to reduce power losses and loads during transition between operating regions caused by changes in wind speed. Two approaches are tested: modifying platform motion control using individual blade pitching; and changing the generator torque trajectory. The best results come from a linearized torque trajectory, reducing transition time by 80-90% and increasing energy capture. A combined controller further improves performance within the transition region.
The document is an assignment submitted by a student for a course in computer applications in geological engineering. It contains 8 chapters analyzing different aspects of slope stability, geological structures, weathering processes, and soil deposits. The assignment involves determining the failure mode of a slope using stereonet analysis, discussing the contributions of engineering geologists, and outlining investigation stages and engineering problems associated with different soil types. Diagrams, tables and references are included.
The document is a project report on parametric design and optimization of propellers using Grasshopper. It discusses using Grasshopper to build a parametric model of the Wageningen B-screw propeller series. The report reviews literature on ship propellers and propulsion. It then analyzes the geometry and performance characteristics of the Wageningen B-screw series. The main body of the report describes realizing a parametric model of the propeller series in Grasshopper that allows modifying the geometry and calculating performance based on parameters. The model is then tested and potential further work is discussed.
Modeling and Structural Analysis of a Wing [FSI ANSYS&MATLAB]BahaaIbrahim10
MODELING AND STRUCTURAL ANALYSIS OF A WING
WITH HISTORICAL PERSPECTIVE.
In our study, analyzing aircraft’s wing with the old assumptions will not give an exact solution but
this solution (total deformation) changes according to the geometry of the cross-section of the beam, so
the total deformation of the beam may be greater or lower than the exact solution. In these two cases,
the solution is not acceptable as in the first case which the deformation is greater than the exact solution
will make more weight and cost, and Engineers design aircraft at minimum weight and less cost. But in
the second case which will make lower deformation than exact solution will be much risky as the aircraft
could be fail at any time, and this case much dangerous because it threatens life of people.
The document summarizes the design of a two-stage planetary gearbox with an overall gear ratio of 10:1 for a 1 HP 3600 RPM NEMA C face motor. Key aspects of the design include:
- Choosing a modular value of 1 and ring gear diameter of 160mm for the first stage.
- Calculating gear ratios, sizes, and speeds for each stage using standard gear equations.
- Performing stress analysis, force calculations, and shaft/bearing design using equations from references.
- Creating 3D CAD models and performing FEA in SolidWorks to validate stress calculations and ensure proper function.
- Producing engineering drawings of the design for manufacturing.
The analytical
This thesis investigates noise from a lift-offset coaxial helicopter configuration using computational modeling. Key findings include:
- Constructive and destructive interference occurs for coaxial thickness noise depending on observer location.
- Blade crossings and blade-vortex interactions are important sources of coaxial loading noise.
- Coaxial thickness noise is generally lower than a single rotor helicopter, especially at forward flight speeds.
- Reducing rotor tip speed through lower RPM provides significant noise reduction potential for coaxial rotors.
- Alternative blade designs like dual-swept tips and curved sweeping can further reduce coaxial thickness noise.
Final thesis numerical simulation of gyroscopic effects in ansys 11.10Akashdeep Brijpuriya
This master's thesis examines the numerical simulation of gyroscopic effects in ANSYS. Natural frequency and transient response analyses are performed in ANSYS on a simple rotor model and the results are verified with analytical solutions. The structural response of a floating wind turbine is also analyzed, comparing parked and operational conditions. While gyroscopic effects introduce additional forces and vibrations in the wind turbine tower, these forces are much smaller than those generated by wave motion. The tendencies observed in the thesis are consistent with previous research.
This document presents the design and analysis of a scramjet engine. The author uses quasi-one-dimensional equations to model the compressible flow and combustion within the engine. Performance is estimated using computational modeling of the inlet, combustor, and nozzle. Initial results show a thrust of nearly 405 kN and specific impulse of 174 seconds. Further analysis of the combustion chamber and boundary layers is recommended.
This thesis aims to expand an existing pneumatic breaker model created in Dymola to include additional interacting systems using Hopsan NG simulation software. The author builds Hopsan models of the breaker with both fixed and floating hitting points. Validation is done by comparing model results to measurements from the real breaker and Dymola simulations. The Hopsan models are able to analyze factors like feed force on the operator and vibrations transmitted, improving understanding of the breaker's internal processes.
This document presents a numerical lifting line model and blade element model to model the aerodynamic effects of a propeller slipstream on a finite wing. The lifting line model uses a numerical vortex lattice method to predict lift distributions across a wing based on 2D airfoil data and known upstream flow conditions. The blade element model uses momentum theory and blade element analysis to model propeller performance and generate upstream velocity profiles. The combined models are expected to be useful for modeling tail-sitting VTOL aircraft where the propeller slipstream affects wing performance. Results are presented comparing the models to experimental data.
The document is a thesis report submitted by Ng Jun Jie to the Department of Mechanical Engineering at the National University of Singapore in partial fulfillment of the requirements for a Bachelor of Engineering degree. The report analyzes and aims to improve the jacking systems used for lifting offshore jack-up rigs by studying the fatigue life of the rack and pinion mechanism and proposing ways to reduce stress through modeling and simulation.
