Master's degree in Aerospace Science and Technology - MAST (Pla 2015)http://hdl.handle.net/2099.1/67512024-03-29T14:31:04Z2024-03-29T14:31:04ZActive flow control of airfoils via multi-sweeping jets at ultra low Reynolds numbersGopavaram, Sai Pradyumna Reddyhttp://hdl.handle.net/2117/3916792023-07-19T09:10:17Z2023-07-19T09:01:42ZActive flow control of airfoils via multi-sweeping jets at ultra low Reynolds numbers
Gopavaram, Sai Pradyumna Reddy
The primary focus is on implementing multiple sweeping jets to eliminate the requirement for high-lift equipment with mechanical components, which are at risk for mechanical failures and increase weight due to redundant control mechanisms. This project deals with the investigation of aerodynamic and performance parameters of Airfoils under subsonic flow regimes. This mainly includes the Active flow control techniques such as multi-sweeping jets used in Airfoils that will help us analyse the lift and drag parameters. The jet configurations are studied and modified to reduce viscous drag, improve pressure distribution and interference effects over and below the airfoil, and maximize lift coefficient. Pre and Post-processing stages would include the generation of a complete airfoil design with built-in sweeping jets using Fusion 360. It requires parametric inputs like altering the position of jets in order to calculate the induced drag and thus decrease the drag effects. The use of this open source also results in advanced visualization capabilities that include pressure, velocity distribution, turbulent kinetic energy, and eddy viscosity contours of the airfoil. This analysis and simulation have been carried out using ANSYS Fluent, industryleading fluid simulation software.
2023-07-19T09:01:42ZGopavaram, Sai Pradyumna ReddyThe primary focus is on implementing multiple sweeping jets to eliminate the requirement for high-lift equipment with mechanical components, which are at risk for mechanical failures and increase weight due to redundant control mechanisms. This project deals with the investigation of aerodynamic and performance parameters of Airfoils under subsonic flow regimes. This mainly includes the Active flow control techniques such as multi-sweeping jets used in Airfoils that will help us analyse the lift and drag parameters. The jet configurations are studied and modified to reduce viscous drag, improve pressure distribution and interference effects over and below the airfoil, and maximize lift coefficient. Pre and Post-processing stages would include the generation of a complete airfoil design with built-in sweeping jets using Fusion 360. It requires parametric inputs like altering the position of jets in order to calculate the induced drag and thus decrease the drag effects. The use of this open source also results in advanced visualization capabilities that include pressure, velocity distribution, turbulent kinetic energy, and eddy viscosity contours of the airfoil. This analysis and simulation have been carried out using ANSYS Fluent, industryleading fluid simulation software.Satellite GLONASS orbit integration and analysisGonzalez Salazar, Guillermo Josehttp://hdl.handle.net/2117/3905102023-07-10T09:50:17Z2023-07-10T09:49:05ZSatellite GLONASS orbit integration and analysis
Gonzalez Salazar, Guillermo Jose
Satellite navigation systems rely on precise knowledge of satellite positions. Galileo,GPS and BeiDou satellite coordinates are computed from pseudo-Keplerian elements. In contrast, GLONASS satellite are computed by interpreting the orbit from initial conditions of position and velocity using a fourth-order Runge-Kutta method. This master thesis aims to develop an algorithm that can compute GLONASS coordinates and clocks at any epoch using the broadcast navigation message. The algorithm analyzes the computed coordinates and key aspects of the satellite orbit derivation, such as external forces affecting the orbits. Through the analysis of the obtained data, coordinate and clock differences can be determined for both short and long terms, the data can be compared with other navigation products and the nature of these external forces can be identified.
