Change search
Refine search result
1 - 19 of 19
CiteExportLink to result list
Permanent link
Cite
Citation style
  • apa
  • harvard1
  • ieee
  • modern-language-association-8th-edition
  • vancouver
  • Other style
More styles
Language
  • de-DE
  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf
Rows per page
  • 5
  • 10
  • 20
  • 50
  • 100
  • 250
Sort
  • Standard (Relevance)
  • Author A-Ö
  • Author Ö-A
  • Title A-Ö
  • Title Ö-A
  • Publication type A-Ö
  • Publication type Ö-A
  • Issued (Oldest first)
  • Issued (Newest first)
  • Created (Oldest first)
  • Created (Newest first)
  • Last updated (Oldest first)
  • Last updated (Newest first)
  • Disputation date (earliest first)
  • Disputation date (latest first)
  • Standard (Relevance)
  • Author A-Ö
  • Author Ö-A
  • Title A-Ö
  • Title Ö-A
  • Publication type A-Ö
  • Publication type Ö-A
  • Issued (Oldest first)
  • Issued (Newest first)
  • Created (Oldest first)
  • Created (Newest first)
  • Last updated (Oldest first)
  • Last updated (Newest first)
  • Disputation date (earliest first)
  • Disputation date (latest first)
Select
The maximal number of hits you can export is 250. When you want to export more records please use the Create feeds function.
  • 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.
    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.

  • 3.
    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.

  • 4.
    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.

  • 5.
    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.

  • 6.
    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.

  • 7.
    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.

  • 8.
    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. 

  • 9.
    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.

  • 10.
    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.

  • 11.
    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.

  • 12.
    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.

  • 13.
    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.

  • 14.
    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.

  • 15.
    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.

  • 16.
    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.

  • 17.
    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.

  • 18.
    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.

  • 19.
    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.

1 - 19 of 19
CiteExportLink to result list
Permanent link
Cite
Citation style
  • apa
  • harvard1
  • ieee
  • modern-language-association-8th-edition
  • vancouver
  • Other style
More styles
Language
  • de-DE
  • en-GB
  • en-US
  • fi-FI
  • nn-NO
  • nn-NB
  • sv-SE
  • Other locale
More languages
Output format
  • html
  • text
  • asciidoc
  • rtf