Searched for: contributor%3A%22Gill%2C+E.K.A.+%28mentor%29%22
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Cuadrat-Grzybowski, Michal (author)
Mitigation strategies which eliminate existing space debris, such as with Active Space Debris Removal (ASDR) missions, are now more important than ever regarding the ever-growing space debris population problem. One of the considered ASDR approaches uses a net as a capturing strategy. The benefits of such strategy are to allow for a large...
master thesis 2023
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Marchese, Franco (author)
While Artificial Neural Networks (ANN) representational capabilities have long been considered to benefit guidance and control tasks, a knowledge gap exists in the literature for their application to augment real-time navigation algorithms. Deep learning has excelled in various tasks, but its computational complexity limits its use in onboard...
master thesis 2023
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Lischwe, Louis (author)
The exponentially increasing number of Earth-orbiting satellites, as well as the pronounced importance for space military operations, impose new challenges on a functional Space Domain Awareness (SDA). A key factor for an effective SDA is the successful identification of an Earthorbiting satellite, or object in general. Current methods are...
master thesis 2022
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Pasqualetto Cassinis, Lorenzo (author)
This thesis reports on the reconstruction of key orbital elements of the Earth’s orbit around the Sun from a miniaturized temperature sensor onboard of theDelfi-C3 Cubesat, a novel approach never explored before to the best of our knowledge. Delfi-C3 is a triple-unit CubeSat with a mass of 2.4 kg, developed by Delft University of Technology,...
master thesis 2017
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Lopes Barreto, J.W. (author)
The use of deployable structures for space telescopes has the advantage of enabling options to improve their optical performance and reducing the launch volume. The Deployable Space Telescope (DST), which is currently developed by the Space Systems Engineering (SSE) department, will make use of a high precision deployable structure to extend the...
master thesis 2017
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Florijn, D.W. (author)
Collision analysis and mitigation performed for the QB50 mission. The aim of this thesis report is to identify which mitigation strategies are most suitable for a network of uncontrollable satellites. Furthermore, the aim is to set-out a method to determine the collision probability for a network of uncontrollable satellites, and identify the...
master thesis 2015
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Bos, C.R. (author)
There is a renewed interest, expressed by ISECG, to return to the Moon and establish a longer human presence on the lunar surface. Long term missions require supplies, which can be transported to the Moon by a new promising solution: the Solar Electric Propulsion (SEP) stage. The goal of this study is to create a conceptual system design (phase...
master thesis 2013
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De Jong, J.P. (author)
The objective of this thesis is to perform systems engineering, detailed (re-)design and testing of the structural and mechanisms subsystems and facilitate the production of components.
master thesis 2012
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Mathew, T.V. (author)
master thesis 2011
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Tindemans, A.M. (author)
System design of the communication subsystem of the Delfi-n3Xt nanosatellite. Delfi-n3Xt is the successor of the Delfi-C3 nanosatellite.
master thesis 2010
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Go, S.Y. (author)
Design of the different elements in the Structural Subsystem of Delfi-n3Xt. This is done by implementation of the lessons learned and solutions to problems encountered with Delfi-C3. First different options for CubeSats are considered and traded. Afterwards the detailed design is treated. Also the arrangement of the different subsystems and...
master thesis 2009
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Te Hennepe, F. (author)
Delfi-C3 is a nanosatellite developed by MSc students of the Faculty of Aerospace Engineering and Electrical Engineering, Mathematics and Computer Science at the Delft University of Technology. It will serve as an in-orbit test bed for three innovative technologies. Delfi-C3 is scheduled for launch in August 2007 by an Indian PSLV launcher. This...
master thesis 2007
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Maessen, D.C. (author)
New space debris mitigation guidelines require satellites in low Earth orbit to de-orbit within 25 years after end of life. This effectively limits the orbital altitude of conventional CubeSat satellites to 400-700 km. For CubeSats employing the generic inflatable de-orbit device discussed here, this range is extended to 910 km by increasing the...
master thesis 2007
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