2023-07-10T09:49:05ZGonzalez Salazar, Guillermo JoseSatellite navigation systems rely on precise knowledge of satellite positions. Galileo,GPS and BeiDou satellite coordinates are computed from pseudo-Keplerian elements. In contrast, GLONASS satellite are computed by interpreting the orbit from initial conditions of position and velocity using a fourth-order Runge-Kutta method. This master thesis aims to develop an algorithm that can compute GLONASS coordinates and clocks at any epoch using the broadcast navigation message. The algorithm analyzes the computed coordinates and key aspects of the satellite orbit derivation, such as external forces affecting the orbits. Through the analysis of the obtained data, coordinate and clock differences can be determined for both short and long terms, the data can be compared with other navigation products and the nature of these external forces can be identified.Design study & architecture of a tool combining remote sensing & tracking technology with Global Navigation Satellite Systems (GNSS)Bradford, Brandon Saviohttp://hdl.handle.net/2117/3853642023-03-23T10:30:31Z2023-03-23T10:26:34ZDesign study & architecture of a tool combining remote sensing & tracking technology with Global Navigation Satellite Systems (GNSS)
Bradford, Brandon Savio
This thesis covers a research study on the application of a Space technology in the field of Defence & Space. The thesis will elaborate a design study & architecture of a conceptual tool combining Remote Sensing technology with GNSS. The author intends to use this preliminary research thesis and expand on its design study in his doctoral program, a PhD in "Defence & Homeland Security" with a Major in Space Technology. The premise of the design study is based on a conceptual tool as a miniaturized ultrasonic sensing and GNSS mapping tool with satellite communication technology, that could be used as a tool placed in an area of interest and may contribute to gathering strategic information. The device could be used to gather information about the environment, such as terrain, obstacles, and other features, which can be used to create maps and 3D models of the environment. Additionally, the GNSS receiver can be used to determine the location of the device and by extension the location of targets. This thesis will contain a design study, operational scenarios, architectures, the possible errors to be expected, environmental analysis, & conclude with an argument for the risks & benefits associated with this technology.
2023-03-23T10:26:34ZBradford, Brandon SavioThis thesis covers a research study on the application of a Space technology in the field of Defence & Space. The thesis will elaborate a design study & architecture of a conceptual tool combining Remote Sensing technology with GNSS. The author intends to use this preliminary research thesis and expand on its design study in his doctoral program, a PhD in "Defence & Homeland Security" with a Major in Space Technology. The premise of the design study is based on a conceptual tool as a miniaturized ultrasonic sensing and GNSS mapping tool with satellite communication technology, that could be used as a tool placed in an area of interest and may contribute to gathering strategic information. The device could be used to gather information about the environment, such as terrain, obstacles, and other features, which can be used to create maps and 3D models of the environment. Additionally, the GNSS receiver can be used to determine the location of the device and by extension the location of targets. This thesis will contain a design study, operational scenarios, architectures, the possible errors to be expected, environmental analysis, & conclude with an argument for the risks & benefits associated with this technology.Airport digital Mock-upSardar, Girish Shiva Prasanna Rajuhttp://hdl.handle.net/2117/3770402022-11-24T11:40:25Z2022-11-24T11:35:38ZAirport digital Mock-up
Sardar, Girish Shiva Prasanna Raju
The accessibility of the Aeronautical Information is available in format such as AIXM, these formats are most suitable for trained eyes and intended for the purpose of Aerodrome monitoring, Landing & Takeoff procedures and Navigation systems on full fledge devices designed and built for AIXM only. Let's say if we want to develop an Aerodrome game where we can land an aeroplane in an airport whose characteristics are close to the real ones on a cross platform friendly format, it is not possible with the current available formats. In this thesis we take advantage of ENAIRE Spain's Air Navigation and Aeronautical Information service provider, availing Aeronautical Information Publication service https://aip.enaire.es/AIP/#LEPA/LESJ, where they provide data regarding to Aerodromes in Spain in the form of PDF and CSVs. The pdfs are sually used by pilots and co pilots as a reference to identify hotspots, taxiways status and obstacles inside the aerodrome, CSV files serve as a data to feed GIS platforms such as QGIS and mostly used by researchers and other people who are involved in aeronautical domain to identify the obstacles in and around the Aerodromes. We used Python libraries such as Pandas, Camelot to extract and convert data from PDF which are in the form of tables. The extracted information which contains Geo Locations and other critical information such as area, altitude and Runways important properties such as Clear way, Strip dimensions & geographic reference point is combined with the Obstacles data such as Geo Location and other characteristics such as altitude, Lighting, Marking and other available information of obstacles such as Trees, vegetation, Signal Towers into a geojson format. The Generated output geojson files are viewed on a 2-Dimensional map on http://geojson.io/#map=2/20.0/0.0, which has two split panes where we can view the geojson information and its geolocation against each other
