Grau en Enginyeria en Vehicles Aeroespacials (Pla 2010)http://hdl.handle.net/2099.1/257252024-03-29T06:33:56Z2024-03-29T06:33:56ZStudy of the design of a bycicle frame by comparing different topology optimization softwareCasas Martínez, Álvarohttp://hdl.handle.net/2117/4051702024-03-22T13:20:55Z2024-03-22T13:10:53ZStudy of the design of a bycicle frame by comparing different topology optimization software
Casas Martínez, Álvaro
Topology optimization is one of the most efficient numerical approaches to obtain new lightweight structures, aiming to generate unintuitive holes in the less stressed areas. Besides, such complex geometries can nowadays be obtained in reality with the constant improvement of additive manufacturing. However, the capacity to obtain a very competitive design, balanced with a relative short computational time, is an important challenge. Therefore, the aim of this work is to test different topology optimization software and compare their performance, along with the Swan open-source GitHub repository. Different benchmark problems are analyzed, as well as a final example consisting of the design of a bicycle frame. In general, the results have shown that topology optimization commercial software are a useful and functional technology. Nevertheless, it still has a lot of room for improvement, given that certain geometries and restrictions can cause problems that directly affect the integrity of the part. Regarding the Swan case,it has also a great room for improvement in some aspects, such as the time, but, despite of using a significant amount of time for their simulations, it was proved that is a very robust software.
2024-03-22T13:10:53ZCasas Martínez, ÁlvaroTopology optimization is one of the most efficient numerical approaches to obtain new lightweight structures, aiming to generate unintuitive holes in the less stressed areas. Besides, such complex geometries can nowadays be obtained in reality with the constant improvement of additive manufacturing. However, the capacity to obtain a very competitive design, balanced with a relative short computational time, is an important challenge. Therefore, the aim of this work is to test different topology optimization software and compare their performance, along with the Swan open-source GitHub repository. Different benchmark problems are analyzed, as well as a final example consisting of the design of a bicycle frame. In general, the results have shown that topology optimization commercial software are a useful and functional technology. Nevertheless, it still has a lot of room for improvement, given that certain geometries and restrictions can cause problems that directly affect the integrity of the part. Regarding the Swan case,it has also a great room for improvement in some aspects, such as the time, but, despite of using a significant amount of time for their simulations, it was proved that is a very robust software.Study for the computational resolution of conservation equations of mass, momentum and energy. Benchmark solutions of heat transfer and fluid flow problemsGuillén Bautista, Héctorhttp://hdl.handle.net/2117/4051662024-03-22T12:42:54Z2024-03-22T12:37:30ZStudy for the computational resolution of conservation equations of mass, momentum and energy. Benchmark solutions of heat transfer and fluid flow problems
Guillén Bautista, Héctor
This bachelor’s thesis focuses on the resolution of the mass, momentum and energy conservation equations through the resolution of several heat transfer and fluid flow benchmark problems. Its resolution is used as in introduction to the topic of computational fluid dynamics. To solve them, a progressive difficulty approach is taken, firstly introducing heat conduction, then convection through the general convection-diffusion equation and the eventual the resolution of the (incompressible) Navier-Stokes equations, finally adding an introduction into turbulent models and turbulence. Each one of the listed topics has its own chapter, in which the relevant equation is introduced theoretically and mathematically and solved using the finite volume method. The resolution of each code is done by developing a self-written code in C++. The aim of these benchmark cases is to reproduce and analyze the results for a further understanding of fluid dynamics and to verify the code. The verification cases for the heat conduction and convection-diffusion equation resolution focuses in a one-dimensional and two-dimensional cases, that help understand and characterize both phenomena. Also, studies are performed analyzing the effect of several parameters and schemes. For the resolution of the Navier-Stokes equation, the fractional step method is applied to solve said equations, that are verified with classical scenarios like the lid-driven and differentially heated cavities, flow between parallel plates and the square cylinder problem. Each one of this verification cases characterizes one specific topic of the Navier-Stokes equation: its resolution, resolution of free convection and introduction of geometries. The thesis culminates with the resolution of Burger’s equation in Fourier space, which is used as an introduction to turbulence and LES modelling.
