Searched for: contributor%3A%22Zandbergen%2C+B.T.C.+%28mentor%29%22
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Duplay, Emmanuel (author)A laser-sustained plasma (LSP) generator capable of operating as a laser-thermal thruster was designed and tested. The apparatus was powered by a 3-kW 1070-nm fiber-optic laser and was operated with argon gas. The laser absorption, radiated spectrum, and change in static pressure were recorded, and high-speed video footage of the LSP was...master thesis 2024
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van Lynden, Willem (author)This study addresses the challenge of accurately modeling the multi-regime plasma flow through Ambipolar Plasma Thrusters (APTs), a type of Electric Propulsion (EP) system. Despite their advantages, understanding the behavior of plasma within APTs is complex due to the presence of two different flow regimes: the fluid regime inside the thruster...master thesis 2023
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van den Berg, Ruben (author)The electric-pump cycle is a rocket engine configuration that uses an electric motor to power the pumps instead of a turbine. This offers several expected advantages such as simpler design, lower development costs, and easier restartability, but comes with reduced performance compared to conventional cycles. Previous research has primarily...master thesis 2023
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Trotta, Luca (author)High-frequency combustion instabilities represent the main technical risk faced by design engineers when developing new chemical rocket propulsion systems. Such instabilities are driven by the coupling between the flames’ heat release rate and the combustion chamber’s acoustic field. As such, they can only be assessed during detailed design...master thesis 2023
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Duplay, Emmanuel (author)The existing literature on Laser-Thermal Propulsion (LTP) and associated concepts such as Directed-Energy Propulsion (DEP) and Laser-Sustained Plasma (LSP) is reviewed in preparation for an experimental thesis project on LTP.student report 2022
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Formisani, Ludovica (author)The space community is currently focusing on defining system architectures able to perform multiple interplanetary missions to support deep space exploration. In particular, placing orbital propellant depots in strategic locations in space would allow to increase the useful payload mass at launch. Despite all the efforts that are being invested...master thesis 2022
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Iyer, Swati (author)Contrasting experience with Reusable Launch vehicles—Space Shuttle and Falcon 9— has established that potential of reusable launch vehicles to achieve low launch costs is driven by the design choices made. Methalox propellant is one such design choice that has been touted to power future missions and potentially replace traditional propellants —...master thesis 2022
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Van Zegbroeck, Bart (author)This thesis details the methods used to build KOTUS (Kit Optimization Tool for Upper Stages) and the application of the tool to the future evolved Ariane 6 upper stage evolution, the Multi-function Upper Stage Express (MUSE), in order to gauge the impact of selected mission-specific kit elements on its payload performance for a range of Earth...master thesis 2022
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Soares dos Santos Vera-Cruz Pinto, Gonçalo (author)The renaissance of reusable space launch vehicles that is being witnessed in the current space industry demands a new cost estimating approach, which takes into account not only the time dependency in the lifecycle brought upon by reusability, but also the complementary considerations of minimizing cost and reliability. To achieve this end, a...master thesis 2022
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Hutten, Rick (author)The Delfi program at the Delft University of Technology aims to develop nano satellites between 1 and 10 kg to provide high level education and to develop a platform for novel space technologies. Miniaturized satellites require miniaturized propulsion systems to provide orbital adjustments for functions like station keeping, extending mission...master thesis 2022
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Squillace, Pietro (author)The Europa Lander is a mission by NASA to land scientific instruments on the Jovian Moon by 2030. The current design of the landing system envisions fixed landing legs with the lander being lowered down at very low velocities (≈ 0.1 m/s) by use of a Skycrane. This latter system not only adds mass, but also requires complicated moving parts and a...master thesis 2022
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Theodoulou, Jorgis (author)In the space industry miniaturization has been a trend for decades, with satellite masses ranging from 0.1-10kg for pico- and nano-satellites. Propulsion subsystems for these satellites have not kept up with this trend performance-wise. They are often limited by safety regulations requiring inert propellants and<br/>power budget constraints of...master thesis 2022
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le Grand, Yonis (author)Electric propulsion is generally characterized by higher specific impulse than traditional chemical rockets, which gives them propellant saving benefits. These have been applied in deep-space missions and micro-satellites. A Pulsed Plasma Thruster consists of two electrodes around a block of teflon. A pulsed discharge ablates the teflon and...master thesis 2021
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Samarawickrama, Kapeel (author)Dawn Aerospace is start up company that is developing a reusable sub-orbital spaceplane. The MK-II rocket powered spaceplane uses High Test Peroxide for its main engine and reaction control system. Catalyst beds are required to decompose High Test Peroxide (HTP) to steam and Oxygen. To investigate the decomposition of HTP in a pellet catalyst...master thesis 2021
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Pappadimitriou, Aris (author)A current trend, in recent decades, in spacecraft engineering is the miniaturization of satellites and their subsystems. One of these subsystems is for propulsion, which is important for orienting satellites and performing orbital manoeuvres. Currently one such micropropulsion system, being developed at the Space Engineering department at the...master thesis 2021
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Ravnan, Sigurd (author)The supersonic split line (SSSL) nozzle has been considered for years in the use of solid rocket motors. The SSSL nozzle is an attractive alternative to the more conventional submerged movable (SM) nozzle. The SSSL nozzle can save up to 43% on nozzle mass and 25% on the thrust vector control (TVC) system mass. The SSSL nozzle also has the...master thesis 2021
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Weinmiller, Julius (author)Even though hundreds of CubeSats have been launched, few have launched with a micropropulsion module on board. Propulsion would allow for an extended lifetime and better mission capabilities, thus greatly increasing the attractiveness of CubeSats. TU Delft is working on a type of thruster suitable for CubeSats, called the Vaporizing Liquid...master thesis 2021
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Takken, Aeilt-Jan (author)Miniaturization in spacecraft is an ongoing process in which the launched satellites become smaller and smaller. This trend introduces issues, such as the choice for a reliable and efficient propulsion subsystem. The implementation of engines would enable the spacecraft to perform maneuvers such as orbit changes, drag compensation and attitude...master thesis 2021
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Rozemeijer, Mark (author)In order to make access to space cheaper, the first stage of a launcher can be recovered. For this research, different options are investigated to make the cost per flight cheaper. Two vehicles are investigated going to two different orbits. The results show that recovering the complete stage is better for vehicles that have a lower separation...master thesis 2020
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Dickert, Zoe (author)Resonance ignition devices utilize the gas dynamic phenomenon to heat propellant gases to their auto-ignition temperature in order to initiate combustion. These devices are a promising alternative to current rocket engine ignition systems. In this thesis a python code was developed to generate a resonance ignition system design. The design was...master thesis 2020
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