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  • 1.
    Abt, Cindy
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Development of a computational tool for thermal baffle sizing2017Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    The combination of a space thermal baffle and radiator builds a passive cooling system for space thermal control. This solution was investigated during the Preliminary Design Review of a satellite optical instrument at the Mechanical Design Office of Airbus Defence and Space, Toulouse. However, the thermal analysis in the baffle sizing process had time-consuming steps that could be automated. This report presents the internship and final Master’s degree project that resulted in the development of a computational tool helping size thermal baffles by automating the generation of the numerical thermal model of the baffle and the radiator sink temperature computation. The tool was designed to provide the necessary inputs and outputs required to carry out an optimization on the baffle geometry. Operational results were obtained thanks to the tool such as the impact of the baffle’s sunshield inclination and of the specularity of its inner coating on the radiator sink temperature. A preliminary work on the baffle geometry optimization was carried out but remaining tasks have to be performed in order to make the tool more robust to input and output changes. Additional work is required to find the optimal baffle geometry in the framework of the instrument project and for prospective projects with similar baffle sizing needs.

  • 2.
    Ask, Jacob
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Selected Trends and Space Technologies Expected to Shape the Next Decade of SSC Services2019Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    Since the early 2000s the space industry has undergone significant changes such as the advent of reusable launch vehicles and an increase of commercial opportunities. This new space age is characterized by a dynamic entrepreneurial climate, lowered barriers to access space and the emergence of new markets. New business models are being developed by many actors and the merging of space and other sectors continues, facilitating innovative and disruptive opportunities. Already established companies are adapting in various ways as efforts to stay relevant are gaining attention. The previous pace of development that was exclusively determined by governmental programs are now largely set by private and commercial ventures. Relating to all trends, new technologies and driving forces in the space industry is no trivial matter. By analyzing and examining identified trends and technologies the author has attempted to discern those that will have a significant impact on the industrial environment during the next decade. Market assessments have been summarized and interviews have been carried out. Discussions and conclusions relating to the services provided by the Swedish Space Corporation are presented. This report is intended to update the reader on the current status of the space industry, introduce concepts and provide relevant commentary on many important trends.

  • 3.
    Borg, Adrian
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Development of ADCS Software Models for Use with *craft2018Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    This report details the development of a software model of an ADCS to form part of the *craft mission design tool, a software design tool used in conjunction with the hardware-in-the-loop testbed, NANOBED. Models for the ADCS have been developed, using Clyde Space Ltd systems as benchmarks, and include sub-models for actuators. The objective for these models is to provide data on power consumption and torques produced by the ADCS throughout an operational simulation, which along with models of other systems gives an indication of the feasibility of a satellite’s mission configuration. The control algorithms which define the logic behind the ADCSs have been discussed and implemented, taking into account effort limitations and distribution to the configuration of actuators. Simulations for several ADCS operational modes were performed and the results were as expected, with the ADCS following the requirements for each mode.

  • 4.
    Bylund, Oscar
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Attitude Determination and Control of a Cubesat2016Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    This report describes the feasibility of attitude determination and control of the student satellite MIST. It investigates the stability and controllability of the satellite system, it covers attitude determination based on magnetometer and sun sensor measurements available and finally compares two controllers and the resulting pointing accuracy of the satellite. The study shows that the pointing requirements can be met under nominal circumstances.

  • 5.
    Carret, Rémi
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Mechanical Assembly Integration and Test of the Qualification Model for the EYESAT Mssion2018Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    In this era of miniaturization and industrial needs for accessing space, nanosatellites are an appropriate and riskless answer. This paper examines the development and the progress of the mechanical assembly, integration and test (AIT) campaign on the CNES CubeSat demonstrator, EYESAT. This student  nanosatellite, designed to observe the zodiacal light in the solar system, is actually in integration and testing phase; and will be launched in 2019. This thesis led the project from the structural and thermal model to the end of the qualification model assembly as well as the beginning of the tests campaign.

