Màster universitari en Enginyeria Aeronàuticahttp://hdl.handle.net/2117/777542024-03-29T06:46:12Z2024-03-29T06:46:12ZA study on the application of generative design in aircraft developmentMañé Ubalde, Santiagohttp://hdl.handle.net/2117/4037572024-03-05T16:43:23Z2024-03-05T16:38:47ZA study on the application of generative design in aircraft development
Mañé Ubalde, Santiago
This thesis explores the application of generative design tools in aircraft development. Generative design allows the automatic exploration of multiple design solutions optimised to the problem constraints, leading to refined products and reduced development times, as unlike traditional design, it does not rely on a manual iteration process based on the principle of trial and error. For this purpose, an engine mount for the light aircraft CESNA 172R and the Lycoming 360 L2A powerplant was designed following the conventional design methodology, which involves extensive research and the use of CAD tools. Then, the process was repeated implementing a new framework in which generative design is the protagonist. By comparing the obtained engine mount properties as well as certain parameters of the design methodologies, the strengths and weaknesses of the new technology are identified, determining the true potential of currently available generative design tools in the aerospace industry.
2024-03-05T16:38:47ZMañé Ubalde, SantiagoThis thesis explores the application of generative design tools in aircraft development. Generative design allows the automatic exploration of multiple design solutions optimised to the problem constraints, leading to refined products and reduced development times, as unlike traditional design, it does not rely on a manual iteration process based on the principle of trial and error. For this purpose, an engine mount for the light aircraft CESNA 172R and the Lycoming 360 L2A powerplant was designed following the conventional design methodology, which involves extensive research and the use of CAD tools. Then, the process was repeated implementing a new framework in which generative design is the protagonist. By comparing the obtained engine mount properties as well as certain parameters of the design methodologies, the strengths and weaknesses of the new technology are identified, determining the true potential of currently available generative design tools in the aerospace industry.Simulation of the ADCS subsystem for a VLEO satelliteRodriguez Tersa, Judithhttp://hdl.handle.net/2117/4037522024-03-05T16:30:28Z2024-03-05T16:23:41ZSimulation of the ADCS subsystem for a VLEO satellite
Rodriguez Tersa, Judith
The current trend of the space industry regarding Earth Observation (EO) and Telecommunications satellites is to keep lowering the orbit to increase the resolution of the images, to have a better Signal to Noise Ratio (SNR), or to have a lower latency in communications, among others things. Very Low Earth Orbits (VLEO) also offers the possibility to use the increased atmospheric density at low altitudes for novel purposes like aerodynamics-based attitude control. However, flying a satellite in VLEO is a technological challenge because atmospheric density is much higher in VLEO. To maintain a long-term mission, huge amounts of propellant would be needed if current propulsion systems were to be used. A possible solution to extend the lifetime of such missions is Atmosphere-Breathing Electric Propulsion (ABEP) that collects atmospheric particles (e.g. atomic oxygen) by an intake and feeds an electric thruster which ionizes and accelerates them to generate thrust. That is what Kreios Space is working on. They are developing an innovative all-electric propulsion system that would not need to carry propellant. On the context of the Kreios Space mission, this project aims to develop a satellite simulator for the Attitude Determination and Control Subsystem (ADCS) for this new satellite prototype. The simulator is developed in MATLAB Simulink. It is a very simple first approach of the subsystem. It aims to develop the bases of the subsystem to then, add new functionalities and make it more accurate as the satellite is developed. The simulator will basically contain the main components in any controlled system, which are: a reference, a controller, the actuators, and the model of the system, which includes the dynamics of the satellite. Additionally, a 3D visualisation block to see the satellite dynamics has been added. Once the simulator is developed, three different studies are carried out. The first one is related with VLEO disturbances. It demonstrates that other disturbances than Earth’s oblatness and drag can be neglected for short simulation periods. The second study aims to tune the controllers, which are three PIDs (one for each axis), in the nadir pointing point. Results of this study show that the error in Z is already in the order of 10−6 degrees, without control on the axis itself. Lastly, the third study has been derived from the results of study 2 and it performs a specific pointing manoeuvre in Z axis to tune the Z controller.
