Searched for: contributor%3A%22Zandbergen%2C+B.T.C.+%28mentor%29%22
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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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Koehler, Stijn (author)
The heat fluxes in (liquid) rocket engines can go up to high values and they need active cooling to prevent the chamber wall from failing. Transpiration cooling is identified as a way to achieve lower wall temperatures than commonly used regenerative cooling and regenerative cooling with additional film cooling (referred to as film cooling from...
master thesis 2020
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Versteeg, Huib (author)
A key element in the development of more capable nano- and pico-satellites is the development of high specific impulse micro-propulsion systems, which allow for more challenging space missions to be flown. One such system being developed at TU Delft is a micro-resistojet with a planar supersonic nozzle geometry. This is currently fabricated by...
master thesis 2020
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Makhan, Rajeev (author)
This thesis includes an experimental study about the performance of a third generation MEMS-VLM chip. The influence of the throat Reynolds number on the discharge factor and the nozzle quality was investigated. This was done by measuring the mass flow and thrust force for a chamber pressure range of 2-5 [bar] using nitrogen gas as propellant. It...
master thesis 2018
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Groll, Christopher (author)
With evermore stringent requirements towards pointing accuracy and platform stability, in both commercial and scientific missions, AirbusDS has initiated the development of micronewton class ion engines for applications in attitude control systems. Here the Friedrichshafen branch of AirbusDS pursues the development of a downscaled version of the...
master thesis 2018
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Wildvank, Roy (author)
Accurate dry mass prediction is essential in early design phases of a launch system. To predict structural mass<br/>of a launch vehicle more accurate at a conceptual design phase, a structural mass model was developed. The model<br/>predicts a launch vehicle’s structural mass, thickness, center of mass and mass moment of inertia. Load carrying...
master thesis 2018
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