  • 6.
    Charbaut, Benjamin
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Robust and Agile Attitude Control for Triple CubeSat Eye-Sat2018Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    Eye-Sat is a student-designed 3U-CubeSat, to be launched to a sun-synchronous orbit from where it will map the zodiacal light, a faint glare caused by the reflection of Sun on interplanetary dust. Such mission requires an accurate 3-axis attitude control, for which Eye-Sat is equipped with reactions wheels, magnetorquers, magnetometers and a star tracker. The star tracker can only be used for inertial pointing, which confines its use to shooting phases. A solution based on the remaining 3 equipment is proposed for the other mission phases, providing 3-axis pointing with high agility, for ground station tracking, at the cost of a slightly degraded accuracy. The magnetometers and magnetorquers work in closed-loop, while manoeuvres are performed in open-loop by the reaction wheels, which also ensure gyroscopic stabilisation of the spacecraft. Since this design relies on only one sensor, efforts have been put into making it robust to the imperfections of the magnetometers. Robustness to potential changes in the mission or the design has also been taken into consideration. Performance assessments carried out on a preliminary tuning have demonstrated the capacity of this magnetic-based mode to recover 3-axis pointing when exiting the survival mode, to provide a 3-axis pointing accuracy better than 8 deg  in the worst case, and to sustain slews up to 0.87 deg/s in download.

  • 7.
    Charpigny, Noé
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    An Executable System Model for Behavioural Analyses of the LISA Mission2019Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    This master thesis report presents the modelling process of key elements of the Laser Interferometer Space Antenna mission (LISA mission) in a Modelbased systems engineering (MBSE) approach with SysML (Systems Modeling Language). The model implements a selected set of functions of the mission through executable graphical representations, called diagrams. It is shown how such diagrams can benefit the mission, by comparing this mean of information exchange to the traditional text- based systems engineering. The model represents the mission structure and behaviour through a system of nested layers. The deeper the layer is, the more it gives details on a system part. Each layer can be seen from different point of views, either focusing on the structure, the behaviour, or the performance of related system part.

  • 8.
    Cirillo, Giovanni
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Space Surveillance and Tracking Tool: Implementation and Test of New Methods​2019Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    In March 2019 the number of artificial objects bigger than 1 mm in orbit around the Earth is estimated to be more than 170 millions. Only a small fraction of them (0.03%) is catalogued. An impact of an operational satellite with one of these debris can damage the satellite and undermine its mission. So it is important to catalogue as many objects as possible in order to reduce the risk of a collisions. This is done by using the software tool Space Object Observations and Kalman Filtering (SPOOK), developed in Airbus Defence and Space in Friedrichshafen. The goal of this Master Thesis was to create newfunctionalities to this tool and improve the existing ones. In particular three main goals have been accomplished:

    • a new model for the lighting ratio has been built to take into account the occultation of the Sun due to a covering body (for example the Earth or the Moon) and itsinfluence on the solar radiation pressure, necessary to have a good model for orbit propagation;

    • a tracklet building algorithm has been built to distinguish different tracklets (consecutive observations of the same object along its orbit) as a starting point for the association of different measurements belonging to the same object at distant epochs, necessary to update a catalogue of space objects;

    • a model to take into account the process noise has been improved giving some suggestion on how to tune the different parameters for different kinds of orbit.

     

  • 9.
    Cousin, Pierre-Yves
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Aircraft Diesel EngineTests and Production Records2018Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    The aim of this internship is to improve the test process, especially the data exchange and treatment, as well as the production traceability, of an aeronautical Diesel engine. New criteria are devised to enhance the verifications of the engine’s performance.The documentation used throughout the process is globally reworked. New documents are also created, to simplify and codify the process. The updates to forms, instructions and specifications are included. Search for data in the Production Records is simplified by sorting the documents composing them, both in paperand digital formats. This paper also presents the work accomplished with the test subcontractor.