2024-03-05T16:23:41ZRodriguez Tersa, JudithThe current trend of the space industry regarding Earth Observation (EO) and Telecommunications satellites is to keep lowering the orbit to increase the resolution of the images, to have a better Signal to Noise Ratio (SNR), or to have a lower latency in communications, among others things. Very Low Earth Orbits (VLEO) also offers the possibility to use the increased atmospheric density at low altitudes for novel purposes like aerodynamics-based attitude control. However, flying a satellite in VLEO is a technological challenge because atmospheric density is much higher in VLEO. To maintain a long-term mission, huge amounts of propellant would be needed if current propulsion systems were to be used. A possible solution to extend the lifetime of such missions is Atmosphere-Breathing Electric Propulsion (ABEP) that collects atmospheric particles (e.g. atomic oxygen) by an intake and feeds an electric thruster which ionizes and accelerates them to generate thrust. That is what Kreios Space is working on. They are developing an innovative all-electric propulsion system that would not need to carry propellant. On the context of the Kreios Space mission, this project aims to develop a satellite simulator for the Attitude Determination and Control Subsystem (ADCS) for this new satellite prototype. The simulator is developed in MATLAB Simulink. It is a very simple first approach of the subsystem. It aims to develop the bases of the subsystem to then, add new functionalities and make it more accurate as the satellite is developed. The simulator will basically contain the main components in any controlled system, which are: a reference, a controller, the actuators, and the model of the system, which includes the dynamics of the satellite. Additionally, a 3D visualisation block to see the satellite dynamics has been added. Once the simulator is developed, three different studies are carried out. The first one is related with VLEO disturbances. It demonstrates that other disturbances than Earth’s oblatness and drag can be neglected for short simulation periods. The second study aims to tune the controllers, which are three PIDs (one for each axis), in the nadir pointing point. Results of this study show that the error in Z is already in the order of 10−6 degrees, without control on the axis itself. Lastly, the third study has been derived from the results of study 2 and it performs a specific pointing manoeuvre in Z axis to tune the Z controller.Assessment of turbulence modelling in internal flows with detached flow: current improvements within non-zonal hybrid RANS/LES methodsSoriano Samper, Guillemhttp://hdl.handle.net/2117/4037512024-03-05T16:05:23Z2024-03-05T15:58:46ZAssessment of turbulence modelling in internal flows with detached flow: current improvements within non-zonal hybrid RANS/LES methods
Soriano Samper, Guillem
This project is dedicated to the study of turbulence models applied to the Navier-Stokes equations to predict turbulent flows. For such purpose, the turbulence is firstly approached from a mathematical point of view, being the reasoning behind each modeling technique explored and the formulation of each approach mathematically explained. Two different types of modeling approaches are considered: the Reynolds Averaged Navier-Stokes equations and the Large Eddy Simulation. The most widely used models in industry of each approach are tested in a canonical case: the turbulent channel flow. In that case, the performance that each model has is analysed, detecting the advantages and shortcomings of each solution and the specific characteristics that the engineer has to consider when using these models. With that, the best-performing models for the case are selected and tested in a more challenging case: the backward-facing step. In this case, with a shear layer present as well as a wall-bounded flow, the performance of the models is again assessed. Furthermore, a compromise solution that has been used in industry between RANS and LES named Delayed Detached Eddy Simulation (DDES) is tested for this more complex case. To improve the performance of the model, a modification on a function (called shielding function) characteristic of this type of model is implemented in OpenFOAM and tested to check whether better performance is reached.