Development of controller for electric racing motorcycleShih Cheng Tung
Globally, electric motors are considered to be one of the solutions that could reduce environmental issues. Numerous applications involve electric motors, for example, electric and hybrid vehicles. In order to increase the stability and efficiency of applications, there has been a growing development of controllers for electric motors. In addition, electric motors could provide high reliability and power density in collaboration with the appropriate controller. Thus, it is essential to develop a dedicated control system for high-performance vehicles such as an electric racing motorcycle. This project focuses on the torque control system for an electric racing motorcycle that will allow it to reach the maximum performance of acceleration in a straightline. However, the instantaneous torque produces a great acceleration and also increases the risk of injures, for example, back-flip of the motorcycle. In order to assist the launch of the high-powered electric motor, the torque should be regulated by the torque control system. This allows the control system to process the maximum output of powertrain in a safe amount. The electric motor is commanded by the torque control with effective methods that use an established database. Through the simulation of motorcycle acceleration models, a customised lookup table is generated. In addition, the results are compared to the performance of the human-driver and torque control. The differences will then be discussed and conclusions drawn. The torque control system will be attached to an electric racing motorcycle constructed at Kingston University for further work to complete a practical test and optimisation.
Nonlinear Simulation of Rotor-Bearing System DynamicsFrederik Budde
This document summarizes a student project investigating nonlinear dynamics of rotor-bearing systems through numerical simulation. Key points:
- Simulations are performed using a 2-DOF rigid disc model and a 72-DOF flexible rotor finite element model to analyze the effects of unbalance and initial perturbations.
- Both models exhibit subsynchronous instabilities around 0.45x and 0.5x the rotational speed due to cross-coupled bearing stiffness and unbalance-induced nonlinearity. Increasing unbalance can suppress the lower instability.
- Qualitative analysis using bifurcation diagrams, phase planes, frequency spectra and Poincaré maps characterizes various motions like quasi-periodicity and chaos, with evidence of period-dou
[Phys 6006][Ben Williams][Inertial Confinement Fusion]Ben Williams
This document summarizes Ben Williams' investigation into the parameters affecting the performance of inertial confinement fusion. Specifically, it explores gain, defined as the ratio of energy released to energy delivered, and hydrodynamic instabilities caused by imperfections in the capsule surface. The relationship between these parameters is analyzed. Classical and ablative Rayleigh-Taylor instability growth rates are derived. Plots are replicated to show the accuracy of the author's research into how factors like the in-flight aspect ratio affect instability growth and maximum gain. Reducing growth through pulse shaping techniques is also discussed.
This document contains an examination for the International General Certificate of Secondary Education in Physics. It consists of multiple choice and written response questions covering various topics in physics, including:
- Measuring the acceleration of a trolley and determining its mass.
- Calculating power ratings using pulleys and ropes.
- Pressure and volume changes of gases with depth in liquids.
- Electrical circuits and components including resistors, batteries and transformers.
- Wave properties including wavelength, frequency and speed.
- Refraction of light in optical fibers.
- Radioactive decay and half-life calculations.
- Thermionic emission in cathode ray tubes.
- Phase changes and specific heat capacity.
The exam
This thesis analyzes the effect of N2 vibrational energy on flow characteristics in high-speed flight using computational fluid dynamics (CFD). The author validates relaxation models for N2 vibrational energy transfer and compares results with and without including vibrational energy effects. A key finding is that including N2 vibrational energy shows different thermal energy redistribution over a blunt body, with significant impacts on pressure and temperature profiles.
This document presents the results of a feasibility study for upgrading the Canada-France-Hawaii Telescope (CFHT) to create a next generation CFHT (ngCFHT). The study evaluated reusing the existing telescope and enclosure structures, developed feasible optical designs including single, double, and triple mirror configurations, and a fiber-fed spectrograph. It also examined the aero-thermal performance and estimated costs. The study found that upgrading key systems is feasible and reusing the existing structures could reduce costs significantly compared to a new build. The resulting ngCFHT would provide a powerful wide-field spectroscopic facility for the next 20 years.
The document describes a numerical simulation of flow through a centrifugal pump impeller. Hassan Adel Talaat El-Sheshtawy conducted 3D CFD simulations using ANSYS/CFX to analyze the flow field and evaluate the slip factor. The simulation results agreed well with the design performance curve, especially near the best efficiency point. Several empirical slip factor correlations were compared to the numerically obtained slip factor. The effects of adding splitters and increasing the number of blades on slip factor, head rise and hydraulic efficiency were also investigated. It was found that while slip factor improved with more blades or longer splitters, hydraulic efficiency did not always increase due to additional losses.
This document is a semester thesis submitted by Jesús Ignacio Maldonado Covarrubias to ETH Zurich in June 2011. The thesis investigates the dimensioning of an access panel for the fixed leading edge of a commercial aircraft. The objectives are to analyze an initial access panel design using finite element analysis, evaluate it against criteria such as strength and stability, and perform optimizations to reduce the panel's mass. The work is broken down into tasks such as creating CAD and FE models, analyzing different stiffener configurations, and conducting a design improvement study. The document outlines the problem definition, reviews relevant literature, describes the analytical and FE modeling approaches, and presents the results and conclusions of the study.
