Master's degree in Space and Aeronautical Engineering
http://hdl.handle.net/2117/90863
2020-03-29T01:06:16ZDesign and implementation of a single On-Board Computer for CubeSats
http://hdl.handle.net/2117/180871
Design and implementation of a single On-Board Computer for CubeSats
Molina Ordóñez, Carlos
his document reports the process of design, implementation, and testing of an On-Board Computer for CubeSats in a single 1U-sized CubeSat PCB. The aim is to design a modular, cheap, e cient and exible product than could be easily reproduced and implemented in forthcoming CubeSats missions. The document describes all the hardware design phases, from the selection of components to the creation of the circuits and blocks, following with the physical design of the layout in two stackable boards, and nally the actual integration and subsequent electrical test of the components. The project ended successfully with a prototype of the OBC allowing the boot of a Linux operative system from a µSD card, and the documentation needed to reproduce the work and manufacture new products.
2020-03-23T10:50:17ZMolina Ordóñez, Carloshis document reports the process of design, implementation, and testing of an On-Board Computer for CubeSats in a single 1U-sized CubeSat PCB. The aim is to design a modular, cheap, e cient and exible product than could be easily reproduced and implemented in forthcoming CubeSats missions. The document describes all the hardware design phases, from the selection of components to the creation of the circuits and blocks, following with the physical design of the layout in two stackable boards, and nally the actual integration and subsequent electrical test of the components. The project ended successfully with a prototype of the OBC allowing the boot of a Linux operative system from a µSD card, and the documentation needed to reproduce the work and manufacture new products.Study and development of attitude control and determination simulation software and control algorithms for 3Cat-4 mission
http://hdl.handle.net/2117/180780
Study and development of attitude control and determination simulation software and control algorithms for 3Cat-4 mission
Diez Garcia, Carlos
The AOCS of a spacecraft is the responsible for determining the attitude of the satellite and controlling it to reach a specific pointing state, to alloww the execution of scientific experiments on board. In the case of 3Cat-4 mission, a magnetic control system is used to align the deployable helix antenna with the Nadir vector to perform the GNSS-R and L-band radiometry experiments for Earth Observation. This task is especially complex to perform in nanosatellites due to the limitations of mass, size, and power consumption. To analyze the performance of this subsystem, facilities (Helmholtz coils, TVAC, Sun simulator) are used that try to emulate the environment in which the satellite will operate, but this is not always possible and for this reason this project has been carried out. In this project, a simulation software programmed in MATLAB has been developed to analyze the performance of the AOCS subsystem. This tool has been used to validate the design and verify the compliance with the subsystem requirements, but also to support the design phase. In addition, the simulator has been used to analyze the AOCS of the 3Cat-4 mission developed by the UPC NanoSat Lab. This document explains the physics behind each of the blocks modeled to emulate the space environment, implementing the equations that govern the orbial dynamics and attitude of the satellite and including the disturbance forces that affect a satellite in orbit LEO . In addition, the development of the attitude determination and control system, both of the hardware part (i.e. sensors and actuators) and of the estimation and control algorithms, is presented. In particular, the Optimal-REQUEST algorithm has been implemented and the control laws for the Detumbling and Nadir Pointing Mode modes, corresponding to the 3Cat-4 mission, have been developed. The results of the analysis showthe correct operation of the simulator and the compliance of the subsystem requirements of the 3Cat-4 mission. The control modes meet the objectives defined, i.e. the detumbling mode is capable to stabilize the system and reduce the angular velocity of the CubeSat below 2°/s in less than 24 hours and the Nadir Pointing mode allows to reach the pointing towards Nadir, with a maximum angular deviation of 10° and angular velocity of 0.5°/s in the X and Y axes of the satellite. On the other hand, the results show the great negative impact of the aerodynamic drag, due to the physical characteristics of the CubeSat and the orbit in which it is located, causing the control system to have to be continuously active to compensate for the disturbances and reach the desired attitude state. 2
