Màster universitari en Enginyeria Aeronàuticahttp://hdl.handle.net/2117/777542019-02-22T18:15:48Z2019-02-22T18:15:48ZStudy of the model order reduction of an entire aircraft configurationLajas Contreras, Fabiánhttp://hdl.handle.net/2117/1160702019-02-06T02:48:31Z2018-04-09T10:22:04ZStudy of the model order reduction of an entire aircraft configuration
Lajas Contreras, Fabián
The primary aim of this study is to understand and implement in a computer program the basic theory underlying model order reduction of Finite Element (FE) structural models. More concretely, attention is focused on modal analysis via substructuring techniques, and the interest lies in comparing the performance of such substructuring methods with the standard modal analysis of linear elastodynamic FE models. The method is applied to 3 aeronautical structures, ranging in complexity from a simple truss structure to a complete airframe of a private jet aircraft. For the truss structure, all required operations are carried out with a Matlab code developed by the author. For the other two structures, the finite element information ( mass and stiffness matrices ) is retrieved from an open source FE software called KRATOS, and then processed by a Matlab script in order to determine the vibrational modes and the natural frequencies. It should be highlighted that the construction of the geometric models of the three tested airframes have been also developed, from scratch, by the author.
2018-04-09T10:22:04ZLajas Contreras, FabiánStudy of earth observation business models by means of the Business Model Canvas methodologyGómez Ferreras, Flàviahttp://hdl.handle.net/2117/1089322019-02-13T02:46:11Z2017-10-20T13:58:25ZStudy of earth observation business models by means of the Business Model Canvas methodology
Gómez Ferreras, Flàvia
Idenfity two big players in Earth Observation marketStudy in detail each case study and see how they operate applying the business model CANVAS Identify the case study peculiarities that make them succeed in the market Propose the successful factors that should be taken into account in this market according the case studies
This project tries to study and compare two big players in the Earth Observation market to identify their main peculiarities that make them succeed in the market.
2017-10-20T13:58:25ZGómez Ferreras, FlàviaIdenfity two big players in Earth Observation marketStudy in detail each case study and see how they operate applying the business model CANVAS Identify the case study peculiarities that make them succeed in the market Propose the successful factors that should be taken into account in this market according the case studiesStudy of unstructured finite volume methods for the solution of the Euler equationsPadilla Montero, Ivanhttp://hdl.handle.net/2117/1062252019-01-24T11:38:19Z2017-07-07T09:23:56ZStudy of unstructured finite volume methods for the solution of the Euler equations
Padilla Montero, Ivan
This work deals with the numerical solution of inviscid compressible flows by means of the Euler equations. It focuses on the description of an unstructured finite volume method for these equations and its numerical application to solve external, two-dimensional steady problems.
On first place, the standard formulation of the Euler equations is presented, reviewing the most important properties that characterize their mathematical behavior. The hyperbolic nature of the system is discussed, emphasizing the fundamental importance of taking into account the propagation of information in the flow field in order to obtain physically meaningful solutions, which also leads to a description of how the boundary conditions should be treated to avoid undesirable behaviors. To complete this presentation, a dimensionless form of the equations is derived, which provides substantial advantages to the numerical solution.
The attention is then focused on the unstructured finite volume formulation, which is based on a central approximation of the fluxes at the volume interfaces. According to the need of properly accounting for the propagation of characteristic variables, the requirement to add artificial dissipation terms to the central discretization is justified. Then, two classical forms of artificial dissipation are defined, namely, the first-order upwind scheme and the Jameson-Schmidt-Turkel high-order model, detailing how to adapt the formulation of the dissipation terms to an unstructured mesh. Eventually, the time integration of the spatially discretized equations is assessed.
With the objective of performing a practical implementation of the theoretical concepts studied, the development of a numerical solver is presented next, briefly describing the program structure and characteristics. After that, five different test cases are solved with the purpose of validating the code, consisting on two transonic flows around a NACA0012 airfoil and three supersonic examples, respectively around a NACA0012 airfoil, a double wedge airfoil and circular cylinder. The results obtained for each case are then analyzed and compared against reference solutions, showing an overall satisfactory performance of the solver developed.
Development of an unstructured finite volume solver for the numerical solution of high-speed flows using the Euler equation set.
2017-07-07T09:23:56ZPadilla Montero, IvanThis work deals with the numerical solution of inviscid compressible flows by means of the Euler equations. It focuses on the description of an unstructured finite volume method for these equations and its numerical application to solve external, two-dimensional steady problems.