SAIL VERSUS HULL FORM PARAMETER CONFLICTS IN YACHT DESIGNBoyang Wang
The document describes a student project that aims to analyze the influence of sail and hull form parameters on yacht performance. It will generate a series of hull forms by modifying parameters of an initial YD-40 hull. Resistance and stability of the hulls will be calculated and their performance tested using sailing simulation software for different sail configurations. The document reviews methods for hull form modification, section mapping, resistance prediction, and stability analysis that will be used in the project.
The document describes a project to improve region transition for a 5 MW floating offshore wind turbine using simulation. The goal is to reduce power losses and loads during transition between operating regions caused by changes in wind speed. Two approaches are tested: modifying platform motion control using individual blade pitching; and changing the generator torque trajectory. The best results come from a linearized torque trajectory, reducing transition time by 80-90% and increasing energy capture. A combined controller further improves performance within the transition region.
it describes the bony anatomy including the femoral head , acetabulum, labrum . also discusses the capsule , ligaments . muscle that act on the hip joint and the range of motion are outlined. factors affecting hip joint stability and weight transmission through the joint are summarized.
How to Setup Warehouse & Location in Odoo 17 InventoryCeline George
In this slide, we'll explore how to set up warehouses and locations in Odoo 17 Inventory. This will help us manage our stock effectively, track inventory levels, and streamline warehouse operations.
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ISO/IEC 27001, ISO/IEC 42001, and GDPR: Best Practices for Implementation and...PECB
Denis is a dynamic and results-driven Chief Information Officer (CIO) with a distinguished career spanning information systems analysis and technical project management. With a proven track record of spearheading the design and delivery of cutting-edge Information Management solutions, he has consistently elevated business operations, streamlined reporting functions, and maximized process efficiency.
Certified as an ISO/IEC 27001: Information Security Management Systems (ISMS) Lead Implementer, Data Protection Officer, and Cyber Risks Analyst, Denis brings a heightened focus on data security, privacy, and cyber resilience to every endeavor.
His expertise extends across a diverse spectrum of reporting, database, and web development applications, underpinned by an exceptional grasp of data storage and virtualization technologies. His proficiency in application testing, database administration, and data cleansing ensures seamless execution of complex projects.
What sets Denis apart is his comprehensive understanding of Business and Systems Analysis technologies, honed through involvement in all phases of the Software Development Lifecycle (SDLC). From meticulous requirements gathering to precise analysis, innovative design, rigorous development, thorough testing, and successful implementation, he has consistently delivered exceptional results.
Throughout his career, he has taken on multifaceted roles, from leading technical project management teams to owning solutions that drive operational excellence. His conscientious and proactive approach is unwavering, whether he is working independently or collaboratively within a team. His ability to connect with colleagues on a personal level underscores his commitment to fostering a harmonious and productive workplace environment.
Date: May 29, 2024
Tags: Information Security, ISO/IEC 27001, ISO/IEC 42001, Artificial Intelligence, GDPR
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How to Make a Field Mandatory in Odoo 17Celine George
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Strategies for Effective Upskilling is a presentation by Chinwendu Peace in a Your Skill Boost Masterclass organisation by the Excellence Foundation for South Sudan on 08th and 09th June 2024 from 1 PM to 3 PM on each day.
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harmonic planetary gear FEM
1. Department of Mechanical and Indutrial Engineering Technology
Project 1
MODELLING OF SUN GEAR AND SHAFT
OF A HAMONIC PLANETARY GEAR
By
Sandile Shembe
(Student No - 201503655)
A mini-project report submitted
in partial fulfilment of the requirements for the module
STRESS ANALYSIS IV (ESA411)
FOR THE DEGREE OF BACHELOR OF
MECHANICAL ENGINEERING TECHNOLOGY
Submitted to
Supervisor - Dr. Daramy Kallon
DEPARTMENT OF MECHANICAL AND INDUSTRIAL ENGINEERING
TECHNOLOGY
FACULTY OF ENGINEERING AND THE BUILT ENVIRONEMNT
UNIVERSITY OF JOHANNESBURG
2. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 1
Submitted: Thursday 17th
September, 2015
Marking plan
Chapter Section Description Sum-
mark
Maximum
Marks
1 I Abstract 5 15
II Introduction 5
III Problem formulation 5
2 I Approach 5 20
II Literature review 10
III Methodology 5
3 I Design 8 20
II Simulation (at all four sections) 10
III Results (tabular, graphical) 2
4 I Discussion (interpretation of graphs) 12 15
II List of assumptions 3
5 I Conclusion (location of critical zones) 6 10
II Recommendations 4
References 6 10
Appendices 4
Report layout 4 10
Neatness 3
Presentation 3
Total Marks 100 100
Name: ………………………..……………Student No: ………………………. ………….
Signature: ..................................................Date: …………………………………………...
3. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 2
DECLARATION
I ……………………………………….. Hereby declare that this mini-project report is
wholly my own work and has not been submitted anywhere else for academic credit, either
by myself or another person.
I understand what plagiarism implies and declare that this report embodies my own ideas,
words, phrases, arguments, graphics, figures, results and organization except where reference
is explicitly made to another work.
I understand further that any unethical academic behaviour, which includes plagiarism, is
seen in a serious light by the University of Johannesburg and is punishable by disciplinary
action as stipulated by the university rules and regulations.
Name: ………………………..……………
Student No: ………………………. …….
Signature: ..................................................
Date: ………..............................................
4. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 3
ACKNOWLEDGEMENTS
I would like to express my gratitude to my Lecture Dr Kallon for his guidance and assistance
which helped me to be able to conduct this Project Report appropriately.
