Searched for: subject%3A%22rocket%255C%2Bengine%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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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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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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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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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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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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Sanghera, Bhupinder Singh (author)
Prior to the detailed design of turbines, turbomachinery engineers must rely on mean-line and throughflow models to come to a preliminary design. These models are based on empirical loss correlations and are often derived from cascade experiments and numerical analyses that are confined to the subsonic and transonic regime. Axial turbines for...
master thesis 2020
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Nosseir, A.E.S. (author), Cervone, A. (author), Pasini, A (author)
Innovation in small-satellite modern space missions and applications require propulsion capabilities to enable active operations in orbit, such as formation flying, rendezvous operations, orbital altitude &amp; inclination changes, and orbital transfers,– generally, operations demanding high-thrust impulsive maneuvers. In addition, Green...
conference paper 2020
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Huijsman, Ralph (author)
master thesis 2018
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Mercieca, Edward (author)
In Liquid Rocket Engine (LRE) design, knowledge of how the propellant atomization quality varies with respect to some injector design variables would be useful in predicting LRE performance. Three spray characteristics were chosen as a measure of Atomization quality: the Sauter Mean Diameter (SMD), the drop size distribution, and the cone angle....
master thesis 2017
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Hermsen, R.J.G. (author)
To launch a rocket to the edge of space using a pressure fed rocket system with liquid oxygen as propellant, you need to know exactly how much pressurant gas (helium) you need to take along. In this thesis a practical investigation on cryogenic tank pressurization is conducted together with DARE. The measurement results are used to validate...
master thesis 2017
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Denies, L. (author)
Methane is a promising propellant for future liquid rocket engines. In the cooling channels of a regeneratively cooled engine, it would be close to the critical point. This results in drastic changes in the fluid properties, which makes cooling analysis a challenge. This thesis describes a two-pronged approach to tackle this problem. Simple and...
master thesis 2015
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Ernst, R.R.L. (author)
The need to increase specific impulse of rocket launcher engines has lead design engineers to start development of ever more complex engine cycles starting from simple gas pressure fed engines to the very complex staged combustion cycle engines. Currently a wide range of different cycles does exist. These cycles not only differ in terms of...
master thesis 2014
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