2020-03-20T16:28:25ZDiez Garcia, CarlosThe AOCS of a spacecraft is the responsible for determining the attitude of the satellite and controlling it to reach a specific pointing state, to alloww the execution of scientific experiments on board. In the case of 3Cat-4 mission, a magnetic control system is used to align the deployable helix antenna with the Nadir vector to perform the GNSS-R and L-band radiometry experiments for Earth Observation. This task is especially complex to perform in nanosatellites due to the limitations of mass, size, and power consumption. To analyze the performance of this subsystem, facilities (Helmholtz coils, TVAC, Sun simulator) are used that try to emulate the environment in which the satellite will operate, but this is not always possible and for this reason this project has been carried out. In this project, a simulation software programmed in MATLAB has been developed to analyze the performance of the AOCS subsystem. This tool has been used to validate the design and verify the compliance with the subsystem requirements, but also to support the design phase. In addition, the simulator has been used to analyze the AOCS of the 3Cat-4 mission developed by the UPC NanoSat Lab. This document explains the physics behind each of the blocks modeled to emulate the space environment, implementing the equations that govern the orbial dynamics and attitude of the satellite and including the disturbance forces that affect a satellite in orbit LEO . In addition, the development of the attitude determination and control system, both of the hardware part (i.e. sensors and actuators) and of the estimation and control algorithms, is presented. In particular, the Optimal-REQUEST algorithm has been implemented and the control laws for the Detumbling and Nadir Pointing Mode modes, corresponding to the 3Cat-4 mission, have been developed. The results of the analysis showthe correct operation of the simulator and the compliance of the subsystem requirements of the 3Cat-4 mission. The control modes meet the objectives defined, i.e. the detumbling mode is capable to stabilize the system and reduce the angular velocity of the CubeSat below 2°/s in less than 24 hours and the Nadir Pointing mode allows to reach the pointing towards Nadir, with a maximum angular deviation of 10° and angular velocity of 0.5°/s in the X and Y axes of the satellite. On the other hand, the results show the great negative impact of the aerodynamic drag, due to the physical characteristics of the CubeSat and the orbit in which it is located, causing the control system to have to be continuously active to compensate for the disturbances and reach the desired attitude state. 2Advanced study for the numerical resolution of the Navier-Stokes equations. Applications to the industrial and aerodynamic fields: Case 80A
http://hdl.handle.net/2117/176774
Advanced study for the numerical resolution of the Navier-Stokes equations. Applications to the industrial and aerodynamic fields: Case 80A
Santos Serrano, Daniel
The main objective of this work is to study interesting cases related to mechanics of fluids and heat transfer: they have studied two cases to validate the discrete diffusion equation by convection in laminar regime, they have studied two cases to validate the discrete equations of Navier-Stokes in laminar regime and they have studied two cases to validate the discrete Navier-Stokes equations in turbulent regime using LES and RANS models. In addition, the spectral and pseudospectral methods are Revised in Appendix A. To do so, the author has written his own code for the first four cases and for the spectral and pseudospectral cases, and has used Termo code uids and Open- FOAM code for fifth and sixth cases. All results have been contrasted with experimental results and / or DNS. The sixth chapter, which is the most interesting, contains a novel preprocessing. tool based on the background Conservation of symmetry [1]. This tool allows us to guarantee if the pressure-speed coupling system will reach convergence when used meshes placed (in any dimension and with any type of mesh). The development This tool consists of 2 new slogans, 3 new theorems and 3 new corollaries. Motto 1, theorems 2 and 3 and corollaries 1 and 3 have been proven by me, motto 2 years corollary 2 has been proven by Dr. Xavi Trias and theorem 1 has been proven by Dr. Xavi Trias and me.