  • 10.
    Debeney, Louis
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Control Cost Reduction in the Aerospace Industry2017Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    This report deals with new technologies about control time saving and reliability within a manufacturing unit at Airbus Safran Launchers. Firstly, it analyses various kind of checked performances and describes how checking processes work in the different workshops and define what the main problems are. Then, it focuses on checking countersunk holes control and on three-dimensional control. It studies two kinds of new technologies and explains how it can decrease checking time relating to these two issues and how it can increase control reliability. To conclude, it also presents some other technologies which reach the same goal.

  • 11.
    Farid, Ramin
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Optimisation of satellite to ground station data delivery time by means of pathfinding and inter-satellite communication2019Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    Many satellites share the need to transmit data to Earth. However, depending on their orbital parameters the total delivery time may be very long, starting from when a satellite acquires its data to ground station data delivery. In an era where the need for fast data acquisition grows ever larger, there is a need to optimise this issue. In this thesis, it is suggested that a communicating system of satellites that utilise a pathfinding algorithm offers a viable solution to decrease the total delivery time of the satellite data. This is examined by creating simulations of different satellite constellations in MATLAB and in each of these comparing two satellite systems, with only one of them utilising the pathfinding algorithm. The results from the simulations provided a clear indication that the pathfinding algorithm did in fact provide a significantly faster average delivery time and could thus serve as a viable solution to the problem. 

  • 12.
    Jackson, Eric
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    An Investigation of the Effects of Sustained G-Forces on the Human Body During Suborbital Spaceflight2017Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    With the advent of private commercial suborbital spaceflight, a new demo-graphic of untrained individuals will begin to travel to space. These individuals are exposed to high levels of G-forces, resulting in medical considerations which are not a normal factor with high performance fighter pilots or astronauts.The acceleration profiles of the Virgin Galactic and Blue Origin spacecraft were obtained from publicly available data. Video analysis was performed on footage of spacecraft test launches and human centrifuge tests to obtain individual data sets. These data sets were used to develop the acceleration profiles for both spacecraft. Based on the spacecraft’s acceleration profiles and peak G-forces, medical conditions were investigated and considered to identify potential risks that may affect the passengers, particularly the elderly.

  • 13.
    Klicker, Laura
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    A Method for Standardization within the Payload Interface Definition of a Service-Oriented Spacecraft using a Modified Interface Control Document​2017Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    With a big picture view of increasing the accessibility of space, standardization is applied within a service-oriented space program. The development of standardized spacecraft interfaces for numerous and varied payloads is examined through the lens of the creation of an Interface Control Document (ICD) within the Peregrine Lunar Lander project of Astrobotic Technologies, Inc. The procedure is simple, transparent, and adaptable; its applicability to other similar projects is assessed.

  • 14.
    Maury, Lucas
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Optimization of Transfer Trajectories Towards Lagrangian Points Orbits2019Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    Investigations on the Circular Restricted 3- Body Problem (CR3BP) and the motion about the Lagrangian points are not recent. Several past (upcoming) missions have used (plan to use) its dynamics. The existence of specific periodic orbits and their associated invariant manifolds is one property of the CR3BP that raises the interest. These periodic orbits are interesting for their great observation properties, eclipse avoidance, communication’s continuity with the Earth, etc. However, to reach them, optimized transfer trajectories have to be found. A numerical tool is developed to construct firstly these orbits, before using them as input parameters for the invariant manifolds. Indeed, when a spacecraft is inserted into one of these manifolds, it shall naturally reach the orbit without any additional cost. This numerical computation provides manifolds’s insertion points, which are used in return by a Nonlinear Programming (NLP) tool to eventually find the optimized trajectory. Families of periodic orbits and manifolds, together with optimized transfer trajectories, have been successfully computed, with a focus on the Halo Orbits of the Earth-Moon system. Some members of this family, the Near-Rectilinear Halo Orbits (NRHOs), are of a great interest both for their geometry characteristics (close approach of the secondary body) and stability properties. However, in the Earth-Moon system, the associated manifolds do not have points relatively close from the Earth. The thesis work hence does not ensure that using manifolds as transfer arcs is beneficial, compared to a direct transfer. Besides, the Time-Of-Flight (TOF) is significantly larger. Transfer strategies making use of the CR3BP dynamics still are interesting, radically different from the usual trajectories and offering a larger number of opportunities. They may be less expansive, and could particularly be used for uncrewed space missions.

