Searched for: subject%3A%22rocket%22
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Thiam, Arthur (author)
Progress in Laser powder bed fusion manufacturing has led to greater use of Additive Manufacturing in combustion chambers/nozzles. This allows for the creation of more intricate and efficient solutions, but generates the need for a better understanding of how surface roughness in micro-channels used for engine cooling relates to build angle and...
master thesis 2024
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García Sánchez, Raúl (author)
Early design decisions have a significant influence in the final success of the project. One of the most important decisions is to determine the system architecture, as it highly impacts the performance of the system. System architecture optimization can be used to determine the best possible architectures through the formulation of an...
master thesis 2024
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Dutruel, Benjamin (author)
The startup Rocket Factory Augsburg (RFA) is developing the RFA ONE orbital launch vehicle. A significant hurdle for its closed-loop guidance is the need to fully deplete the third stage for insertion during the first flight, which results in lengthy burn-arcs and complexity not managed properly by traditional guidance algorithms. Additionally,...
master thesis 2023
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Bron Jacobs, Joachim (author)
A Tomographic Background-Oriented Schlieren (TBOS) technique is developed to aid in the visualization of compressible flows. An experimental setup was devised around a sub-scale rocket nozzle, in which four cameras were set up in a circular configuration with 30° angular spacing in azimuth. Measurements were taken of the overexpanded supersonic...
student report 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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Vissers, Casper (author)
Quantifying the exergy requirement of propellant insertion into LEO can lead to insight into the feasibility of a lunar propellant-generating architecture. Spacecraft leaving from Earth can greatly reduce their lift-off mass if in-space refueling would possible. Exergy analyses quantify the available energy of a system and show where a reduction...
master thesis 2023
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Formidabile, Martina (author)
TOP contoured nozzles, with large area-ratios, are commonly employed in rocket propulsion systems as they feature an excellent thrust-to-weight ratio. A significant shortcoming to this design is that, during the startup and shutdown transients of a LRE, the internal nozzle flow progresses through a series of overexpanded flow states - Free Shock...
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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Sonneveldt, Douwe (author)
Observing that the majority of SSTO programs failed due to the propulsion system being far ahead of its time. Furthermore, acknowledging the that the private launch markets is increasingly dominated by partly reusable TSTOs. This thesis aims to evaluate whether next generation rocket engines make an SSTO viable within a foreseeable economical...
master thesis 2022
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Garcia Ezquerro, Ignacio (author)
The number of IoT devices and their applications is projected to continue increasing in the future, creating a demand for low-power wireless communications that allow IoT devices to either be connected directly to the internet or to use other devices as a back gate to it. BLE is already one of the most used wireless communication protocols for...
master thesis 2022
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Gaffarel, Jérémie (author)
The Mars Ascent Vehicle will bring samples back from the surface of Mars to its low orbit in 2031. Its preliminary design has been performed by NASA, defining it as a two-stage solid propellant rocket. However, a research gap exists in finding what the optimum solid rocket motors geometries are to bring the Martian samples to a target orbit...
master thesis 2022
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Koelemij, Laura (author)
A flight termination system (FTS) is one of the most important safety features on a launch vehicle, as it allows for the vehicle's flight to be terminated in a controlled way when predetermined safety criteria or boundaries are exceeded. Currently, T-Minus Engineering B.V. aims to develop a custom flight termination system for the Dart payload...
master thesis 2022
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Wubben, Rolf (author)
After the breakup of the Stratos III vehicle, inertial roll coupling was pinpointed to be the root cause. In order to battle the problem a propulsive roll control system was suggested to keep the roll rate under acceptable bounds. A restartable hybrid rocket engine using nitrous oxide and ABS plastic was proposed. 27 tests have been performed of...
master thesis 2022
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van den Wijngaart, Jeije (author)
Solid rocket motors power sounding rockets and their thrust profile are determined mostly by their internal geometry. This study investigates the effect of the changes in internal geometry by changing the aspect ratio, truncation and elongation of grains in multiple BATES grain solid rocket motors. BATES grains are propellant segments in a thick...
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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Grendysz, Michał (author)
The rocket-based combined cycle (RBCC) engines are a hybrid between rocket and air-breathing propulsion. They can offer performance gains when compared to traditional rocket engines. At the same time, they are relatively simple in design. Therefore, they generally do not require long development times or large funds so they could be an...
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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Molenberg, Ilse (author)
This thesis report is written as part of the Master Aerospace Engineering - Space Flight of the Delft University of Technology. The thesis was started in November 2020 and completed by June 30, 2021. The space industry is dominated by traditional highly toxic propellants, namely hydrazine. Due to its carcinogenic nature, REACH makes provisions...
master thesis 2021
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Kerstens, Fabio (author)
As a part of a <i>Future Launcher Preparatory Programme</i> contract issued by the European Space Agency, the aerospace startup company Dawn Aerospace is developing an integral, additive manufactured (AM), liquid rocket engine. This 2.5 kN class engine is propelled by the storable propellants 90% hydrogen peroxide and kerosene and used in the...
master thesis 2021
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Kerstens, Fabio (author), Cervone, A. (author), Gradl, P.R. (author)
High performance liquid rocket engines require cooling to maintain structural integrity of the combustion chamber which is exposed to high thermal and environmental loads. For many systems, this is achieved by means of regenerative cooling, where a coolant flows through passages around the chamber wall whilst extracting heat from the wall. A...
journal article 2021
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