2020-02-04T18:32:53ZSantos Serrano, DanielThe main objective of this work is to study interesting cases related to mechanics of fluids and heat transfer: they have studied two cases to validate the discrete diffusion equation by convection in laminar regime, they have studied two cases to validate the discrete equations of Navier-Stokes in laminar regime and they have studied two cases to validate the discrete Navier-Stokes equations in turbulent regime using LES and RANS models. In addition, the spectral and pseudospectral methods are Revised in Appendix A. To do so, the author has written his own code for the first four cases and for the spectral and pseudospectral cases, and has used Termo code uids and Open- FOAM code for fifth and sixth cases. All results have been contrasted with experimental results and / or DNS. The sixth chapter, which is the most interesting, contains a novel preprocessing. tool based on the background Conservation of symmetry [1]. This tool allows us to guarantee if the pressure-speed coupling system will reach convergence when used meshes placed (in any dimension and with any type of mesh). The development This tool consists of 2 new slogans, 3 new theorems and 3 new corollaries. Motto 1, theorems 2 and 3 and corollaries 1 and 3 have been proven by me, motto 2 years corollary 2 has been proven by Dr. Xavi Trias and theorem 1 has been proven by Dr. Xavi Trias and me.Study of Optimization Methods for Space Debris Removal in Low Earth Orbits
http://hdl.handle.net/2117/176773
Study of Optimization Methods for Space Debris Removal in Low Earth Orbits
Sadeghi, Ehsan
2020-02-04T17:57:27ZSadeghi, Ehsan[eProject] Study of control and stability of a STOL light aircraft
http://hdl.handle.net/2117/175386
[eProject] Study of control and stability of a STOL light aircraft
Puljic, Stjepan
2020-01-21T15:25:01ZPuljic, StjepanStudy of minimum length, supersonic nozzle design using the Method of Characteristics
http://hdl.handle.net/2117/174450
Study of minimum length, supersonic nozzle design using the Method of Characteristics
Murnaghan Murnaghan, Murrough
This report outlines the pertinent theory and methods for supersonic nozzle design using the method of characteristics. The programmes developed design ideal nozzle contours, using numerical methods based on the gas properties, for desired exit velocities. Ideal contours include the most rapidexpansion without inducing shock waves followed by the straigh tening sec-tion to provide uniform exit conditions. Then based on the ideal results, thecontours can be truncated and the shape modified to induce minor shocksand only sacrifice minimal thrust to save length and thereby weight.
2020-01-08T18:08:31ZMurnaghan Murnaghan, MurroughThis report outlines the pertinent theory and methods for supersonic nozzle design using the method of characteristics. The programmes developed design ideal nozzle contours, using numerical methods based on the gas properties, for desired exit velocities. Ideal contours include the most rapidexpansion without inducing shock waves followed by the straigh tening sec-tion to provide uniform exit conditions. Then based on the ideal results, thecontours can be truncated and the shape modified to induce minor shocksand only sacrifice minimal thrust to save length and thereby weight.Study: The ion propulsion system and trajectory of Dawn spacecraft
http://hdl.handle.net/2117/170538
Study: The ion propulsion system and trajectory of Dawn spacecraft
Boix Candil, Álvaro
Dawn mission represents a revolutionary achievement in space research due to the fact that it was the first spacecraft to orbit two different extraterrestrial bodies, the asteroids Vesta and Ceres. It was managed by NASA’s JPL since its design, its launch in 2007 until its end in November 2018. Its objective was accomplished thanks to its Ion Propulsion System (IPS), which made possible the required manoeuvres and trajectories required to fulfil the mission’s objectives.
This thesis focuses on the study of this innovative IPS, specifically on how it works during the mission and trying to understand why it operates in one way or another. Specially, the thesis centres in the most characteristic manoeuvre
of the entire Dawn mission, the escape trajectory from Vesta to begin cruise to Ceres.
In order to do this, the JPL’s SPICE library and toolkit is employed during the whole computations due to its high reliable source of data. From this information provided by SPICE, some calculations are performed regarding the
Dawn IPS such as its trajectory, thrust force and even though its input power given by the spacecraft’s solar arrays. One of this thesis’s goals is to prove the reliability of this SPICE given data as well as its programming tools, which is confirmed after analysing the extracted results and comparing them to corroborated information.
Furthermore, together with the SPICE computations, the same IPS parameters are estimated employing some theoretical models related to space manoeuvres similar to the ones performed by Dawn. The feasibility of the
application of these established procedures is also wanted to be demonstrated in the case of each determined value.