He made it clear for me what is required from the readings taken during the lab and also what
is expected in terms of the ELO’s on the discussion.
I would also like to thank my classmates for taking their time assisting me in inventor CAD.
5. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 4
ABSTRACT
This document reports the stress analysis of the Sun Gear and a shaft of a harmonic planetary
gear design assemble. Both Gear and Shaft are manufactured from mild steel. The Material
was chosen taking to considerations the mechanical properties, manufacturability and cost
study. The analysis is done so that critical stress concentrations can be identified and design
changes can be done to minimise chances of failure. Other motives for the analysis is that it is
critical to design transmission components as they possess high risk to passengers of the
motor vehicles.
The shaft and gear must withstand static and dynamic loads exacted on it. The sun gear is
locked on the shaft by a key. Loads varying from 15kN to 25kN directly on the
circumference of the gear. The assembly model is created on Inventor professional as well as
the simulation, then the stress concentration deflection is analysed and discussed in this
document.
The stress analysis of the gear and shaft is clearly illustrated graphically for the interpretation
and design decision. The graph indicates the force on the x-axis and the stress on the y-axis.
Theoretically the graph should be linear and increase proportionally.
The first graph on the table is section A-A, it indicating a true relationship between the load
applied and the stress induced. The stress is increases with the increase in load and the graph
is linear. However on the graph for B-B vs load, the stress increases with the load but it
reaches a point where it is constant.
In conclusion section A-A proved to be the only graph repreasenting true results for stress vs
load analysis.The minimum avarage principal stress is 84.45MPa and the maximum avarage
principal stress is 565.5MPa.The relationship is directly proportional because the as the force
increases the stress also increases.As it was stated on the assumptions the graph for this
material obeys Hookes law of stresses as the relationship is propotional.
6. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 5
Table of Contents
DECLARATION............................................................................................................................ 2
ACKNOWLEDGEMENTS............................................................................................................ 3
ABSTRACT.................................................................................................................................... 4
CHAPTER 1 ................................................................................................................................... 9
INTRODUCTION .......................................................................................................................... 9
1.1. Project Background.....................................................................................................9
1.2. Problem Formulation...................................................................................................9
1.2.1 Problem Statement...................................................................................................9
1.2.2 Scope of Project.....................................................................................................10
1.2.3 Limitations.............................................................................................................10
2.1 Introduction [Note: Give a one paragraph summary of this chapter] .......................11
2.2 Approach...................................................................................................................11
2.3 Literature review .......................................................................................................11
2.3.1 The Sun Gear and Shaft of a Harmonic Planetary Gear........................................11
2.3.2 Design and Application of the Sun Gear of a Harmonic Planetary Gear..............13
2.3.3 Fatigue and failure of the Sun Gear and Shaft of a Harmonic Planetary Gear
Error! Bookmark not defined.
2.3.4 Engineering Stress Analysis Procedure (Steps in FEM) .......................................17
2.3.5 Stress Analysis of the Sun Gear and Shaft of a Harmonic Planetary Gear ...........18
3.1 Introduction [Note: Give a one paragraph summary of this chapter] .......................19
3.2 Design........................................................................................................................19
3.3 Simulation (at all four sections) ................................................................................21
3.4 Results (tabular and graphical)..................................................................................33
4.1 Introduction [Note: Give a one paragraph summary of this chapter] .......................34
4.2 Discussions................................................................................................................34
4.3 Assumptions..............................................................................................................35
5.1 Introduction [Note: Give a one paragraph summary of this chapter] .......................36
5.2 Conclusions...............................................................................................................36
5.3 Recommendations.....................................................................................................36
REFERENCES ............................................................................................................................. 38
7. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 6
LIST OF FIGURES
Figure 1.1 Planetary gear system illustration……………………………………….9
Figure 2.3.1 Mild steel Stress Vs Strain Curve…………………………………12
Figure 2.3.2.2 (a). Gantry Milling Machine………………………………………..14
Figure 2.3.2.2 (b). Gantry Milling Machine ………………………………………14
Figure 2.3.2.2(c) Other Applications of Planetary gears…………………………14
Figure 2.3.3 (b) fatigue crack……………………………………………………...15
Figure 3.2a Harmonic gear and Shaft 2 D…………………………………….….19
Figure 3.2b Sun Gear 2 D…………………………………………………………19
Figure 3.2.2 Assembly 2 D………………………………………………………..20
Figure 3.4 Stress Vs Force Graph’s……………………………………………….33
Figure 5.2.1 Stress Vs Force (A-A) graphical Representation…………………….36
8. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 7
LIST OF TABLES
Table 3.1 Assemble Bill of Material
Table 3.3.1 Table of Result - 15kN
Table 3.3.2 Table of Result - 17kN
Table 3.3.3 Table of Result - 19kN
Table 3.3.4 Table of Result - 21kN
Table 3.3.5 Table of Result - 23kN
Table 3.3.6 Table of Result - 25kN
Table 3.4 Sectional Planes
9. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 8
LIST OF SYMBOLS or NOMENCLATURE
Symbol Description
P Point Load
x Varying distance
y Displacement
d^2y/dx^2 Moment Integral
dy/dx Slope Integral
Mmax Maximum Moment
Ixx Moment of Inertia
D Diameter
E Modulus of Elasticity
C Integration Constants
10. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 9
CHAPTER 1
INTRODUCTION
----------------------------------------------------------------------------------------------------------------
1.1. Project Background
Figure 1.1 Planetary gear system illustration
The purpose for this project is to identify critical location where the beam is likely to failure.