     

  • 15.
    Muresan, Alexandru Camil
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology. Inkonova AB.
    Analysis and Definition of the BAT-ME (BATonomous Moon cave Explorer) Mission2019Independent thesis Advanced level (degree of Master (Two Years)), 80 credits / 120 HE creditsStudent thesis
    Abstract [en]

    Humanity has always wanted to explore the world we live in and answer different questions about our universe. After the International Space Station will end its service one possible next step could be a Moon Outpost: a convenient location for research, astronaut training and technological development that would enable long-duration space. This location can be inside one of the presumed lava tubes that should be present under the surface but would first need to be inspected, possibly by machine capable of capturing and relaying a map to a team on Earth.In this report the past and future Moon base missions will be summarized considering feasible outpost scenarios from the space companies or agencies. and their prospected manned budget. Potential mission profiles, objectives, requirements and constrains of the BATonomous Moon cave Explorer (BAT-ME) mission will be discussed and defined. Vehicle and mission concept will be addressed, comparing and presenting possible propulsion or locomotion approaches inside the lava tube.The Inkonova “Batonomous™” system is capable of providing Simultaneous Localization And Mapping (SLAM), relay the created maps, with the possibility to easily integrate the system on any kind of vehicle that would function in a real-life scenario.Although the system is not fully developed, it will be assessed from a technical perspective, and proper changes for a viable system transition for the space-Moon environment will be devised. The transition of the system from the Batonomous™ state to the BAT-ME required state will be presented from the requirement, hardware, software, electrical and operational point of view.The mission will be devised into operational phases, with key goals in mind. Two different vehicles will be presented and designed on a high engineering level. A risk analysis and management system will be made to understand the possible negative outcomes of different parts failure on the mission outcome.

  • 16.
    Nicolle, Mathias
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Mechanical and structural conceptof the ISS microgravity experimentpayload: AtmoFlow2019Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    This Master Thesis report presents the mechanical concept and design of a microgravity fluid science experiment that is planned to be launched to the International Space Station in approximately five years. Named AtmoFlow, this experiment aims to study the complex flow phenomena occurring in different planets’ atmosphere by implementing a scaled-down model of a planet-atmosphere system in microgravity. The design introduced here focuses on several of the experiment’s systems: the Turn Table, a rotating system involving a Fluid Cell Assembly, a Thermal Control System and two Rotation Drive Systems. Design methods, main choices and crucial conception steps are presented. Components’ dimensioning and choices are motivated. Models and analyses are derived from the selected design to ensure that the design meets the requirements on microgravity disturbances, structural and rotational characteristics stated during previous project’s phases. The Computer Assisted Design model of the experiment’s final concept and its integration sequence are eventually proposed and discussed.

  • 17.
    Noyon, Matthieu
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Supervision Tools at Airbus Safran Launchers2018Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    This master thesis is a study of supervision tools in a context of high confidentiality. Indeed, the status “confidential defense” imposes governmental restrictions with national stakes and places the team project to higher security restrictions than a common internal project. First it introduces the context of the fusion between Airbus Defense and Space, and Safran, and then it gives the context of the ADELINE project. Then I proceed to the details of my activities at Airbus Safran Launchers through two main missions: data processing supervision on an avionic platform and supervision of several subcontractors via management of projects and compare both in a discussion part.

  • 18.
    Paskeviciute, Agne
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Preliminary Lander CubeSat Design for Small Asteroid Detumbling Mission2019Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    Asteroid mining is expected to become reality in the near future. The first step is to redirect an asteroid to a stable Earth orbit so that mining technologies can be demonstrated. Detumbling

    of the asteroid is one of the important steps in asteroid redirection missions. In this thesis, a preliminary lander CubeSat design is suggested for a small asteroid detumbling mission.