2024-03-05T15:58:46ZSoriano Samper, GuillemThis project is dedicated to the study of turbulence models applied to the Navier-Stokes equations to predict turbulent flows. For such purpose, the turbulence is firstly approached from a mathematical point of view, being the reasoning behind each modeling technique explored and the formulation of each approach mathematically explained. Two different types of modeling approaches are considered: the Reynolds Averaged Navier-Stokes equations and the Large Eddy Simulation. The most widely used models in industry of each approach are tested in a canonical case: the turbulent channel flow. In that case, the performance that each model has is analysed, detecting the advantages and shortcomings of each solution and the specific characteristics that the engineer has to consider when using these models. With that, the best-performing models for the case are selected and tested in a more challenging case: the backward-facing step. In this case, with a shear layer present as well as a wall-bounded flow, the performance of the models is again assessed. Furthermore, a compromise solution that has been used in industry between RANS and LES named Delayed Detached Eddy Simulation (DDES) is tested for this more complex case. To improve the performance of the model, a modification on a function (called shielding function) characteristic of this type of model is implemented in OpenFOAM and tested to check whether better performance is reached.Desenvolupament d'un sistema de comunicacions per operacions remotes amb dronsMontejo Fernández, Guillemhttp://hdl.handle.net/2117/4034912024-02-29T15:50:23Z2024-02-29T15:42:28ZDesenvolupament d'un sistema de comunicacions per operacions remotes amb drons
Montejo Fernández, Guillem
Amb l’augment dels avanços tecnològics, les operacions remotes amb drons han guanyat rellevància degut al seu potencial en la realització de tasques en entorns desafiant i de risc. Aquest projecte es dedica al desenvolupament i validació d’un innovador sistema de comunicació basat en la tecnologia 4G per a la gestió de drons a distància. Per això, es fa ús d’un Raspberry Pi Zero juntament amb un mòdem 4G, connectant-se directament amb el controlador de vol del dron. La transmissió de dades es realitza mitjançant el protocol MQTT, mentre que la visualització i gestió d’aquestes es fa amb l’ajuda de Node-RED. La investigació aprofundeix en l’estat actual de les operacions remotes en la indústria del dron, emfatitzant la necessitat de sistemes de comunicació fiables. La implementació del sistema de comunicació 4G implica establir una connexió estable 4G, transmetre dades de telemetria i facilitar el control bidireccional. Les proves rigoroses avaluen l’eficiència, fiabilitat i seguretat del sistema, assegurant una connectivitat perfecta i la transmissió de dades en diverses condicions. Aquest estudi destaca la importància de les operacions de drons remots i el paper fonamental dels sistemes de comunicació avançats. El sistema de comunicació 4G validat demostra el seu potencial per millorar les operacions de drons a través de les indústries, incloent la vigilància, l’agricultura, i la cerca i el rescat. L’adaptabilitat i futura escalabilitat del sistema subratlla la seva importància en la formació del paisatge de les operacions de drons remots.