The analysis is done based on stresses induced by varying the load acting on the gear. The
material for the whole assemble is mild steel. Investigate the material selected satisfy the four
main properties or criteria namely High tensile and endurance strength allowing the material
to withstand static and dynamic loads respectively.
This sun gear and shaft to be design is for an automatic transmission of a Bell Front End
Loader. Then using Autodesk Inventor Professional 2015 both the sun gear and shaft is
designed, and simulate is run to identify stress concentration as well as deflection. The results
will be inspected, conclusion and recommendations are pointed out.
1.2. Problem Formulation
1.2.1 Problem Statement
A shaft of an automatic transmission planetary gear system carries a sun gear linked to three
gears orbiting around the planetary ring gear.
The assembly components are made up of mild steel. The loading on the shaft need to be
analysed for failure stress analysis. The aim is to find the location of the Fatigue and direct
stresses induced on assemble that may result in to mechanical failure. The load applied is
varied for different stress values.
The shaft geometry and material selected must be able to allow it to withstand the load of
gear and the point load varying from 15kN to 25kN acting on top of the gear and the beam is
fixed on the left-hand.
11. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 10
1.2.2 Scope of Project
Designing a sun gear and shaft of harmonic planetary gears, and then selecting mild steel as a
base material that will provide acceptable yield strength, cost effective and that has good
manufacturability.
The design assemble needs to simulated for stress analysis results and conclusion need to be
drawn based on the results. CAD simulation is done to investigate the degree of failure of the
selected material; this is achieved by data inputting material properties on the design model.
Deflection and slope is calculated for the designed assembly at maximum point load of 25KN
applied at 42mm from the fixed end.
The following is guideline or scope of the project.
1. Literature review on material selection for planetary gears.
2. Select mild steel as a material for the shaft, gear and key of the planetary system.
3. Determine the slope and deflection at maximum loading.
4. Model the design and do stress analysis on inventor.
1.2.3 Limitations
Since material is assigned based on the procedure stated on this report and can only be
proved by calculations and stress analysis on Inventor Auto Cad.The limitations are practical
testing of the material selected, because selection was done by investigating the material used
in industry then selected on the standard tables.
To ensure proper selection of material, hardness test must be done on the material then a
prototype must be manufactured to do precise test
12. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 11
CHAPTER 2
Approach, Literature Review and Methodology
----------------------------------------------------------------------------------------------
2.1 Introduction
The engine drives the transmission, and then the transmission will transmit the drive through
the propeller shaft to the axle for wheel drive. In the system there must be a sun gear and
shaft of a planetary gear system, this system or mechanism convert the reciprocating motion
to rotational motion. Therefore the harmonic shaft is induced with mechanical stresses and
then material selection becomes a critical or import factor in the design so as to try and
minimise those stresses. The literature covers the theory behind material selection,
application and methodology of designing effective structures.
2.2 Approach
In this design the history and applications of a sun gear and a harmonic shaft is investigated.
The sun gear and shaft being designed is used on the automatic transmission. In this design
the shaft and the gear are mild steel and assemble is simulate on CAD for stress analysis and
deformation, results are documented on chapter three.
The material to be selected must also have the shaft diameter as a standard size so that the
design can be cost effective. Results will be illustrated by the drawing programme so that it
can be concluded about the impact of the applied force on the shaft of selected material.
2.3 Literature review
2.3.1 The Sun Gear and Shaft of a Harmonic Planetary Gear
The sun gear is located at the centre of the planetary gears traveling on the ring gear. The sun
gear is transmitting torque from the shaft to the planet gears.
Therefore the material of the sun gear must be able to withstand bending and torsional
stresses induced by the motor driving the harmonic shaft. When the sun and planetary gear
system was invented the aim was to convert reciprocation motion to rotary motion. In trying
to convert the reciprocating motion to rotary motion the planetary gears are exposed to
mechanical stress in different planes.
13. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 12
The following performance material indices are considered for the material selection of
transmission gears.
surface fatigue limit
root bending fatigue limit
wear resistance of tooth’s flank and
Machinability.
The material used for the gear and shaft design is mild steel.
Mild Steel
Mild steel composition consist of iron alloy containing 0.3 % carbon ,but the range is
normally between 0.1-0.25 %.It main characteristics are its ductility and malleability.
Those characteristics are important and therefore mild steels are used to manufacture
fasteners and also used in railings and decorative gates.
The property of malleability allows mild steels to be bent, twisted without fracture and
fatigue.
Figure 2.3.1 Mild steel Stress Vs Strain Curve (Design of Steel Structures at Indian Institute
of Technology Madras)
14. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 13
Low Carbon steels
Low carbon steels has less composition of carbon, ranging from 0.05% to 0.3%.Generally in
vehicle body panels, pipes chains, rivets and fasteners the composition of carbon is between 0
.05 And 0.2 while on gears, shafts it ranges from 0.2 – 0.3 % of C.
Low carbon steels are normally used where high strength is not a requirement.