After the calculations, it is found out that these methodologies are validated due to the absolute similarity to the results obtained with SPICE. The estimated low thrust climb trajectory results in a truly approximate escape trajectory, and
the thrust force value provided by a low thrust escape is incredibly similar to the SPICE one, even taking into account the definitely low values of ion propulsion compared to the common hydrazine thrusters. Last but not least,
thanks to the determination of the IPS input power, given by the solar arrays’ orientation and efficiency, it is possible to verify the real values of the thrust force, which even improved the results extracted previously.
This thesis means a first approach to the analysis of a space mission and its elements, and it represents a starting point into a more various or deeper study of the parameters of them
2019-10-22T08:04:58ZBoix Candil, ÁlvaroDawn mission represents a revolutionary achievement in space research due to the fact that it was the first spacecraft to orbit two different extraterrestrial bodies, the asteroids Vesta and Ceres. It was managed by NASA’s JPL since its design, its launch in 2007 until its end in November 2018. Its objective was accomplished thanks to its Ion Propulsion System (IPS), which made possible the required manoeuvres and trajectories required to fulfil the mission’s objectives.
This thesis focuses on the study of this innovative IPS, specifically on how it works during the mission and trying to understand why it operates in one way or another. Specially, the thesis centres in the most characteristic manoeuvre
of the entire Dawn mission, the escape trajectory from Vesta to begin cruise to Ceres.
In order to do this, the JPL’s SPICE library and toolkit is employed during the whole computations due to its high reliable source of data. From this information provided by SPICE, some calculations are performed regarding the
Dawn IPS such as its trajectory, thrust force and even though its input power given by the spacecraft’s solar arrays. One of this thesis’s goals is to prove the reliability of this SPICE given data as well as its programming tools, which is confirmed after analysing the extracted results and comparing them to corroborated information.
Furthermore, together with the SPICE computations, the same IPS parameters are estimated employing some theoretical models related to space manoeuvres similar to the ones performed by Dawn. The feasibility of the
application of these established procedures is also wanted to be demonstrated in the case of each determined value.
After the calculations, it is found out that these methodologies are validated due to the absolute similarity to the results obtained with SPICE. The estimated low thrust climb trajectory results in a truly approximate escape trajectory, and
the thrust force value provided by a low thrust escape is incredibly similar to the SPICE one, even taking into account the definitely low values of ion propulsion compared to the common hydrazine thrusters. Last but not least,
thanks to the determination of the IPS input power, given by the solar arrays’ orientation and efficiency, it is possible to verify the real values of the thrust force, which even improved the results extracted previously.
This thesis means a first approach to the analysis of a space mission and its elements, and it represents a starting point into a more various or deeper study of the parameters of themFrom pure conduction to homogeneous isotropic turbulence
http://hdl.handle.net/2117/127948
From pure conduction to homogeneous isotropic turbulence
Alsalti Baldellou, Àdel
L’objectiu d’aquest treball és estudiar multiples casos relacionats amb la dinàmica de ﬂuids i amb la transferència de calor. Més concretament, sis casos de complexitat creixent han estat abordats des de la perspectiva de la dinàmica de ﬂuids computacional, resolent les equacions en derivades parcials associades a cada fenomen a partir del mètode de volums ﬁnits. Els casos que han estat simulats són: conducció pura, convecció-difusió, lid-driven cavity, differentially heated cavity, equació de Burgers en una i dues dimensions i turbulència isotròpica homogènia (implementant el model de turbulència de Smagorinsky).; The aim of this work is to study multiple cases related to ﬂuid dynamics and heat transfer. More concretely, six cases of increasing complexity will be approached from the perspective of computational ﬂuid dynamics, solving the partial di↵erential equations related to each phenomenon by means of the ﬁnite volume method. The cases that have been simulated are: pure conduction, convection-di↵usion, lid-driven cavity, differentially heated cavity, one and two-dimensional Burgers equation and homogeneous isotropic turbulence (implementing the Smagorinsky turbulence model).
