Searched for: faculty:"Aerospace%5C%2BEngineering"
(1 - 11 of 11)
document
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
document
Srongprapa, P. (author)
A geostationary transfer orbit (GTO) is typically used to inject spacecraft into the geosta- tionary orbit. There are many inoperative launcher upper stages and other fragments or- biting in GTOs. These parts collide and disintegrate, becoming even smaller fragments and thereby worsening the problem of space debris. The objects could also...
master thesis 2015
document
Arts, M.L.J. (author)
In this thesis, a dual-beam design concept for the LOUPE (Lunar Observatory for Unresolved Polarimetry of Earth) spectropolarimeter is presented based on the work by Karalidi [2012] and Hoeijmakers [2013]. The mission statement of LOUPE is: LOUPE shall do spectropolarimetry of the Earth from the Moon in order to obtain reference data for...
master thesis 2015
document
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
document
Van wal, S. (author)
The deployment of passive, spherical lander pods provides a low-cost, low-risk technique for measuring the (sub-)surface of asteroids and comets. In this masters thesis, we numerically investigate the feasibility of such pods through the development of simulation software. This software models the complex gravity field of asteroids, as well as...
master thesis 2015
document
Boudestijn, E. (author)
Develop the basis for a TU Delft Astrodynamics Toolbox (Tudat)-based software tool that comprises the fundamental functionalities required in order to optimize low-thrust Earth-centered orbit transfer trajectories for the preliminary mission design phase. Motivation: contribution to Tudat and facilitate case studies for the MicroThrust consortium.
master thesis 2014
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Noroozi, A. (author)
The trend of space technology developments is moving from high power consuming, bulky and costly systems towards low-power, small, low-cost and flexible systems. Thus, the spacecraft can benefit from multi-purpose and flexible systems which can be low-power and low-cost by employing new technology. One example of such system is a GNSS receiver...
doctoral thesis 2013
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Koerselman, J.R. (author)
A design methodology for composite space enclosures was generated. As a result a panel of an electronics housing structure, as part of a general satellite traversing both GEO and LEO, was designed and optimized. A mass saving of 18% was achieved over a conventional aluminum panel, while assuring structural integrity for acceleration loads,...
master thesis 2012
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Van der Ham, L. (author)
Instead of the two-body problem commonly used in interplanetary trajectory design, also three bodies can be considered: the satellite, a planet and the Sun. Knowing that planet and Sun orbit one another in almost circular orbits, and the mass of the satellite is negligible compared to the mass of these bodies, the model of the circular...
master thesis 2012
document
Sterken, V.J. (author)
ESA's space interferometry mission Darwin will make use of optical delay lines (ODL) to help control the optical path differences (OPD) between the satellites to the nanometer level. In order to determine the required ODL control bandwidth, this study investigates the order of magnitude of the high-frequency (> 1 Hz) disturbance forces, and...
master thesis 2005
document
Mooij, E. (author)
report 1994
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