2.3.2 Design and Application of the Sun Gear of a Harmonic Planetary Gear
2.3.2.1 Design of the Sun Gear of a Harmonic Planetary Gear
Transmissions of this century are becoming more based on high speeds and precision which
then require gear systems with special design.
Therefore planetary gears are mostly used in machines that are required to transfer
information, energy and materials. The design is in such a way that there are no internal
backlash or minimal if complex to ignore totally. The design of harmonic gears have
advantages of high output capacity on the bearing.
The other advantages of modern design of harmonic gears high torque capacity, precise
positioning geometry, compact design, single stage high ratios and high effectiveness.
Planetary gears sizes and configuration vary widely depending on desired speed ratios and
design requirements. That is an advantage that allows them to be used in various applications
for example in clocks, car mirrors, toys, automobile transmissions and turbine engines.
2.3.2.2 Application of the Sun Gear of a Harmonic Planetary Gear
An example of application of sun gear of harmonic planetary gear mechanism is a gantry
milling machine of large turbine components. This machine has high cutting forces going up
to 30KN.
The harmonic planetary gear system design is able to handle the pre-load torque that can be
varied which the machine operating mode. In this application there are very high
accelerations in torque and precision is also important as this is governed by a co-ordinate
system. When one actuator of the milling machine acts as a brake it increases the pre-load
which remove the backlash in the pinion ring and the torsional stiffness is increased as well.
And the advantages of this system arrangement are high performance without comprising
accuracy. Below the machine is illustrated.
15. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 14
Figure 2.3.2.2 (a). Gantry Milling Machine
Figure 2.3.2.2 (b). Gantry Milling Machine
Figure 2.3.2.2(c) Other Applications of Planetary gears
16. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 15
2.3.3 Fatigue and failure of the Sun Gear and Shaft of a Harmonic Planetary Gear
Figure 2.3.3(a) Failure due to heavy static loads induced.
Figure 2.3.3 (b) According to the research done by the K S Rangasamy College of
Technology, the failure that was observed here was caused by rust then the gear failed
because of fatigue crack.
17. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 16
2.3.4 Engineering Materials
Materials selected for gear application are expected to provide a combination of
characteristics without comprising cost in trying to satisfy the requirements. Physical
properties that are significant for gear material are fatigue, shear, static strength, wear
resistance, toughness and strength at high temperatures.
Engineering materials properties vary because they depend on a wide range of factors, such
as chemical composition, processes of manufacture, molecular defects, heat treatment and
temperature.
Usually on ATSM tables and charts, the common properties that are specified are the
ultimate, yield strength, compressive strength, Modulus of elasticity normally when looking
in tension and torsion, then Brinell hardness and finally fatigue stress factors.
Constrains in selecting the gear material are the component geometry, manufacturability and
cost effectiveness.
For the purpose of this project the materials that are being investigated are Plain carbon
steels, medium carbon steels and low alloy ASTM High strength steel.
Plain carbon steels
.
2.3.5 Engineering Materials Selection Procedure
Gears can be made from variety of material depending on application needs, for example they
can be manufactured from Steel, Cast Iron, nylon, acetal etc.
Normally the first step in selecting the material is to gather information about the
performance requirements of the system where the gear will be used. Thus assist on choosing
the material with sufficient physical and chemical properties, then processing requirements.
According NSI-AGMA 2004-B89 Gear Material Manual, there seven guidelines used in this
project for material selection for sun gear and shaft they are listed below:-
1. Physical Mechanical Properties
2. Grade and Heat Treatment
3. Manufacturability
4. Availability and Cost
5. Hardenability and Size Effects
6. Cleanliness
7. Dimensional Stability
18. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 17
Other requirements for material selection during design stage are, design requirements such
as knowing what the application of the component to be designed, essential requirements that
need to be met e.g. strength and stiffness etc. The material life is mostly affected by corrosion
and fatigue.
The geometric and material properties also are a requirements and these assist in determining
equations for constrains such as yield, fracture, buckling etc.
2.3.6 Engineering Stress Analysis Procedure (Steps in FEM)
Essential steps to be followed for stress analysis are as follows:-
Discretization
In this step it where the nodes are selected and the element mesh is formed either in
2d or 3D.The mesh is a formation of shapes such as triangles, quadrilaterals,
tetrahedral, prismatic etc.
Selection of element to be analysed
Selection of displacement function
Displacement function can any polynomial, that function will produce an approximate
result and it will also satisfy basic requirements for the analysis.
Defining the stress verses strain relationship
Derive the element stiffness matrix
To derive the element stiffness matrix, nodal forces are used because they are related
to the stiffness. In this step the material is also specified.
The function consist of force, stiffness and displacement.
Derivation of overall matrices and equations
In this step the matrices for each nodal points is assembled to form a global.
Solving for nodal displacements
Specify the boundary conditions
Solving for element forces applied at nodes
Interpretation of the results
19. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 18
2.3.7 Stress Analysis of the Sun Gear and Shaft of a Harmonic Planetary Gear
Due to the mechanical movements in the transmission, the sun gear and harmonic planetary
gears become under mechanical stresses. These stresses results into catastrophic failures if
unidentified.