    The candidate asteroid for the detumbling mission is chosen to be 2014 UR, an Arjunatype asteroid with an estimated diameter ranging from 10.6 to 21.2 m. Due to the small size of the asteroid, the landing must be performed with an active control method after which the spacecraft must be firmly anchored to the asteroid. By using the multi-criteria decision making method PROMETHEE, the microspine gripper is chosen as the most suitable anchoring mechanism. Three main mission drivers are identified during the design process: data-flow between

    the lander and the mothership, Delta-V budget and pointing accuracy. The Delta-V required for landing on the asteroid and despinning it is estimated to be 10 m/s and 0.15 m/s at most,

    respectively. The uncertainty with the despinning Delta-V is due to varying estimates of the size of the asteroid. The required minimum pointing accuracy is estimated to be 6 degrees. The preliminary lander CubeSat design can be largely realised with commercial off-the-shelf components suggested in this work. Only some of the components have to be custom built or the technologies further developed. It is shown that a CubeSat lander is not able to detumble an asteroid that is rotating fast around multiple axes. However, if the considered asteroid is rotating around a single axis with a rotational period of 2.4 hours, it is be possible to despin it by spending just 1.5 kg of propellant. The suggested lander is a 12U CubeSat with an overall mass of 15 kg and power consumption of 65 W.

  • 19.
    Pettersson, Gustav
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Compact 3D Microscopy for Planetary Exploration2018Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    We propose using grain-of-sand-scale microscopy (1-micrometre resolution) to study the microstructure and composition of planetary material in a fast, in-situ, solid-state device. We have constructed a small and light prototype instrument (100 grams, 0.3 litres) from commercial-off-the-shelf components, targeted for applications in miniaturised robotic exploration, mounted to a robotic arm, or used as a hand-held tool. This microscope employs a programmable LCD aperture to virtually record multiple perspectives, and a dome studded with LEDs surrounding the sample to control illumination. With this prototype microscope we have captured rich and intuitive raw images for a human observer, and reconstructed 3D surfaces and photometric properties of the samples. The broad applicability of this method is demonstrated by integration into a novel exploration concept in which sensor projectiles are launched from a rover into inaccessible environments. Our microscope can there deliver 3D-maps of the surfaces they encounter and extract relevant morphological properties. Our prototype device is evaluated using a range of lunar and planetary simulants. We argue that this microscope delivers large scientific value on its own, and context for other instruments, with small resource requirements similar to those of a camera alone.

  • 20.
    Raiti, Federico
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Efficient and Robust Attitude Determination and Control System Design for the MIST CubeSat2018Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    This thesis investigated different configurations of the attitude determination and control system (ADCS) for the MIST satellite, to find a satisfying trade-off between computational demand and estimation/pointing accuracy. A model of the satellite dynamics was developed and used in a simulation. The designed ADCS consists of a discrete extended Kalman filter (EKF) and a model predictive control (MPC) controller tunable in different ways. The filter works with a linearization of the spacecraft dynamics model which is performed about the last attitude estimate and it is also capable of estimating the residual magnetic moment of the spacecraft without any initial guess. Three different models were used with the MPC and compared: a linear-like, state-dependent model, a model linearized around a fixed equilibrium point, and a model linearized around the last attitude estimate. The simulation, developed with Simulink, served as a testbed for the different tunings. From the simulation results, the filter proved to be capable of estimating the residual magnetic moment of the satellite with satisfying accuracy. Estimation and pointing requirements were met on average with a mean absolute estimation error of 0.8 deg and a mean absolute pointing error of 3.5 deg. This performance was achieved in face of measurement and model uncertainty.

  • 21.
    Rommelaere, Simon
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Ball Bearing Design Tool Evaluation​2017Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    This report has been written during my internship/master thesis at Thales Alenia Space, Cannes, FRANCE. The subject of the thesis is ball bearing design, and is focused on the software RBSDyn. This software has been developed by CNES, the French Center for Space Studies, and is used to simulate bearings behaviors under various conditions. My mission was to verify, test and implement this software for the company. In order to do so, the first step was to understand the bearing theory, which is the first part of this report. The second step was to use the software and verify its results, which is presented in the second section. Eventually, the final goal of this internship was to create a sequence to help Thales

    Alenia Space engineers to design and select bearings, using this software and an Excel tool that needed to be created. Note that for confidentiality reasons, the values and names used for internal TAS mechanisms have been removed of this document.