2022-11-24T11:35:38ZSardar, Girish Shiva Prasanna RajuThe accessibility of the Aeronautical Information is available in format such as AIXM, these formats are most suitable for trained eyes and intended for the purpose of Aerodrome monitoring, Landing & Takeoff procedures and Navigation systems on full fledge devices designed and built for AIXM only. Let's say if we want to develop an Aerodrome game where we can land an aeroplane in an airport whose characteristics are close to the real ones on a cross platform friendly format, it is not possible with the current available formats. In this thesis we take advantage of ENAIRE Spain's Air Navigation and Aeronautical Information service provider, availing Aeronautical Information Publication service https://aip.enaire.es/AIP/#LEPA/LESJ, where they provide data regarding to Aerodromes in Spain in the form of PDF and CSVs. The pdfs are sually used by pilots and co pilots as a reference to identify hotspots, taxiways status and obstacles inside the aerodrome, CSV files serve as a data to feed GIS platforms such as QGIS and mostly used by researchers and other people who are involved in aeronautical domain to identify the obstacles in and around the Aerodromes. We used Python libraries such as Pandas, Camelot to extract and convert data from PDF which are in the form of tables. The extracted information which contains Geo Locations and other critical information such as area, altitude and Runways important properties such as Clear way, Strip dimensions & geographic reference point is combined with the Obstacles data such as Geo Location and other characteristics such as altitude, Lighting, Marking and other available information of obstacles such as Trees, vegetation, Signal Towers into a geojson format. The Generated output geojson files are viewed on a 2-Dimensional map on http://geojson.io/#map=2/20.0/0.0, which has two split panes where we can view the geojson information and its geolocation against each otherNew winglet designs to minimize drag and turbulenceJyothi, Sushmahttp://hdl.handle.net/2117/3756722022-11-04T10:50:13Z2022-11-04T10:49:00ZNew winglet designs to minimize drag and turbulence
Jyothi, Sushma
The aerospace industry relies on the continuous upgrading of available technology and the testing of novel concepts to ensure that there is a demand for aircraft design investments. These aircraft design improvements will substantially impact the aircraft's aerodynamic efficiency and structural design. Winglets are one of the essential components of an aircraft's design that contribute to its aerodynamic efficiency. The winglet design plays a significant part in reducing aerodynamic drag when it comes to the geometry of a wing. The winglet is responsible not only for the aircraft's efficiency but also for its structural integrity. So, based on the backdrop, as mentioned earlier, we'll now focus on implementing alternative winglet designs, generating parameters such as drag force and lift, and finally determining the most effective design based on the shape and flow regimes. Autodesk Fusion 360, Education License, the integrated CAD/CAM and 3D modeling software, is used to develop novel winglet designs. Ansys Fluent student version displays flow parameters, analysis, and simulations.
2022-11-04T10:49:00ZJyothi, SushmaThe aerospace industry relies on the continuous upgrading of available technology and the testing of novel concepts to ensure that there is a demand for aircraft design investments. These aircraft design improvements will substantially impact the aircraft's aerodynamic efficiency and structural design. Winglets are one of the essential components of an aircraft's design that contribute to its aerodynamic efficiency. The winglet design plays a significant part in reducing aerodynamic drag when it comes to the geometry of a wing. The winglet is responsible not only for the aircraft's efficiency but also for its structural integrity. So, based on the backdrop, as mentioned earlier, we'll now focus on implementing alternative winglet designs, generating parameters such as drag force and lift, and finally determining the most effective design based on the shape and flow regimes. Autodesk Fusion 360, Education License, the integrated CAD/CAM and 3D modeling software, is used to develop novel winglet designs. Ansys Fluent student version displays flow parameters, analysis, and simulations.Heat transfer enhancement in air by means of acoustic fieldsFerreiro Cuevas, Yagohttp://hdl.handle.net/2117/3713272022-10-14T19:10:47Z2022-07-27T12:08:18ZHeat transfer enhancement in air by means of acoustic fields
Ferreiro Cuevas, Yago
Convection is the most important heat transfer mechanism in air, and every heat source cools down thanks to it. However, this phenomenon relies on buoyancy and this does not exist in microgravity conditions. For this reason, heat will remain attached to the heat sources and this might lead to overheat problems. A possible solution to this problem might be to apply an acoustic field, as their interaction with the air can produce an acoustic streaming that will enhance the heat transfer between the heat source and the air. Several experiments have been performed to study this heat transfer enhancement due to acoustics, but all of them have been carried out in terrestrial gravity. Acoustic fields have shown to be effective for heat managing for liquids in microgravity conditions, and it is expected that this will happen also with gases. In this regard, an experiment will be designed and performed in the ZARM Drop Tower in Bremen in order to demonstrate that heat transfer in gases can be enhanced with acoustic fields. This work presents the preliminary tests, prior to the microgravity experiment, with the objective of achieving a deep understanding and be in a good position to optimize the design of the mentioned experiment.