In the planetary gears the stresses increases as the torque increases. The vibrations that occur
during rotation in the system courses fatigue in critical areas where the shafts are fixed. In
design of planetary gears, finite element analysis is applied to a single tooth so that results are
accurate. The material strength is the key factor in major consideration for the operational
loading. CAD software’s are used to analyse the structures programmes such as Pro
Engineer, PTC creo, solid works and Inventor.
2.4 Methodology
The design methodology followed could be summarized as follows;
Step 1: Modelling assemble consisting of a gear, shaft and key.
Step 2: Select Mild steel as base material.
Step 3: Apply different loads ranging from 15 kN to 25kN with increments of 2 kN
Step 4: Create a simulation and run.
Step5: Assemble is then analysed for weight, stress and displacement.
Step6: The results are then compared to the commercial figures and observed if they
are still within mechanical operational requirement, and if not then iterations from
step 3 are necessary.
Design constraints
The dimensions must not be altered.
The load position and increments must be kept constant throughout.
20. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 19
CHAPTER 3
Modelling of Sun Gear and Shaft
----------------------------------------------------------------------------------------------
3.1 Introduction
The design consist of assemble of a gear, shaft and key. The structure forms a cantilever
beam fixed on the left-hand of the beam. The position of the load is 44mm from the fixed
wall. The magnitude of the load applied is varied from 15kN to 25kN and simulation is done
to identify the location of critical failure points.
3.2 Design
Below there are 2 dimensional drawings for the assemble and its parts
Figure 3.2a.Gear and shaft assemble.
Figure 3.2b.Gear.
21. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 20
Figure 3.2c. shaft
Figure 3.2d.Gear and shaft assemble with dimensions (Illustration)
Table 3.1 Assemble Bill of Material
Bill of Material
Parts List Material Quantity
Gear Steel, Mild 1
Shaft Steel, Mild 1
Key Steel, Mild 1
22. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 21
3.3 Simulation (at all four sections)
Table 3.3.1 Table of Result - 15kN
Name Minimum Maximum
Volume 45817.5 mm^3
Mass 0.359668 kg
Von Mises Stress 0.0856843 MPa 678.622 MPa
1st Principal Stress -224.781 MPa 806.017 MPa
3rd Principal Stress -815.195 MPa 247.271 MPa
Displacement 0 mm 0.194262 mm
Safety Factor 0.30503 ul 15 ul
Von Mises Stress
23. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 22
1st
Principal Stress
3rd
Principal Stress
24. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 23
Table 3.3.2Table of Result - 17kN
Name Minimum Maximum
Volume 45817.5 mm^3
Mass 0.359668 kg
Von Mises Stress 0.649899 MPa 1081.39 MPa
1st Principal Stress -386.234 MPa 1406.22 MPa
3rd Principal Stress -1389.3 MPa 404.037 MPa
Displacement 0 mm 0.37656 mm
Safety Factor 0.191421 ul 15 ul
Von Mises Stress
25. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 24
1st
Principal Stress
3rd
Principal Stress
26. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 25
Table 3.3.3 Table of Result - 19kN
Name Minimum Maximum
Volume 45817.5 mm^3
Mass 0.359668 kg
Von Mises Stress 1.33718 MPa 1629.75 MPa
1st Principal Stress -566.569 MPa 2118.43 MPa
3rd Principal Stress -2031.03 MPa 555.983 MPa
Displacement 0 mm 0.580473 mm
Safety Factor 0.127013 ul 15 ul
Von Mises Stress
27. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 26
1st
Principal Stress
3rd
Principal Stress
28. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 27
Table 3.3.4 Table of Result - 21kN
Name Minimum Maximum
Volume 45817.5 mm^3
Mass 0.359668 kg
Von Mises Stress 2.08496 MPa 2238.68 MPa
1st Principal Stress -765.845 MPa 2913.13 MPa
3rd Principal Stress -2740.36 MPa 718.377 MPa
Displacement 0 mm 0.805869 mm
Safety Factor 0.092465 ul 15 ul
Von Mises Stresses
29. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 28
1st
Principal Stresses
3rd
Principal Stresses
30. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
Page | 29
Table 3.3.5Table of Result – 23 kN
Name Minimum Maximum
Volume 45817.5 mm^3
Mass 0.359668 kg
Von Mises Stress 3.18833 MPa 2906.77 MPa
1st Principal Stress -984.063 MPa 3785.58 MPa
3rd Principal Stress -3517.21 MPa 893.883 MPa
Displacement 0 mm 1.05276 mm
Safety Factor 0.071213 ul 15 ul
Von Mises Stresses
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1st
Principal Stresses
3rd
Principal Stresses
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Table 3.3.6 Table of Result – 25 kN
Name Minimum Maximum
Volume 45817.5 mm^3
Mass 0.359668 kg
Von Mises Stress 3.31356 MPa 3633.71 MPa
1st Principal Stress -1221.26 MPa 4734.92 MPa
3rd Principal Stress -4361.68 MPa 1083.58 MPa
Displacement 0 mm 1.32112 mm
Safety Factor 0.0569665 ul 15 ul
Von Mises Stresses
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1st
Principal Stresses
3rd
Principal Stresses
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3.4 Results (tabular and graphical)
Table 3.4 Sectional Planes
F (kN) A-A B-B C-C D-D
15 84,45 -18,65 -121,7 -121,7
17 151,25 -27 -207 -207
19 238,5 -30 -298,5 -567
21 338 -30 -398 -766
23 447 -30 -507 -984
25 565,5 -30 -625,5 -1221
Graphical Representation
Figure 3.4 Stress Vs Force Graph’s
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CHAPTER 4
Discussion of Results - Stress Analysis of the Sun Gear and Shaft
----------------------------------------------------------------------------------------------
4.1 Introduction
This chapter discusses the results of the stress analysis report generated from Inventor
simulation. The stresses that were developed in the analysis were, then tabulated and used to
derive graphs that represent the relationship between the stress and the force. The readings
are separated by sectional planes namely A-A, B-B, C-C & D-D. These graphs are clearly
explained in this chapter and it can be seen that only the graph of section A-A is on the
positive axis thus shows the where there is high concentration of stresses. Assumptions are
also stated in this chapter for the design.