2024-03-22T12:37:30ZGuillén Bautista, HéctorThis bachelor’s thesis focuses on the resolution of the mass, momentum and energy conservation equations through the resolution of several heat transfer and fluid flow benchmark problems. Its resolution is used as in introduction to the topic of computational fluid dynamics. To solve them, a progressive difficulty approach is taken, firstly introducing heat conduction, then convection through the general convection-diffusion equation and the eventual the resolution of the (incompressible) Navier-Stokes equations, finally adding an introduction into turbulent models and turbulence. Each one of the listed topics has its own chapter, in which the relevant equation is introduced theoretically and mathematically and solved using the finite volume method. The resolution of each code is done by developing a self-written code in C++. The aim of these benchmark cases is to reproduce and analyze the results for a further understanding of fluid dynamics and to verify the code. The verification cases for the heat conduction and convection-diffusion equation resolution focuses in a one-dimensional and two-dimensional cases, that help understand and characterize both phenomena. Also, studies are performed analyzing the effect of several parameters and schemes. For the resolution of the Navier-Stokes equation, the fractional step method is applied to solve said equations, that are verified with classical scenarios like the lid-driven and differentially heated cavities, flow between parallel plates and the square cylinder problem. Each one of this verification cases characterizes one specific topic of the Navier-Stokes equation: its resolution, resolution of free convection and introduction of geometries. The thesis culminates with the resolution of Burger’s equation in Fourier space, which is used as an introduction to turbulence and LES modelling.Study of the F-35 Lightning II structure and reproduction of a 1:12 scale modelIborra De Toledo, Guillemhttp://hdl.handle.net/2117/4049802024-03-19T17:40:27Z2024-03-19T17:36:22ZStudy of the F-35 Lightning II structure and reproduction of a 1:12 scale model
Iborra De Toledo, Guillem
The Lockheed Martin F-35 Lightning II stands as an iconic American family of single-seat, single-engine, all-weather stealth multi-role combat aircraft. Developed during the ’80s and ’90s and finally introduced in 2015, it was designed with the capability to excel in air superiority and strike missions. The F-35 represents a cutting-edge advancement in aerospace technology. This thesis meticulously examines the internal structure of the F-35A variant by delving into relevant available literature. The primary focus involves designing the model components, utilising both 2D and 3D design tools. Through an analysis of blueprints and cutaways, the aim is to achieve a deep understanding of the airframe design details. The ultimate goal is the replication of the F-35A’s structure through the construction of a 1:12 scale model. The final structure of the model is robust while being lightweight. The usage of a combination of Balsa and Poplar wood has made the scale aircraft beautiful, but most importantly, ensures a balance of strength and lightness. Undoubtedly, this process reflects a significant task that engineers may encounter in their professional careers, emphasising the importance of hands-on design and final assembly. An environmental impact assessment has been made considering both the materials utilised and the power consumption throughout the whole thesis. During the development of the project, sustainable practices have been maintained, to the extent possible given the nature of the work, aiming to minimise the ecological footprint. This research aims to contribute to the broader understanding of aerospace technology, providing insights into the complexities of airframe design and the practical application of advanced modelling tools in replicating aircraft structures.