2019-01-30T17:12:45ZAlsalti Baldellou, ÀdelL’objectiu d’aquest treball és estudiar multiples casos relacionats amb la dinàmica de ﬂuids i amb la transferència de calor. Més concretament, sis casos de complexitat creixent han estat abordats des de la perspectiva de la dinàmica de ﬂuids computacional, resolent les equacions en derivades parcials associades a cada fenomen a partir del mètode de volums ﬁnits. Els casos que han estat simulats són: conducció pura, convecció-difusió, lid-driven cavity, differentially heated cavity, equació de Burgers en una i dues dimensions i turbulència isotròpica homogènia (implementant el model de turbulència de Smagorinsky).
The aim of this work is to study multiple cases related to ﬂuid dynamics and heat transfer. More concretely, six cases of increasing complexity will be approached from the perspective of computational ﬂuid dynamics, solving the partial di↵erential equations related to each phenomenon by means of the ﬁnite volume method. The cases that have been simulated are: pure conduction, convection-di↵usion, lid-driven cavity, differentially heated cavity, one and two-dimensional Burgers equation and homogeneous isotropic turbulence (implementing the Smagorinsky turbulence model).Development of Computational Fluid Dynamic codes for the numerical resolution of the Navier-Stokes equations applied to benchmark problems using finite volume method
http://hdl.handle.net/2117/126239
Development of Computational Fluid Dynamic codes for the numerical resolution of the Navier-Stokes equations applied to benchmark problems using finite volume method
Ortega Varas, Boris Marcial
The main objective of this work is the development of different programs to learn and verify computational fluid dynamics problems which are governed by the Navier-Stokes equations. The document will be divided into different chapters in which we will detail the procedures performed. During the first chapter there will be an introduction on computational fluid dynamics problems, as the basic requirements to deal with this type of cases, as well as the limits that will be encountered during the development of these. In the second chapter there will be a brief introduction about the necessary theory which will be of great help during the development of the case studies. The convection-diffusion equations will be studied in the third chapter, which will be discretized for the development of the different cases. In this chapter we will also introduce the concept of Finite volume method that will be a fundamental part of this work. Finally, we will see the different numerical schemes that can be implemented, as well as the different solvers. During the fourth chapter the different cases will be presented, such as the Transient Conduction problem, the Diagonal flow and the Smith Hutton problem, which will be developed and commented. In the fifth chapter we will introduce in the Fractional Step Method, we will see the different steps to follow for the implementation of this method in the development of the case the Driven Cavity. the spatial discretization and the algorithm necessary for the development of this will be detailed. Finally, the results will be discussed, and the pertinent conclusions will be given. We will make an introduction to the field of turbulence that is why in chapter six the Burgers equations will be discretized; two different methods will be studied LES (Large eddy simulation) and DNS (Direct numerical simulation). The results obtained will be compared with the references given by the CTTC.
Aprofundir en la simulació de les equacions fonamentals de la dinàmica de fluids i transferència de calor i massa, així com la seva aplicació en algun cas d’interès per l’estudiant en el camp de l’enginyeria industrial i/o aeronàutica. Depenen del background de l’estudiant en la resolució multidimensional de les equacions de Navier-Stokes treballat en assignatures del seu màster, es farà una tutela personalitzada que li permeti avançar en la modelitzacióó de situacions més complexes d’acord amb els seus interessos. Així, l’estudiant podrà aprofundir en el desenvolupament de codis de simulació de fluxos laminars en geometries complexes (malles no estructurades), fluxos turbulents (simulació directe de la turbulència i models de Large Eddy Simulation), fluxos bifàsics (sòlid-líquid o líquid-vapor), medis participants a la radiació, combustió, interacció sòlid-fluid, etc. El codis es desenvoluparan utilitzant preferentment tècniques de volums finits i en llenguatge de programació C o C++. També es considerarà la possibilitat de crear subrutines per ser implementades en codis de propòsit general (e.g. el codi obert OpemFoam, el codi TermoFluids, etc.). L’estudiant tindrà també la possibilitat d’orientar el seu TFM a aplicacions específiques en el camp de l’optimització de sistemes i equips termo-fluídics i aeronàutics per tal d’aconseguir la seva optimització, i.e. màxima eficiència energètica amb el mínim cost i impacte ambiental. Aquí l’estudiant podrà proposar, d’acord amb els professors, aquelles situacions que consideri més adients als seus interessos. Com a possibles casos d’aplicació citarem: En base al treball de simulació desenvolupat, una segona part del TFG estarà dirigida a aplicacions específiques en el camp de l’optimització de sistemes i equips termo-fluídics i aeronàutics per tal d’aconseguir la seva optimització, i.e. màxima eficiència energètica amb el mínim cost i impacte ambiental. Aquí l’estudiant podrà proposar, d’acord amb els professors, aquelles situacions que consideri més adients als seus interessos. Com a possibles casos d’aplicació citarem: Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to aerodynamics of airfoils shaped bodies.Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to heating, ventilating, air conditioning and refrigeration (HVAC & R). Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to combustion processes for aeronautic and aerospace applications. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to turbomachinery. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to solar thermal collectors for low and middle temperatures. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to thermal energy storage in industrial applications. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to analysis of the power block in thermoelectric plants. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to compact heat exchangers using micro-channels and fin-and-tube systems. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to bioengineering applications. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to refrigeration of electric and electronic components. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to solid-fluid interaction. El títol final del TFM dependrà de l’aplicació final escollida. El llistat anterior és representatiu de com podria quedar el títol final.
2019-01-07T18:36:19ZOrtega Varas, Boris MarcialThe main objective of this work is the development of different programs to learn and verify computational fluid dynamics problems which are governed by the Navier-Stokes equations. The document will be divided into different chapters in which we will detail the procedures performed. During the first chapter there will be an introduction on computational fluid dynamics problems, as the basic requirements to deal with this type of cases, as well as the limits that will be encountered during the development of these. In the second chapter there will be a brief introduction about the necessary theory which will be of great help during the development of the case studies. The convection-diffusion equations will be studied in the third chapter, which will be discretized for the development of the different cases. In this chapter we will also introduce the concept of Finite volume method that will be a fundamental part of this work. Finally, we will see the different numerical schemes that can be implemented, as well as the different solvers. During the fourth chapter the different cases will be presented, such as the Transient Conduction problem, the Diagonal flow and the Smith Hutton problem, which will be developed and commented. In the fifth chapter we will introduce in the Fractional Step Method, we will see the different steps to follow for the implementation of this method in the development of the case the Driven Cavity. the spatial discretization and the algorithm necessary for the development of this will be detailed. Finally, the results will be discussed, and the pertinent conclusions will be given. We will make an introduction to the field of turbulence that is why in chapter six the Burgers equations will be discretized; two different methods will be studied LES (Large eddy simulation) and DNS (Direct numerical simulation). The results obtained will be compared with the references given by the CTTC.Computational study for the numerical resolution of thermal and fluid dynamic problems
http://hdl.handle.net/2117/126238
Computational study for the numerical resolution of thermal and fluid dynamic problems
Navas Prada, Cesar David
Since the development of the mechanical, aeronautical, and other industries along the computational technologies advances, a crucial field in engineering has studied the behavior and properties of fluids involved in engineering. During the last years this has led to advanced studies of the numerical resolution of Navier-Stokes equations, a relevant step to understand the fluid dynamics. Discretization methods, numerical schemes and solver methods has been developed; however, the application for specific cases and its effectivity or convenience for each case need to be thoroughly studied. Through the study of the convection-diffusion equation and the fractional step method and further implementation in thermal and fluid dynamic problems, this document analyzes the computational effects of these three components of CFD. Results shows how finer mesh sizes and discretization methods give a better performance in cases when the convective flows are higher than the diffusive flows. Contrarily, in relatively equal convective-diffusive flows the mesh size does not have a great influence, although finer meshes will have more precise results and better convergence features. Moreover, results show how numerical schemes can influence on the computational cost and time, especially for high-order schemes where stability is an important parameter to be aware. Finally, the analysis of solver methods demonstrates that the correct use and selection can be an important engineering decision because it could optimize the computational cost of the CFD studies applied to real fluid analysis.