  • 22.
    Ruhlmann, Sébastien
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    The FLARE Suit: A protection against solar radiation in space2019Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    The FLARE Suit is a device that aims to protect astronauts from intense solar radiation when travelling out of the magnetosphere on future Deep Space missions. This suit is an emergency solution against solar particles that, due to their high density, can cause acute radiation sickness and lead to excessive destruction of internal organs (gastro-intestinal system, nervous system, blood forming bone marrow) and eventually to death. These symptoms will be a lot stronger out of the Earth’s magnetosphere, towards the Moon or Mars. For now, the FLARE Suit is being studied in the intra-vehicular environment as a supplement to already existing shielding provided by the spacecraft’s structure, but extra vehicular activities in space and on other planets can be considered. It consists of a bladder-suit that is to be filled with water when needed, the water being already present on any human carrying spacecraft. The suit can be deployed within a few minutes, be very lightweight at launch due to the resource utilization of on-board water, and does not use a lot of material compared to a fully shielded module since it is fitted to the individual human body. Furthermore, water has been shown to provide a decent shielding per mass capability, the third most shielding efficient material after hydrogenated boron nanotubes (H-BNNT) and high-density polyethylene (HDPE). Water could eventually be complemented with salt that shows high neutron blocking efficiency and could help shield from neutrons (present in secondary particles). Finally, it has a fully adaptive multilayered and shape changing design which allows for real-time scenario adaptation depending on the intensity of the solar radiation, the number of astronauts involved, the time frame and the water supplies. Preliminary design of the FLARE suit is show cased and radiation simulations are being performed in a 1D environment within the Columbus module, highlighting a fifty percent reduction in radiation exposure with 3.5 to 4 centimeters of water, depending on the salt content. Afterwards, a 3D environment is being built, however not tested. For this, selection of a relevant 3D human model, construction of the Columbus module and design choices on human morphology have been made. Matlab codes also were written to build and shape the 3D suit on top of the human model, following diverse radiation shielding strategies.

  • 23.
    Sadones, Thibault
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Assisted Natural Reentry: An innovative low-thrust deorbiting strategy to reduce human casualty risk2019Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    With a growing concern about space debris accumulation and the “French Space Operation Act” becoming strictly enforced in 2020, French space operators investigate new deorbiting methods or strategies. Among those, the Assisted Natural Reentry is an innovative deorbiting method developed by CNES to deorbit satellites with a low-thrust propulsive system. With correctly planned maneuvers, it becomes possible to minimize the reentry duration and the human casualty risk. This thesis aimed to further develop the Assisted Natural Reentry software as well as to compute the human casualty risk for several types of satellites. This study showed promising results as Assisted Natural Reentry could reduce the human casualty risk up to tenfold.

  • 24.
    Serrand, Jonathan
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    A Study of an Orbit Determination Software2018Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    In this report, have been treating the problem of validation of an orbit determination software. Orbit determination is one of the core element of satellite operations and is essential for any space mission. CNES is replacing its orbit determination tools and developed a generic software providing both routine operation and expert analysis tools. Several configurations for this software have been tested to validate the orbit determination tools. Optimal configurations have been set concerning the determination interval and the integrator and the software has been proven to give satisfying and expected results with another mission using real measurements. Optimal configurations are then to be used for routine operations while the new satellite configuration provide a new environment to compare the software results with its predecessor and serve as a reference configuration for the future studies.

  • 25.
    Tanguy, Nicolas
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Development of the tool Constellation for deployment of low thrust propulsion satellites constellations2018Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    The conception of constellations of satellites is now at the heart of the space industry programs. This review focuses on the development of a tool for the deployment of constellations composed of electric propulsion satellites, considering the perturbations due to the oblateness of the Earth. This Matlab tool named Constellation, is based on the software Mipelec from CNES (Centre National, d’Etudes Spatiales) and it is used for the first phases of space projects to select the best deployment among all the deployments considered for a given constellation. The low thrust transfers considering the Earth oblateness effects have been studied to develop a first Matlab tool. Then the tool for deployment of constellation has been developed. The different strategies for the RAAN rendezvous, the scenarios of deployments and the method to calculate the different transfers have been defined. The tool has been tested and its optimal configuration has been derived.