2024-03-19T17:36:22ZIborra De Toledo, GuillemThe Lockheed Martin F-35 Lightning II stands as an iconic American family of single-seat, single-engine, all-weather stealth multi-role combat aircraft. Developed during the ’80s and ’90s and finally introduced in 2015, it was designed with the capability to excel in air superiority and strike missions. The F-35 represents a cutting-edge advancement in aerospace technology. This thesis meticulously examines the internal structure of the F-35A variant by delving into relevant available literature. The primary focus involves designing the model components, utilising both 2D and 3D design tools. Through an analysis of blueprints and cutaways, the aim is to achieve a deep understanding of the airframe design details. The ultimate goal is the replication of the F-35A’s structure through the construction of a 1:12 scale model. The final structure of the model is robust while being lightweight. The usage of a combination of Balsa and Poplar wood has made the scale aircraft beautiful, but most importantly, ensures a balance of strength and lightness. Undoubtedly, this process reflects a significant task that engineers may encounter in their professional careers, emphasising the importance of hands-on design and final assembly. An environmental impact assessment has been made considering both the materials utilised and the power consumption throughout the whole thesis. During the development of the project, sustainable practices have been maintained, to the extent possible given the nature of the work, aiming to minimise the ecological footprint. This research aims to contribute to the broader understanding of aerospace technology, providing insights into the complexities of airframe design and the practical application of advanced modelling tools in replicating aircraft structures.Estudi de la manufactura de peces 3D de fibra de carboni aplicades al sector de dronsLópez i Ruiz, Mireiahttp://hdl.handle.net/2117/4047352024-03-15T13:30:23Z2024-03-15T13:26:00ZEstudi de la manufactura de peces 3D de fibra de carboni aplicades al sector de drons
López i Ruiz, Mireia
En el present projecte s’han analitzat les diferents tècniques existents per la fabricació de peces de fibra de carboni i se n’ha escollit la més adient (mitjançant el mètode de decisió OWA) en funció dels objectius de que fos econòmicament accessible, tècnicament senzilla, que requerís pocs equips i que es poguessin emprar motlles impresos amb impressora 3D. Un cop determinat el mètode, s’ha definit a nivell teòric el procediment associat a aquest i se n’han realitzat 6 peces a nivell pràctic (4 d’elles aplicades al sector de drons). En total, s’han obtingut 5 peces tècnicament viables i se n’ha analitzat els acabats superficials i estructurals. També s’han emprat 3 d’aquestes peces per actualitzar un dron de plàstic a un dron de fibra de carboni. Finalment, s’ha realitzat un assaig d’impacte per determinar la resiliència del material fabricat. S’ha arribat a la conclusió de que la laminació en humit és un mètode viable per a la fabricació de peces aplicades al sector de drons tot i no obtenir els millors resultats superficials i tenir diverses limitacions geomètriques. Son per aquest motius que seria interesant comparar aquest mètode amb la infusió per buit (RTI), ja que podria oferir millors resultats.
2024-03-15T13:26:00ZLópez i Ruiz, MireiaEn el present projecte s’han analitzat les diferents tècniques existents per la fabricació de peces de fibra de carboni i se n’ha escollit la més adient (mitjançant el mètode de decisió OWA) en funció dels objectius de que fos econòmicament accessible, tècnicament senzilla, que requerís pocs equips i que es poguessin emprar motlles impresos amb impressora 3D. Un cop determinat el mètode, s’ha definit a nivell teòric el procediment associat a aquest i se n’han realitzat 6 peces a nivell pràctic (4 d’elles aplicades al sector de drons). En total, s’han obtingut 5 peces tècnicament viables i se n’ha analitzat els acabats superficials i estructurals. També s’han emprat 3 d’aquestes peces per actualitzar un dron de plàstic a un dron de fibra de carboni. Finalment, s’ha realitzat un assaig d’impacte per determinar la resiliència del material fabricat. S’ha arribat a la conclusió de que la laminació en humit és un mètode viable per a la fabricació de peces aplicades al sector de drons tot i no obtenir els millors resultats superficials i tenir diverses limitacions geomètriques. Son per aquest motius que seria interesant comparar aquest mètode amb la infusió per buit (RTI), ja que podria oferir millors resultats.Geo-enginyeria aeroespacial. Anàlisi de patrons i impactes socioambientals a escala regionalSánchez Bosch, Martíhttp://hdl.handle.net/2117/4047292024-03-15T12:50:18Z2024-03-15T12:40:52ZGeo-enginyeria aeroespacial. Anàlisi de patrons i impactes socioambientals a escala regional
Sánchez Bosch, Martí