Aprofundir en la simulació de les equacions fonamentals de la dinàmica de fluids i transferència de calor i massa, així com la seva aplicació en algun cas d’interès per l’estudiant en el camp de l’enginyeria industrial i/o aeronàutica. Depenen del background de l’estudiant en la resolució multidimensional de les equacions de Navier-Stokes treballat en assignatures del seu màster, es farà una tutela personalitzada que li permeti avançar en la modelitzacióó de situacions més complexes d’acord amb els seus interessos. Així, l’estudiant podrà aprofundir en el desenvolupament de codis de simulació de fluxos laminars en geometries complexes (malles no estructurades), fluxos turbulents (simulació directe de la turbulència i models de Large Eddy Simulation), fluxos bifàsics (sòlid-líquid o líquid-vapor), medis participants a la radiació, combustió, interacció sòlid-fluid, etc. El codis es desenvoluparan utilitzant preferentment tècniques de volums finits i en llenguatge de programació C o C++. També es considerarà la possibilitat de crear subrutines per ser implementades en codis de propòsit general (e.g. el codi obert OpemFoam, el codi TermoFluids, etc.). L’estudiant tindrà també la possibilitat d’orientar el seu TFM a aplicacions específiques en el camp de l’optimització de sistemes i equips termo-fluídics i aeronàutics per tal d’aconseguir la seva optimització, i.e. màxima eficiència energètica amb el mínim cost i impacte ambiental. Aquí l’estudiant podrà proposar, d’acord amb els professors, aquelles situacions que consideri més adients als seus interessos. Com a possibles casos d’aplicació citarem: En base al treball de simulació desenvolupat, una segona part del TFG estarà dirigida a aplicacions específiques en el camp de l’optimització de sistemes i equips termo-fluídics i aeronàutics per tal d’aconseguir la seva optimització, i.e. màxima eficiència energètica amb el mínim cost i impacte ambiental. Aquí l’estudiant podrà proposar, d’acord amb els professors, aquelles situacions que consideri més adients als seus interessos. Com a possibles casos d’aplicació citarem: Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to aerodynamic design of wind turbine blades. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to aerodynamics of different structures. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to combustors in the industry. Director C.D.Perez-Segarra; Co-director: A.OlivaAdvanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to Concentrated Solar Power (central receivers, parabolic trough collectors, linear Fresnel reflectors, parabolic dishes)Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to thermal energy storage in concentrated solar power plants. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to thermal energy storage in buildings and district heating. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to thermal and fluid-dynamic behaviour of bioclimatic buildings. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to solar absorption machines. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to thermal dissipation systems for applications with photovoltaic concentration. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to buoyancy driven flows in cavities. Advanced study for the computational resolution of conservation equations of mass, momentum and energy. Application to high performance computing. El títol final del TFM dependrà de l’aplicació final escollida. El llistat anterior és representatiu de com podria quedar el títol final.
2019-01-07T17:57:01ZNavas Prada, Cesar DavidSince the development of the mechanical, aeronautical, and other industries along the computational technologies advances, a crucial field in engineering has studied the behavior and properties of fluids involved in engineering. During the last years this has led to advanced studies of the numerical resolution of Navier-Stokes equations, a relevant step to understand the fluid dynamics. Discretization methods, numerical schemes and solver methods has been developed; however, the application for specific cases and its effectivity or convenience for each case need to be thoroughly studied. Through the study of the convection-diffusion equation and the fractional step method and further implementation in thermal and fluid dynamic problems, this document analyzes the computational effects of these three components of CFD. Results shows how finer mesh sizes and discretization methods give a better performance in cases when the convective flows are higher than the diffusive flows. Contrarily, in relatively equal convective-diffusive flows the mesh size does not have a great influence, although finer meshes will have more precise results and better convergence features. Moreover, results show how numerical schemes can influence on the computational cost and time, especially for high-order schemes where stability is an important parameter to be aware. Finally, the analysis of solver methods demonstrates that the correct use and selection can be an important engineering decision because it could optimize the computational cost of the CFD studies applied to real fluid analysis.