On first place, the standard formulation of the Euler equations is presented, reviewing the most important properties that characterize their mathematical behavior. The hyperbolic nature of the system is discussed, emphasizing the fundamental importance of taking into account the propagation of information in the flow field in order to obtain physically meaningful solutions, which also leads to a description of how the boundary conditions should be treated to avoid undesirable behaviors. To complete this presentation, a dimensionless form of the equations is derived, which provides substantial advantages to the numerical solution.
The attention is then focused on the unstructured finite volume formulation, which is based on a central approximation of the fluxes at the volume interfaces. According to the need of properly accounting for the propagation of characteristic variables, the requirement to add artificial dissipation terms to the central discretization is justified. Then, two classical forms of artificial dissipation are defined, namely, the first-order upwind scheme and the Jameson-Schmidt-Turkel high-order model, detailing how to adapt the formulation of the dissipation terms to an unstructured mesh. Eventually, the time integration of the spatially discretized equations is assessed.
With the objective of performing a practical implementation of the theoretical concepts studied, the development of a numerical solver is presented next, briefly describing the program structure and characteristics. After that, five different test cases are solved with the purpose of validating the code, consisting on two transonic flows around a NACA0012 airfoil and three supersonic examples, respectively around a NACA0012 airfoil, a double wedge airfoil and circular cylinder. The results obtained for each case are then analyzed and compared against reference solutions, showing an overall satisfactory performance of the solver developed.Study of the boundary layer flow control using synthetic jets by means of spectro-consistent discretizationsDuran Perez, Davidhttp://hdl.handle.net/2117/1058712019-01-24T11:38:19Z2017-06-26T13:54:35ZStudy of the boundary layer flow control using synthetic jets by means of spectro-consistent discretizations
Duran Perez, David
This report presents a study of the interaction of AFC (specifically, synthetic jets)
with the laminar boundary layer of a NACA 0012 airfoil.
First of all, in order to understand the phenomenology of Navier-Stokes equations,
a spectro-consistent Computational Fluid Dynamics (CFD) code has been
developed from scratch. By using a spectro-consistent discretization, the fundamental
symmetry properties of the underlying differential operators are preserved.
This code also helps to understand how the energy is transported from big to small
scales.
After solving a paradigmatic problem (TGV) using the aforementioned code, a
mature CFD code (Alya) is used to simulate the flow around the NACA 0012 airfoil.
Alya software also uses a spectro-consistent code but in Finite Element Method
(FEM).
Once the reference cases are solved for different angles of attack, a boundary
condition representing an idealized synthetic jet is implemented. A systematic
parametrization of the synthetic jet has been performed in order to assess the level
of flow control in the boundary layer.
Results demonstrate that, by selecting a correct combination of actuator frequency
and momentum coefficient, the lift coefficient increases while the drag coefficient
decreases producing a better lift-to-drag ratio. This aerodynamic improvement
implies that a better circulation control is achieved, less noise is produced and
less fuel consumption is required.
It is also worth noting that, for high angles of attack, it is necessary to perform
3D flow simulations in order to capture the entire physics of the problem
Synthetic jets have emerged as fluid devices for active control boundary layer separation and turbulence. In the proposed TFM the interaction of a modelled synthetic h¡jet with a laminar boundary layer will be investigated numerically using a incompressible Navier–Stokes solver.The main goals of the present TFM are oriented to:-The numerical simulation of synthetic jets into a laminar boundary layer and, -to perform a systematic parametrisation of the synthetic jet in order to characterise the level of flow control in the boundary layer.
2017-06-26T13:54:35ZDuran Perez, DavidThis report presents a study of the interaction of AFC (specifically, synthetic jets)
with the laminar boundary layer of a NACA 0012 airfoil.
First of all, in order to understand the phenomenology of Navier-Stokes equations,
a spectro-consistent Computational Fluid Dynamics (CFD) code has been
developed from scratch. By using a spectro-consistent discretization, the fundamental
symmetry properties of the underlying differential operators are preserved.
This code also helps to understand how the energy is transported from big to small
scales.
After solving a paradigmatic problem (TGV) using the aforementioned code, a
mature CFD code (Alya) is used to simulate the flow around the NACA 0012 airfoil.
Alya software also uses a spectro-consistent code but in Finite Element Method
(FEM).
Once the reference cases are solved for different angles of attack, a boundary
condition representing an idealized synthetic jet is implemented. A systematic
parametrization of the synthetic jet has been performed in order to assess the level
of flow control in the boundary layer.