Aquest treball s’ha centrat en l’estudi dels deixants de condensació dels avions (an., contrails), partint de la base que s’empren, de manera potser inconscient, com a mètode de geoenginyeria aeroespacial. La intenció ha estat estudiar si el fenomen dels deixants pot ser motiu d’alarma social, si s’empra de manera anòmala i les conseqüències que té. L’objectiu del treball, doncs, ha consistit a resoldre qüestions relacionades amb l’existència de deixants no susceptibles de ser explicats per condicions climàtiques favorables, les aeronaus que poden estar-hi associades i si, independentment de si tenen relació amb la geoenginyeria, els deixants tenen un impacte en les condicions climàtiques locals. Per a fer-ho, he dividit el treball en dues parts. En primer lloc un apartat teòric, on he realitzat una recerca per a obtenir informació de la literatura referent a la geoenginyeria, als deixants de condensació i les condicions climàtiques que n’afavoreixen l’aparició, a les teories de la conspiració que en els últims temps hi estan relacionades i, finalment, als diferents impactes que presenten, d’acord amb els diferents estudis i referències. En segon lloc, he realitzat una recopilació de dades meteorològiques al llarg de 48 dies. Per una banda prediccions de temperatura per tal de corroborar-ne la predicció en funció de la circulació d’aparells que generin traces de condensació. I per l’altre, un enregistrament d’aparicions de deixants per tal de comprovar l’existència d’accions de geoenginyeria i si coincideixen amb les condicions climàtiques favorables. Els resultats han mostrat que els deixants de condensació no estan relacionats amb pujades de temperatura locals per damunt de les prediccions. D’altra banda, els deixants persistents es donen a unes condicions climàtiques que comporten una davallada de la temperatura respecte de la prevista, de manera anàloga a la que ocasionen les cobertures nuvoloses. En relació amb la documentació de deixants, de 52 casos enregistrats cap correspon a comportament anòmal. Tots els casos coincideixen amb les condicions climàtiques previsibles d’acord amb la teoria dels estudis relacionats i totes les aeronaus associades als deixants documentats són identificables i responen a operacions regulars. La conclusió és que els deixants de condensació no haurien de ser motiu d’alarma social. Són un fenomen físic, derivat d’unes condicions climàtiques concretes, i els resultats desmenteixen tota anomalia. No tenen un impacte local, tot i que sí que contribueixen al canvi climàtic amb la seva aportació al forçant radiatiu global.
2024-03-15T12:40:52ZSánchez Bosch, MartíAquest treball s’ha centrat en l’estudi dels deixants de condensació dels avions (an., contrails), partint de la base que s’empren, de manera potser inconscient, com a mètode de geoenginyeria aeroespacial. La intenció ha estat estudiar si el fenomen dels deixants pot ser motiu d’alarma social, si s’empra de manera anòmala i les conseqüències que té. L’objectiu del treball, doncs, ha consistit a resoldre qüestions relacionades amb l’existència de deixants no susceptibles de ser explicats per condicions climàtiques favorables, les aeronaus que poden estar-hi associades i si, independentment de si tenen relació amb la geoenginyeria, els deixants tenen un impacte en les condicions climàtiques locals. Per a fer-ho, he dividit el treball en dues parts. En primer lloc un apartat teòric, on he realitzat una recerca per a obtenir informació de la literatura referent a la geoenginyeria, als deixants de condensació i les condicions climàtiques que n’afavoreixen l’aparició, a les teories de la conspiració que en els últims temps hi estan relacionades i, finalment, als diferents impactes que presenten, d’acord amb els diferents estudis i referències. En segon lloc, he realitzat una recopilació de dades meteorològiques al llarg de 48 dies. Per una banda prediccions de temperatura per tal de corroborar-ne la predicció en funció de la circulació d’aparells que generin traces de condensació. I per l’altre, un enregistrament d’aparicions de deixants per tal de comprovar l’existència d’accions de geoenginyeria i si coincideixen amb les condicions climàtiques favorables. Els resultats han mostrat que els deixants de condensació no estan relacionats amb pujades de temperatura locals per damunt de les prediccions. D’altra banda, els deixants persistents es donen a unes condicions climàtiques que comporten una davallada de la temperatura respecte de la prevista, de manera anàloga a la que ocasionen les cobertures nuvoloses. En relació amb la documentació de deixants, de 52 casos enregistrats cap correspon a comportament anòmal. Tots els casos coincideixen amb les condicions climàtiques previsibles d’acord amb la teoria dels estudis relacionats i totes les aeronaus associades als deixants documentats són identificables i responen a operacions regulars. La conclusió és que els deixants de condensació no haurien de ser motiu d’alarma social. Són un fenomen físic, derivat d’unes condicions climàtiques concretes, i els resultats desmenteixen tota anomalia. No tenen un impacte local, tot i que sí que contribueixen al canvi climàtic amb la seva aportació al forçant radiatiu global.Study of secondary flow losses in a gas turbine high pressure compressorBrugué Bartolí, Pauhttp://hdl.handle.net/2117/3967122023-11-20T14:30:27Z2023-11-20T14:20:21ZStudy of secondary flow losses in a gas turbine high pressure compressor