  • 26.
    Thierry, Maxime
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Developing and enriching a guidance library for the Earth Observation Satellite MicroCarb2018Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    My Master Thesis takes place in the context of the MicroCarb mission. The goal of this mission is to identify the sinks and the sources of carbon dioxide on Earth in order to map them and to improve the knowledge of its cycle. To fulfill this mission, some particular guidance modes must be implemented in order to study their feasibility. My thesis consisted in defining and enriching the algorithms used to define the guidance laws, by implementing new tools and a new guidance law, and studying the induced performances in terms of data acquisition and with respect to the constraints related to the satellite. Alongside with this mission, the implementation of those elements support the development of the guidance library POLARIS, actual in its early phase, which is at first only dedicated to MicroCarb but which is intended to become multimissions. First, I describe the CNES as well as the guidance team I worked in. Then, the context of the Master Thesis is introduced. Once the context is established we will focus on the first elements I have been working on, as part of the Dazzling studies. Indeed, the spectrometer used in MicroCarb is very sensitive and has to be maintained at very low temperature. Thus the passive cooling mechanism must be protected from the Sunlight and from the light reflected by the Earth. I had to use a class of the Space mechanics library PATRIUS, called Assembly, in order to materialize the satellite and its numerous parts. Once implemented, I was able to perform some Dazzling Studies, highlighting some issues with the various strategies that were considered, and opening new perspectives. Moreover, a problem was detected on a crucial function of the guidance laws calculator. Once a new function was compiled, I had to made a cross validation using Scilab, and results were positive. This part will end with a Geometric Cape study, realized in order to quantify the influence of the satellite, and the MCV roll, over the Geometric Shifting. In the second part, we will introduce a guidance law which was not implemented initially, and on which I had to work during the last weeks of the thesis: The City mode. Although this mode is similar to an existing calibration mode, it has its own characteristics I had to take into account. The code for this acquisition mode worked well, but the results were not satisfying, considering the Dazzling problem and the kinematic constraints. Thus new strategies had to be considered, and more particularly the 2-scans mode. This mode brought a lot of satisfactions, but there is still more work to be done. This report ends with a general conclusion about my work and some perspectives which could be considered for future studies. I also present my personal contribution and some encountered difficulties I had to deal with.

  • 27.
    Wehtje, Ernst
    KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Space Technology.
    Development of miniaturized fill and drain system for propellant tanks on small satellites2019Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
    Abstract [en]

    During recent years, private funding and new technology have boosted a change of the space industry, resulting in smaller and cheaper satellites being available on the market. GomSpace Sweden, part of GomSpace Group, is located in this market and develops propulsion systems for small satellites, so called, CubeSats. One of these highly miniaturized and efficient products is the cold gas propulsion system, suitable for 3-unit CubeSats. Due to the current design, the propellant tank of the system can be filled through a port but only drained through the thrusters, which causes several issues. This thesis concerns the development of a solution to these issues and creating a complete fill and drain system.

    A conceptual solution for a fill and drain tool was created and later designed as well as manufactured. The tool was tested and all initial requirements were successfully verified. However, through testing the functionality of the tool, several areas of improvement were found. A second version of the tool was digitally designed to meet these improvements. Also, a proposal of a more general fill and drain solution was digitally designed, which could be realized as a module in future development processes, including a fill and drain tank interface, fill and drain tool and a fill and drain procedure.

    In conclusion of the thesis, a solution to the problem with the current design of the propulsion system was successfully developed and tested. An improved version of the solution was designed, which decreases the risk of damage to the propulsion system and simplifies the usage. Finally, a design of a general fill and drain system was created, which could possibly span over several future GomSpace products and lowering both the cost and time of development.

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