Results demonstrate that, by selecting a correct combination of actuator frequency
and momentum coefficient, the lift coefficient increases while the drag coefficient
decreases producing a better lift-to-drag ratio. This aerodynamic improvement
implies that a better circulation control is achieved, less noise is produced and
less fuel consumption is required.
It is also worth noting that, for high angles of attack, it is necessary to perform
3D flow simulations in order to capture the entire physics of the problemProject of monitoring the wind tunnel of the ETSEIAT’s Aerospace Engineering laboratory (Software)Villanueva Pujol, Oriolhttp://hdl.handle.net/2117/990532019-01-24T11:38:19Z2017-01-11T17:20:24ZProject of monitoring the wind tunnel of the ETSEIAT’s Aerospace Engineering laboratory (Software)
Villanueva Pujol, Oriol
The ETSEIAT’s aerospace engineering laboratory’s wind tunnel used to vary
its airflow speed thanks to a potentiometer and the air properties were
manually measured. Hence, monitoring the tunnel’s behaviour was the goal.
This aim was to be achieved by making use of an Arduino, the proper sensors
and genuine software in order to have better control of the velocity and to
gather data automatically.
Taking this into consideration, a Matlab code which interacts with Arduino
was created. It collects the temperature, the atmospheric pressure and the
differential pressure at the nozzle, and saves and plots in real time all the data.
Moreover, it calculates and stores the air speed as well as comparing it to the
desired velocity so as to obtain the error, which is aimed to be minimized, and
is later on processed by a PID controller.
After mounting the whole system with the appropriate hardware, the sensors
were tested and some of them re-calibrated to reduce, as much as possible, all
the uncertainties and get a simultaneously efficient, accurate and robust
system.
Once all the difficulties have been solved it is possible to say that the project
has finally been carried out with a greatly satisfactory result and it will be a
useful tool for the university.
Monitoritzar i automatitzar el funcionament del túnel de vent del laboratori d'Enginyeria Aeroespacial. Es vol substituir el funcionament manual actual per un d'automatitzat, de forma que es puguin programar assajos i adquirir les dades de forma automàtica
2017-01-11T17:20:24ZVillanueva Pujol, OriolThe ETSEIAT’s aerospace engineering laboratory’s wind tunnel used to vary
its airflow speed thanks to a potentiometer and the air properties were
manually measured. Hence, monitoring the tunnel’s behaviour was the goal.
This aim was to be achieved by making use of an Arduino, the proper sensors
and genuine software in order to have better control of the velocity and to
gather data automatically.
Taking this into consideration, a Matlab code which interacts with Arduino
was created. It collects the temperature, the atmospheric pressure and the
differential pressure at the nozzle, and saves and plots in real time all the data.
Moreover, it calculates and stores the air speed as well as comparing it to the
desired velocity so as to obtain the error, which is aimed to be minimized, and
is later on processed by a PID controller.
After mounting the whole system with the appropriate hardware, the sensors
were tested and some of them re-calibrated to reduce, as much as possible, all
the uncertainties and get a simultaneously efficient, accurate and robust
system.
Once all the difficulties have been solved it is possible to say that the project
has finally been carried out with a greatly satisfactory result and it will be a
useful tool for the university.Study of the optimal location of wing sensors using model-order reductionBelmonte Lauroba, Marchttp://hdl.handle.net/2117/978002019-02-06T02:06:17Z2016-12-05T16:26:40ZStudy of the optimal location of wing sensors using model-order reduction
Belmonte Lauroba, Marc
The overall goal of this work is to numerically determine the optimal location of sensors for predicting the vibration behavior of a wing. The methodology to achieve this goal will be to construct, using as starting point finite element simulations, a reduced-order model able to capture the essential vibrational characteristic of the wing.
2016-12-05T16:26:40ZBelmonte Lauroba, MarcStudy of the optimum fleet for a LCC (Low-Cost-Carrier)Durán Gómez, Núriahttp://hdl.handle.net/2117/977952019-01-24T11:38:19Z2016-12-05T15:47:29ZStudy of the optimum fleet for a LCC (Low-Cost-Carrier)
Durán Gómez, Núria
2016-12-05T15:47:29ZDurán Gómez, NúriaProyecto de un UAV de autonomía infinitaSans Fàbregas, Marchttp://hdl.handle.net/2117/977902019-01-24T11:38:19Z2016-12-05T15:29:30ZProyecto de un UAV de autonomía infinita
Sans Fàbregas, Marc
El objetivo es diseñar un UAV (unmanned air vehicle) que, alimentado mediante células
fotovoltaicas, sea capaz de volar 24 horas 7 días a la semana
2016-12-05T15:29:30ZSans Fàbregas, MarcEl objetivo es diseñar un UAV (unmanned air vehicle) que, alimentado mediante células
fotovoltaicas, sea capaz de volar 24 horas 7 días a la semanaStudy for the numerical resolution of combustion phenomena in burnersGodayol Capdevila, Èrichttp://hdl.handle.net/2117/977812019-01-24T11:38:19Z2016-12-05T13:52:04ZStudy for the numerical resolution of combustion phenomena in burners
Godayol Capdevila, Èric
Combustion is a complex phenomenon of interest that combines chemical reactions and turbulent flows. Resolution of both problems is a difficult task. On the one hand, chemical reactions introduce a large amount of species with different properties and small temporal scales due to chemical kinetics. On the other hand, turbulent flows imply a large span of spatial scales.
