Searched for: subject%3A%22Rocket%255C+propulsion%22
(1 - 12 of 12)
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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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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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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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Nosseir, Ahmed E.S. (author), Cervone, A. (author), Pasini, Angelo (author)
Green propellants are currently considered as enabling technology that is revolutionizing the development of high-performance space propulsion, especially for small-sized spacecraft. Modern space missions, either in LEO or interplanetary, require relatively high-thrust and impulsive capabilities to provide better control on the spacecraft,...
journal article 2021
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Nosseir, Ahmed E.S. (author), Cervone, A. (author), Pasini, Angelo (author)
Current research trends have advanced the use of “green propellants” on a wide scale for spacecraft in various space missions; mainly for environmental sustainability and safety concerns. Small satellites, particularly micro and nanosatellites, evolved from passive planetary-orbiting to being able to perform active orbital operations that may...
journal article 2021
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van den Berg, Peter (author)
The Dutch/New Zealand based aerospace company Dawn aerospace has developed a 0.5N green bi-propellant propulsion system for use in CubeSat applications called the PM200. This thruster uses gaseous nitrous oxide and propylene as propellants. Currently, the burn time of this thruster is limited to 10 seconds after which cool down of the thruster...
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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Govaert, Thomas (author)
The German Aerospace Centre (DLR) has in the past years been performing test runs with their experimental sub-scale combustion chambers to measure and investigate the effects of unstable combustion. Some of these investigations are focused on the heat flux to the chamber walls, changes in which can cause a significant shift in chamber wall...
master thesis 2019
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Huijsman, Ralph (author)
master thesis 2018
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Ehlen, Johannes (author)
Unlike a liquid rocket-engine, it is not possible to actively throttle the overall combustion of a solid rocket-motor. It is however possible to alter the thrust of an individual thruster by varying its throat area. The throat area can be altered by inserting a pintle of a conical or other shape into the nozzle throat. A setup which consist of...
master thesis 2018
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Wisse, M.E.N. (author)
The major technical challenge the development of next-generation launchers is facing today, is to achieve complete reusability in two stages to orbit or ultimately in one single stage. These Two-Stage-To-Orbit (TSTO) or Single-Stage-To-Orbit (SSTO) Reusable Launch Vehicles (RLV) may reduce payload cost by a factor of ten or more. The challenge,...
doctoral thesis 2005
Searched for: subject%3A%22Rocket%255C+propulsion%22
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