Brugué Bartolí, Pau
Assessing entropy generation gives an accurate and reliable data on where pressure and kinetic energy are lost. In this study, the entropy generation on a Raynolds (Re)= 104 flow inside a high pressure compressor (HPC) blade is analyzed. In order to compute this entropy production, Reynolds-averaged Navier Stokes equation of energy and first thermodynamic law have been used to formulate the transport equation for entropy generation. The analysis has been carried out using DNS data previously used in other reports (Ventosa 2020). A differentiation between secondary and primary flow is made by dividing the computational domain into different parts. Turbulence effects are found to be the most important sources of the entropy production in HPC. Secondary flow sources account for 3/4 of the global entropy accumulation. It is found that tip leakage vortex (TLV) and endwall friction are the main sources of this entropy production. However, high peaks in LE and TE are observed as a consequence of high shear stresses and pressure in the entrance, and turbulent mixing, respectively.
2023-11-20T14:20:21ZBrugué Bartolí, PauAssessing entropy generation gives an accurate and reliable data on where pressure and kinetic energy are lost. In this study, the entropy generation on a Raynolds (Re)= 104 flow inside a high pressure compressor (HPC) blade is analyzed. In order to compute this entropy production, Reynolds-averaged Navier Stokes equation of energy and first thermodynamic law have been used to formulate the transport equation for entropy generation. The analysis has been carried out using DNS data previously used in other reports (Ventosa 2020). A differentiation between secondary and primary flow is made by dividing the computational domain into different parts. Turbulence effects are found to be the most important sources of the entropy production in HPC. Secondary flow sources account for 3/4 of the global entropy accumulation. It is found that tip leakage vortex (TLV) and endwall friction are the main sources of this entropy production. However, high peaks in LE and TE are observed as a consequence of high shear stresses and pressure in the entrance, and turbulent mixing, respectively.Implementation of the Taylor-Maccoll equations and CFD simulation of a scramjet engineZurita Sánchez, Davidhttp://hdl.handle.net/2117/3967092023-11-20T14:01:07Z2023-11-20T13:50:13ZImplementation of the Taylor-Maccoll equations and CFD simulation of a scramjet engine
Zurita Sánchez, David
2023-11-20T13:50:13ZZurita Sánchez, DavidPreliminary design of a tailless standard-class sailplaneVillar Vinadé, Albertohttp://hdl.handle.net/2117/3966292023-11-17T14:00:36Z2023-11-17T13:54:15ZPreliminary design of a tailless standard-class sailplane
Villar Vinadé, Alberto
The main objective of the present thesis is to present a preliminary design of a tailless sailplane. The aforementioned sailplane’s class will be standard, which means that the wingspan will be 15 meters and without flaps.
2023-11-17T13:54:15ZVillar Vinadé, AlbertoThe main objective of the present thesis is to present a preliminary design of a tailless sailplane. The aforementioned sailplane’s class will be standard, which means that the wingspan will be 15 meters and without flaps.Study and development of Ardupilot missions for fixed-wingsFalomir Vilà, Marchttp://hdl.handle.net/2117/3966252023-11-17T13:40:18Z2023-11-17T13:34:45ZStudy and development of Ardupilot missions for fixed-wings
Falomir Vilà, Marc
Although Unmanned Aerial Vehicles (UAV) have been developed since the early 20th century, it is only over the last two decades that they have gained prominence in the civilian market. This has opened the doors to a whole new world of possibilities where the UAVs are offering a cheaper, faster and most effective solution. In this project, the first prototype of a fixed wing autonomous UAV is developed to act as a relaying node between a ground station and an other UAV, which is operating Beyond Visual Line Of Sight (BVLOS); thus ensuring connectivity between the two ends of the chain without the use of satellite communications or other complex ground infrastructure. The resulting UAV system is composed of two main parts: the airframe and the avionics. Three sub-systems can also be distinguished in the avionics group, being those the propulsion plant, the autopilot and the communications system; whose common feature is to be 100% Open Source. A functional prototype of the described UAV is built, and both the design parameters of the vehicle and configuration of the autopilot is validated through flight tests. All the design decisions, configuration parameters and building steps are documented in this report. The developed prototype aims demonstrate the viability of an aerial system built out of affordable materials, simple building techniques, and low-cost accessible open source hardware and software; that provides a solution for the rapid and efficient deployment of an airborne system capable of operating BVLOS.