Different models are commonly applied to reduce these requirements. Chemical reactions can be modeled with reduced chemical mechanisms. These have less species and reactions than complex ones, but are able to describe the combustion. Turbulence is modeled by means of Large Eddy Simulation (LES), which filters the Navier-Stokes equations spatially. Thus, the small scales of the flow are filtered out. These ones are modeled through a turbulent viscosity.
The present study focuses on the theoretical basis required to model combustion phenomena. First, the algorithm used to solve variable density flows is presented. It uses the low-Mach equations, which are discretized in terms of the convective-diffusive equation. Its resolution is achieved by applying an algorithm based on a projection method, using a predictor-corrector step. Then the algorithm used to solve chemical kinetics is detailed. In this case, the Arrhenius law is used for laminar flames and a two equations model for turbulent flows. The latter introduces an eddy dissipation model besides the Arrhenius law to include the effect of the filtered spatial scales in LES simulations. The study concludes with an introduction to LES. The spatial filter introduces some additional terms in the governing equations. These ones are modeled through a turbulent viscosity. Different models to evaluate the turbulent viscosity can be found in the literature. In the present study the Smagorinsky model is used.
Different tests are carried out to verify the results. The lid driven cavity and the heated cavity tests show that accurate results are obtained for incompressible and variable density non-reacting flows. A laminar methane/air flame test is used to verify the laminar chemical algorithm. Additionally, the influence of chemical mechanism on the flame behavior is shown. Finally, a three dimensional propane burner is simulated to study the turbulent combustion phenomena and verify the interaction between turbulent combustion chemical algorithm and LES.
An additional test is used to assess the speedup of the parallelization implemented and also to check its performance.
2016-12-05T13:52:04ZGodayol Capdevila, ÈricCombustion is a complex phenomenon of interest that combines chemical reactions and turbulent flows. Resolution of both problems is a difficult task. On the one hand, chemical reactions introduce a large amount of species with different properties and small temporal scales due to chemical kinetics. On the other hand, turbulent flows imply a large span of spatial scales.
Different models are commonly applied to reduce these requirements. Chemical reactions can be modeled with reduced chemical mechanisms. These have less species and reactions than complex ones, but are able to describe the combustion. Turbulence is modeled by means of Large Eddy Simulation (LES), which filters the Navier-Stokes equations spatially. Thus, the small scales of the flow are filtered out. These ones are modeled through a turbulent viscosity.
The present study focuses on the theoretical basis required to model combustion phenomena. First, the algorithm used to solve variable density flows is presented. It uses the low-Mach equations, which are discretized in terms of the convective-diffusive equation. Its resolution is achieved by applying an algorithm based on a projection method, using a predictor-corrector step. Then the algorithm used to solve chemical kinetics is detailed. In this case, the Arrhenius law is used for laminar flames and a two equations model for turbulent flows. The latter introduces an eddy dissipation model besides the Arrhenius law to include the effect of the filtered spatial scales in LES simulations. The study concludes with an introduction to LES. The spatial filter introduces some additional terms in the governing equations. These ones are modeled through a turbulent viscosity. Different models to evaluate the turbulent viscosity can be found in the literature. In the present study the Smagorinsky model is used.
Different tests are carried out to verify the results. The lid driven cavity and the heated cavity tests show that accurate results are obtained for incompressible and variable density non-reacting flows. A laminar methane/air flame test is used to verify the laminar chemical algorithm. Additionally, the influence of chemical mechanism on the flame behavior is shown. Finally, a three dimensional propane burner is simulated to study the turbulent combustion phenomena and verify the interaction between turbulent combustion chemical algorithm and LES.
An additional test is used to assess the speedup of the parallelization implemented and also to check its performance.