4.2 Discussions
4.2.1 Interpretation of the first four graphs
The stress analysis of the gear and shaft is clearly illustrated graphically for the interpretation
and design decision. The graph indicates the force on the x-axis and the stress on the y-
axis.Theoritically the graph should be linear and increase proportionally.
The first graph on the table is section A-A ,it indicating a true relationship between the load
applied and the stress induced.The stress is increases with the increase in load and the graph
is linear. However on the graph for B-B vs load ,the stress increases with the load but it
reaches a point where it is constant.
The graph for section D-D & C-C the relationship is linear but the trend is ever decreasing
which indicates that as the load increases the stress is lesser .It is then found that as you move
closer to the load location the stress tend to decrease even when the load is increased.
From the graphical interpretation it can be deduced that the stress is concentrated more on the
fixed end between the shaft and the wall.as it is shown on figure 4.2.1 the concentration is
more on the fixed wall.
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4.2.1 Stress Concentration critical points illustration
4.3 Assumptions
1. The material in the model complies with Hooke’s law and therefore stress is directly
proportional to strain.
2. The induced displacements are small enough to ignore the change in stiffness caused
by loading.
3. Boundary conditions do not vary during the application of loads. Loads must be
constant in magnitude, direction, and distribution. They should not change while the
model is deforming.
4. All loads are applied slowly and gradually until they reach their full magnitudes. After
reaching their full magnitudes, loads remain constant (time-invariant).
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CHAPTER 5
Conclusions and Recommendations
----------------------------------------------------------------------------------------------
5.1 Introduction
This chapter documents the conclusion about the stress analysis performed on assemble. The
stresses from the graphs were tabulated and grouped into sections. Plane A-A graph produced
results that shows the true relationship between stress induced and force applied.
Recommendations are also stated in this chapter, recommendations such as position of the
load and method of calculating the sectional stresses need to be investigated for accuracy.
5.2 Conclusions
5.2.1 Interpretation of final graph (Location of critical zones)
The graph that possess more appropriate results is for section A-A since the relationship of
the stress and force is proportional. Below is the graph of section AA. The minimum avarage
principal stress is 84.45MPa and the maximum avarage principal stress is 565.5MPa.
Figure 5.2.1 Stress Vs Force (A-A) graphical Representation
The minimum avarage principal stress is 84.45MPa and the maximum avarage principal
stress is 565.5MPa.The relationship is directly proportional because the as the force increases
the stress also increases.As it was stated on the assumptions the graph for this material obeys
Hookes law of stresses as the relationship is propotional.The sectional stresses indicate that as
the planes shift away from the critical stress area the stress concentration decreases and that is
clear when the assemble simulate is viewd.
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The graphical results also illustrate the material selected obeys Hooks law.The material is
alos not brittle ,that is proven by the analysis since it didn’t breck but it resisted the and
consumed the stress applied.
Recommendations
Load needs to be applied at the centre of the gear so that it can act in line with the
weight of the gear.
The gear need to be designed with the tooth for more accurate results, and remove the
holes because they affect the stress.
The method of calculating the sectional stresses need to be investigated for accuracy.
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REFERENCES
Examples of References
1. http://www.ehow.com/facts_6961115_properties-uses-mild-steel.html
2. Analysis of Stresses and Deflection of Sun Gear by Theoretical and ANSYS
Method_PDF
3. 02/05/2015,http://www.ezlok.com/TechnicalInfo/MPCarbonSteel.html
4. (Published in 1997) Strength of Materials For Technicians ;J.G Drosky
5. (Published: 2011-01-04)Mechanics of Materials 6th Edition .James Gere
6. DA6-BeamFormulas Downloaded document
7. (1 Mar. 2010) Shigley's Mechanical Engineering Design 9th Edition by Budynas,
Richard, Nisbett, Keith
8. Marks' Standard Handbook for Mechanical Engineers
Appendix_B.pdf
9. 10/05/2015,https://www.google.co.za/search?q=planetary+gear+transmission
10. 06/05/2015,https://www.google.co.za/search?q=Gantry+Milling+Machine
11. 10/05/2015,Carbon Steel Hand Book by D. Gandy; EPRI Project Manager
12. Developments In Abrasive WaterJet Technology
13. http://www.wjta.org/wjta/New_Developments_etc.asp, Accessed August 2011
14. WaterJet Technology
15. http://www.todaysconcretetechnology.com/waterjet-cutting-will-create-new-
opportunities-for-designers.html, Accessed August 2011
40. Modelling of Sun Gear and Shaft of a Harmonic Planetary Gear – ESA411
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Appendices