2022-07-27T12:08:18ZFerreiro Cuevas, YagoConvection is the most important heat transfer mechanism in air, and every heat source cools down thanks to it. However, this phenomenon relies on buoyancy and this does not exist in microgravity conditions. For this reason, heat will remain attached to the heat sources and this might lead to overheat problems. A possible solution to this problem might be to apply an acoustic field, as their interaction with the air can produce an acoustic streaming that will enhance the heat transfer between the heat source and the air. Several experiments have been performed to study this heat transfer enhancement due to acoustics, but all of them have been carried out in terrestrial gravity. Acoustic fields have shown to be effective for heat managing for liquids in microgravity conditions, and it is expected that this will happen also with gases. In this regard, an experiment will be designed and performed in the ZARM Drop Tower in Bremen in order to demonstrate that heat transfer in gases can be enhanced with acoustic fields. This work presents the preliminary tests, prior to the microgravity experiment, with the objective of achieving a deep understanding and be in a good position to optimize the design of the mentioned experiment.Multidisciplinary design optimization for aerodynamic and propulsion components of rocketsSayar, Yaseminhttp://hdl.handle.net/2117/3711142022-10-14T19:06:31Z2022-07-26T10:12:03ZMultidisciplinary design optimization for aerodynamic and propulsion components of rockets
Sayar, Yasemin
Rockets are vehicles that people have worked hard on and made great progress in return throughout history. Over the years rockets have continued to evolve and have been clas- sified in different categories. Multistage rockets represent one of these categories. The purpose of multistage rockets is to place the fuel at different stages and to ensure that each stage operates within specified time intervals. The research in the present work is focused on serial multistage rockets. Thus a single stage, after completing a stage task, i.e. after consuming its fuel, becomes disconnected and leaves the whole structure and reduces the amount of total load. In other words, it makes the rocket lighter. Right after the previous stage has left, the next stage is ignited and so starts its duty and continues to carry the rocket to higher altitude by burning its fuel. In particular, present research is car- ried out on rockets consisting of 2 and 3 stages. During the studies, the most attention was paid to the aerodynamic forces and moments, because they have a serious effect on the stability of the rocket. The stability of the rocket is as important as rocket design. For this purpose, an attempt was made to balance the center of gravity and the center of pressure by calculating. Likewise, aerodynamic forces and moments affect the speed and position of the rocket. The main center of the study was 6 DOF blocks in Simulink. To meet the objectives, the Earth-centered Earth fixed coordinate system was also used. In this way, all values could be obtained in a loop. Different coordinate systems were the most useful approach for observing and evaluating outputs. The model, which was created with the contribution of all these, was run by designing 2 and 3 stages. All together 4 main points were investigated. First aim was to investigate the minimum fuel to reach the constant altitude with the constant payload in both designs. Secondly, the minimum and maximum fuel quantities found in the first step were considered constant, and the maximum payload amount that could be increased to a certain height was investigated. Third, the known min- imum and maximum fuel amounts and which payload can be safely lifted to what height were examined. Fourth, the most reasonable height that can be obtained by increasing the amount of payload and fuel was investigated.
2022-07-26T10:12:03ZSayar, YaseminRockets are vehicles that people have worked hard on and made great progress in return throughout history. Over the years rockets have continued to evolve and have been clas- sified in different categories. Multistage rockets represent one of these categories. The purpose of multistage rockets is to place the fuel at different stages and to ensure that each stage operates within specified time intervals. The research in the present work is focused on serial multistage rockets. Thus a single stage, after completing a stage task, i.e. after consuming its fuel, becomes disconnected and leaves the whole structure and reduces the amount of total load. In other words, it makes the rocket lighter. Right after the previous stage has left, the next stage is ignited and so starts its duty and continues to carry the rocket to higher altitude by burning its fuel. In particular, present research is car- ried out on rockets consisting of 2 and 3 stages. During the studies, the most attention was paid to the aerodynamic forces and moments, because they have a serious effect on the stability of the rocket. The stability of the rocket is as important as rocket design. For this purpose, an attempt was made to balance the center of gravity and the center of pressure by calculating. Likewise, aerodynamic forces and moments affect the speed and position of the rocket. The main center of the study was 6 DOF blocks in Simulink. To meet the objectives, the Earth-centered Earth fixed coordinate system was also used. In this way, all values could be obtained in a loop. Different coordinate systems were the most useful approach for observing and evaluating outputs. The model, which was created with the contribution of all these, was run by designing 2 and 3 stages. All together 4 main points were investigated. First aim was to investigate the minimum fuel to reach the constant altitude with the constant payload in both designs. Secondly, the minimum and maximum fuel quantities found in the first step were considered constant, and the maximum payload amount that could be increased to a certain height was investigated. Third, the known min- imum and maximum fuel amounts and which payload can be safely lifted to what height were examined. Fourth, the most reasonable height that can be obtained by increasing the amount of payload and fuel was investigated.An open-source software-defined radio collection for GNSS receiversBernabeu Frias, Joan Miguelhttp://hdl.handle.net/2117/3700922022-07-13T09:10:17Z2022-07-13T09:06:50ZAn open-source software-defined radio collection for GNSS receivers
Bernabeu Frias, Joan Miguel
The master's thesis has as a main objective to encompass the progress and efforts dedicated to the development and improvement of an open-source collection of Software-Defined Radios (SDR) for Global Navigation Satellite Systems (GNSS). Most of the efforts have focused in conducting an extensive test campaign for each implementation of the collection, with the aim of determining their characteristics at every stage in the positioning process, and make the required adjustments to achieve the defined performance. This document details the structure of the collection, the adjustments made to improve each code-base as well as the metrics considered to assess the obtained results.