2024-02-29T15:42:28ZMontejo Fernández, GuillemAmb l’augment dels avanços tecnològics, les operacions remotes amb drons han guanyat rellevància degut al seu potencial en la realització de tasques en entorns desafiant i de risc. Aquest projecte es dedica al desenvolupament i validació d’un innovador sistema de comunicació basat en la tecnologia 4G per a la gestió de drons a distància. Per això, es fa ús d’un Raspberry Pi Zero juntament amb un mòdem 4G, connectant-se directament amb el controlador de vol del dron. La transmissió de dades es realitza mitjançant el protocol MQTT, mentre que la visualització i gestió d’aquestes es fa amb l’ajuda de Node-RED. La investigació aprofundeix en l’estat actual de les operacions remotes en la indústria del dron, emfatitzant la necessitat de sistemes de comunicació fiables. La implementació del sistema de comunicació 4G implica establir una connexió estable 4G, transmetre dades de telemetria i facilitar el control bidireccional. Les proves rigoroses avaluen l’eficiència, fiabilitat i seguretat del sistema, assegurant una connectivitat perfecta i la transmissió de dades en diverses condicions. Aquest estudi destaca la importància de les operacions de drons remots i el paper fonamental dels sistemes de comunicació avançats. El sistema de comunicació 4G validat demostra el seu potencial per millorar les operacions de drons a través de les indústries, incloent la vigilància, l’agricultura, i la cerca i el rescat. L’adaptabilitat i futura escalabilitat del sistema subratlla la seva importància en la formació del paisatge de les operacions de drons remots.Study of the dynamics of gases by means of Direct Simulation Monte Carlo, with application to spacecraft in Low Earth OrbitPujol De Miguel, Laurahttp://hdl.handle.net/2117/4034832024-02-29T15:26:27Z2024-02-29T15:17:24ZStudy of the dynamics of gases by means of Direct Simulation Monte Carlo, with application to spacecraft in Low Earth Orbit
Pujol De Miguel, Laura
The present study explores the complex dynamics of spacecraft in Earth’s orbit at altitudes ranging up to a few hundred kilometres. Spacecraft have the challenge of navigating through an atmosphere that consists of gases with extremely low densities, leading to the generation of substantial aerodynamic forces, particularly drag. The long-term impacts of these forces give rise to challenges that cannot be analysed with the assumption of the classical continuous gas model used in fluid dynamics. The primary focus of this study revolves around the thermosphere, a critical atmospheric layer that plays a significant role in the operation of objects in Low Earth Orbit (LEO) as well as in the forecast of re-entering objects. The thermosphere is characterised by its relatively low densities and high kinetic temperatures. Fluid dynamics in the low Earth orbit (LEO) altitudes is governed by the (largely unknown) laws of free molecular flow. The investigation of the dynamic consequences of thermospheric interaction is of the highest importance, and under constant efforts for development, as it improves the accuracy of orbital trajectories of space objects. Furthermore, the analysis of these dynamic effects plays a crucial role in the optimisation of spacecraft design, the mitigation of drag forces, and ultimately the improvement of total vehicle efficiency. Historically, computational fluid dynamics (CFD) simulations have been widely utilised as a major approach for the modelling of spaceship drag. Computational Fluid Dynamics (CFD), which involves the numerical solution of governing equations for fluid flow, offers a comprehensive analysis of the flow properties surrounding a spacecraft. However, this methodology frequently requires significant computational resources and time, and yet can not be employed above 100 km above sea level. Therefore, the present thesis aims to investigate alternative approaches based on Statistical Mechanics, specifically focusing on the Direct Simulation Monte Carlo (DSMC) technique, to analyse the dynamic implications of thermospheric interaction. The primary objective of this study revolves around the creation and testing of a Direct Simulation Monte Carlo (DSMC) algorithm specifically designed for the simulation of rarefied gases in 3D. The algorithm facilitates the coordination of gas particles’ motion inside a grid that is built from an importable mesh. The initial code iteration is based on the assumption of a non-collisional flow. This assumption is supported by the fact that the mean free path is much larger than the size of the domain being considered. Additionally, an assessment of the effectiveness of the DSMC approach is conducted by simulating a sphere and a cylinder geometry in particular conditions. A thorough exposition and comparison of the acquired findings with some current benchmarks is performed to do so. The key performance metrics encompass the drag coefficients of a sphere, which are analysed in conjunction with atmosphere characteristics such as the energy accommodation coefficient, tangential momentum accommodation coefficient, altitude, free stream velocity, air temperature, and molecular speed ratio.