2023-11-17T13:34:45ZFalomir Vilà, MarcAlthough Unmanned Aerial Vehicles (UAV) have been developed since the early 20th century, it is only over the last two decades that they have gained prominence in the civilian market. This has opened the doors to a whole new world of possibilities where the UAVs are offering a cheaper, faster and most effective solution. In this project, the first prototype of a fixed wing autonomous UAV is developed to act as a relaying node between a ground station and an other UAV, which is operating Beyond Visual Line Of Sight (BVLOS); thus ensuring connectivity between the two ends of the chain without the use of satellite communications or other complex ground infrastructure. The resulting UAV system is composed of two main parts: the airframe and the avionics. Three sub-systems can also be distinguished in the avionics group, being those the propulsion plant, the autopilot and the communications system; whose common feature is to be 100% Open Source. A functional prototype of the described UAV is built, and both the design parameters of the vehicle and configuration of the autopilot is validated through flight tests. All the design decisions, configuration parameters and building steps are documented in this report. The developed prototype aims demonstrate the viability of an aerial system built out of affordable materials, simple building techniques, and low-cost accessible open source hardware and software; that provides a solution for the rapid and efficient deployment of an airborne system capable of operating BVLOS.Study of the flow around a non-planar C-wing via computational fluid dynamicsGiménez Herrero, Sergihttp://hdl.handle.net/2117/3966182023-11-17T12:40:21Z2023-11-17T12:34:40ZStudy of the flow around a non-planar C-wing via computational fluid dynamics
Giménez Herrero, Sergi
In the aeronautical industry, the pursuit of efficiency is a fundamental factor that governs the characteristics of an aircraft. Therefore, the implementation of new aerodynamic devices capable of altering the airflow behavior is a highly significant advancement in the field. One theoretical proposal dedicated to optimizing the aerodynamic efficiency of a wing involves the use of a non-planar "C"-shaped design. By doing so, a significant portion of the aerodynamic resistance produced by wingtip vortices can be drastically reduced while maintaining total lift. In this study, building upon previous research primarily based on inviscid potential flow methods (such as the Discrete Vortex Method or the Vortex Lattice Method), the airflow behavior through a C-wing will be investigated. To this end, a previously designed and analyzed wing configuration will be studied using the Finite Volume Method, which takes into account the effects of viscosity and provides more accurate results. Furthermore, the airflow behavior through the C-wing will be compared to that of an equivalent conventional wing. For this purpose, an open-source computational fluid dynamics program and the Reynolds-averaged Navier-Stokes equations will be employed.
2023-11-17T12:34:40ZGiménez Herrero, SergiIn the aeronautical industry, the pursuit of efficiency is a fundamental factor that governs the characteristics of an aircraft. Therefore, the implementation of new aerodynamic devices capable of altering the airflow behavior is a highly significant advancement in the field. One theoretical proposal dedicated to optimizing the aerodynamic efficiency of a wing involves the use of a non-planar "C"-shaped design. By doing so, a significant portion of the aerodynamic resistance produced by wingtip vortices can be drastically reduced while maintaining total lift. In this study, building upon previous research primarily based on inviscid potential flow methods (such as the Discrete Vortex Method or the Vortex Lattice Method), the airflow behavior through a C-wing will be investigated. To this end, a previously designed and analyzed wing configuration will be studied using the Finite Volume Method, which takes into account the effects of viscosity and provides more accurate results. Furthermore, the airflow behavior through the C-wing will be compared to that of an equivalent conventional wing. For this purpose, an open-source computational fluid dynamics program and the Reynolds-averaged Navier-Stokes equations will be employed.