2022-07-13T09:06:50ZBernabeu Frias, Joan MiguelThe master's thesis has as a main objective to encompass the progress and efforts dedicated to the development and improvement of an open-source collection of Software-Defined Radios (SDR) for Global Navigation Satellite Systems (GNSS). Most of the efforts have focused in conducting an extensive test campaign for each implementation of the collection, with the aim of determining their characteristics at every stage in the positioning process, and make the required adjustments to achieve the defined performance. This document details the structure of the collection, the adjustments made to improve each code-base as well as the metrics considered to assess the obtained results.Development and simulation of an illumination unit for microalgae cultivation in the context of a life support system of a crewed habitat on MarsComa Busquets, Aleixhttp://hdl.handle.net/2117/3630922022-03-06T08:42:54Z2022-02-25T10:07:06ZDevelopment and simulation of an illumination unit for microalgae cultivation in the context of a life support system of a crewed habitat on Mars
Coma Busquets, Aleix
To ensure the sustainability of future bases and settlements on the surface of Mars, bioregenerative life support systems shall be developed. For this purpose, the Institute of Space Systems (IRS), at the University of Stuttgart, works in the development of cultivation systems of algae (Chlorella vulgaris) in a photobioreactor (PBR), which uses natural sunlight to make photosynthesis, producing edible biomass and oxygen. A system of mirrors -the illumination unit- would be used to appropriately collect and focus the sunlight to reduce the demand of artificial illumination. In this Thesis, it has been investigated -both through numerical simulations and an experiment- the feasibility of this system. 4 different scenarios have been defined, which are considered representative of the environmental conditions on the surface of Mars. After that, a thermal model of the PBR and the illumination unit has been created, which has allowed to compute the temperature variation of the microalgae culture medium and the received irradiance during the day in each scenario. A control algorithm for the illumination unit has been designed and implemented, and the previous model has been used to demonstrate that the temperature of the culture medium could be kept constant. Then, the experimental part of the Thesis has been conducted, which has consisted in the cultivation of Chlorella vulgaris under similar illumination conditions to those obtained in one of the simulations. Finally, a model of a life support system with the PBR-illumination unit has been created. Its initial Equivalent System Mass (ESM) and the resupply demand have been computed. This data has been used to compare its performance with that of a Physico-Chemical Life Support System.