2024-02-29T15:17:24ZPujol De Miguel, LauraThe present study explores the complex dynamics of spacecraft in Earth’s orbit at altitudes ranging up to a few hundred kilometres. Spacecraft have the challenge of navigating through an atmosphere that consists of gases with extremely low densities, leading to the generation of substantial aerodynamic forces, particularly drag. The long-term impacts of these forces give rise to challenges that cannot be analysed with the assumption of the classical continuous gas model used in fluid dynamics. The primary focus of this study revolves around the thermosphere, a critical atmospheric layer that plays a significant role in the operation of objects in Low Earth Orbit (LEO) as well as in the forecast of re-entering objects. The thermosphere is characterised by its relatively low densities and high kinetic temperatures. Fluid dynamics in the low Earth orbit (LEO) altitudes is governed by the (largely unknown) laws of free molecular flow. The investigation of the dynamic consequences of thermospheric interaction is of the highest importance, and under constant efforts for development, as it improves the accuracy of orbital trajectories of space objects. Furthermore, the analysis of these dynamic effects plays a crucial role in the optimisation of spacecraft design, the mitigation of drag forces, and ultimately the improvement of total vehicle efficiency. Historically, computational fluid dynamics (CFD) simulations have been widely utilised as a major approach for the modelling of spaceship drag. Computational Fluid Dynamics (CFD), which involves the numerical solution of governing equations for fluid flow, offers a comprehensive analysis of the flow properties surrounding a spacecraft. However, this methodology frequently requires significant computational resources and time, and yet can not be employed above 100 km above sea level. Therefore, the present thesis aims to investigate alternative approaches based on Statistical Mechanics, specifically focusing on the Direct Simulation Monte Carlo (DSMC) technique, to analyse the dynamic implications of thermospheric interaction. The primary objective of this study revolves around the creation and testing of a Direct Simulation Monte Carlo (DSMC) algorithm specifically designed for the simulation of rarefied gases in 3D. The algorithm facilitates the coordination of gas particles’ motion inside a grid that is built from an importable mesh. The initial code iteration is based on the assumption of a non-collisional flow. This assumption is supported by the fact that the mean free path is much larger than the size of the domain being considered. Additionally, an assessment of the effectiveness of the DSMC approach is conducted by simulating a sphere and a cylinder geometry in particular conditions. A thorough exposition and comparison of the acquired findings with some current benchmarks is performed to do so. The key performance metrics encompass the drag coefficients of a sphere, which are analysed in conjunction with atmosphere characteristics such as the energy accommodation coefficient, tangential momentum accommodation coefficient, altitude, free stream velocity, air temperature, and molecular speed ratio.Implementation of environmental and industrial parameters in traffic forecasting modelsParedes Quintanilla, Miguel Angelhttp://hdl.handle.net/2117/4034802024-02-29T15:00:32Z2024-02-29T14:55:35ZImplementation of environmental and industrial parameters in traffic forecasting models
Paredes Quintanilla, Miguel Angel
2024-02-29T14:55:35ZParedes Quintanilla, Miguel AngelNetwork integrity of the Air France operating flight schedule distributionAmador Pla, Fernandohttp://hdl.handle.net/2117/4034782024-02-29T14:50:26Z2024-02-29T14:47:12ZNetwork integrity of the Air France operating flight schedule distribution
Amador Pla, Fernando
2024-02-29T14:47:12ZAmador Pla, FernandoAdvanced methods for numerical simulations of turbulent flowsRegener Roig, Danielhttp://hdl.handle.net/2117/4034772024-02-29T14:50:26Z2024-02-29T14:41:38ZAdvanced methods for numerical simulations of turbulent flows
Regener Roig, Daniel
2024-02-29T14:41:38ZRegener Roig, DanielStudy of the stand planningMartínez Entrena, Adrián Joséhttp://hdl.handle.net/2117/4034762024-02-29T14:42:24Z2024-02-29T14:33:02ZStudy of the stand planning
Martínez Entrena, Adrián José
2024-02-29T14:33:02ZMartínez Entrena, Adrián JoséEstudi del teixit empresarial aeroespacialTintoré i Barreras, Lauhttp://hdl.handle.net/2117/4034752024-02-29T14:43:42Z2024-02-29T14:21:29ZEstudi del teixit empresarial aeroespacial
Tintoré i Barreras, Lau
2024-02-29T14:21:29ZTintoré i Barreras, Lau