2022-02-25T10:07:06ZComa Busquets, AleixTo ensure the sustainability of future bases and settlements on the surface of Mars, bioregenerative life support systems shall be developed. For this purpose, the Institute of Space Systems (IRS), at the University of Stuttgart, works in the development of cultivation systems of algae (Chlorella vulgaris) in a photobioreactor (PBR), which uses natural sunlight to make photosynthesis, producing edible biomass and oxygen. A system of mirrors -the illumination unit- would be used to appropriately collect and focus the sunlight to reduce the demand of artificial illumination. In this Thesis, it has been investigated -both through numerical simulations and an experiment- the feasibility of this system. 4 different scenarios have been defined, which are considered representative of the environmental conditions on the surface of Mars. After that, a thermal model of the PBR and the illumination unit has been created, which has allowed to compute the temperature variation of the microalgae culture medium and the received irradiance during the day in each scenario. A control algorithm for the illumination unit has been designed and implemented, and the previous model has been used to demonstrate that the temperature of the culture medium could be kept constant. Then, the experimental part of the Thesis has been conducted, which has consisted in the cultivation of Chlorella vulgaris under similar illumination conditions to those obtained in one of the simulations. Finally, a model of a life support system with the PBR-illumination unit has been created. Its initial Equivalent System Mass (ESM) and the resupply demand have been computed. This data has been used to compare its performance with that of a Physico-Chemical Life Support System.An approach to some classical libration point orbit problems by means of artificial intelligence tecniquesAbecia Hernanz, Sara Ceciliahttp://hdl.handle.net/2117/3576262022-10-14T18:56:58Z2021-12-02T09:07:07ZAn approach to some classical libration point orbit problems by means of artificial intelligence tecniques
Abecia Hernanz, Sara Cecilia
Rapid developments in the last decade have demonstrated the potential of new techniques within the Artificial Intelligence (AI) field as an effective approach for different classical problems in the area of astrodynamics. Pathfinding strategies in multi-body dynamical regions of space implies some challenges which have traditionally relied on simplifications of the dynamical model or heavy computational loads. However, modern machine learning techniques are likely to provide more lightweight solutions that could be applied to automated on-board guidance systems in future missions traveling though complex environments. This work aims to leverage Artificial Neural Network techniques to study how they can be applied to Libration Point Orbits in the Circular Restricted Three-Body Problem. In particular, new ANN-approaches to compute heteroclinic connections between planar Lyapunov orbits are proposed, and their performance is compared to that of classic methodologies. In order to train, validate and test the ANNs used throughout the work, sufficiently large datasets containing information that accurately represents the dynamics of the Circular Restricted Three-Body Problem are required. To this effect, the datasets are generated by means of solving the problem using well-known classic techniques, since it is the only way to acquire an ensemble of accurate observations of the model. The following steps are taken: first, the heteroclinic connections are computed with arbitrarily high accuracy by numerical propagation of the unstable/stable invariant manifolds of the departure/arrival orbits respectively, using a Runge-Kutta 45 integrator; second, the data from the propagations are tabulated and stored in datasets; third, the datasets are used to train and validate a series of ANNs; and finally, the performance of the obtained ANN models is analysed and compared to the benchmark results. Also, the influence of the sampling technique when generating the datasets and the robustness of the developed method are studied. As a result of this work, it can be concluded that the two new ANN methods developed here can be considered as good as the classical method on terms their fitness to be used as a seed in a realistic ephemeris model, since the Restricted Three Body Problem model used here as a reference is also not an accurate representation of realistic trajectories anyways, but it is an acceptable approximation in early stages of mission design.
2021-12-02T09:07:07ZAbecia Hernanz, Sara CeciliaRapid developments in the last decade have demonstrated the potential of new techniques within the Artificial Intelligence (AI) field as an effective approach for different classical problems in the area of astrodynamics. Pathfinding strategies in multi-body dynamical regions of space implies some challenges which have traditionally relied on simplifications of the dynamical model or heavy computational loads. However, modern machine learning techniques are likely to provide more lightweight solutions that could be applied to automated on-board guidance systems in future missions traveling though complex environments. This work aims to leverage Artificial Neural Network techniques to study how they can be applied to Libration Point Orbits in the Circular Restricted Three-Body Problem. In particular, new ANN-approaches to compute heteroclinic connections between planar Lyapunov orbits are proposed, and their performance is compared to that of classic methodologies. In order to train, validate and test the ANNs used throughout the work, sufficiently large datasets containing information that accurately represents the dynamics of the Circular Restricted Three-Body Problem are required. To this effect, the datasets are generated by means of solving the problem using well-known classic techniques, since it is the only way to acquire an ensemble of accurate observations of the model. The following steps are taken: first, the heteroclinic connections are computed with arbitrarily high accuracy by numerical propagation of the unstable/stable invariant manifolds of the departure/arrival orbits respectively, using a Runge-Kutta 45 integrator; second, the data from the propagations are tabulated and stored in datasets; third, the datasets are used to train and validate a series of ANNs; and finally, the performance of the obtained ANN models is analysed and compared to the benchmark results. Also, the influence of the sampling technique when generating the datasets and the robustness of the developed method are studied. As a result of this work, it can be concluded that the two new ANN methods developed here can be considered as good as the classical method on terms their fitness to be used as a seed in a realistic ephemeris model, since the Restricted Three Body Problem model used here as a reference is also not an accurate representation of realistic trajectories anyways, but it is an acceptable approximation in early stages of mission design.