Rocket Nozzle Design Thesis

The flow-fields and thrust of the aerospike nozzle, for the full and truncated nozzles, were investigated.The purpose of this study is to investigate other rocket nozzles that might have the ability to improve performance of a propulsion system without a large penalty on vehicle mass or cost.

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This study documents the research, design, and analysis of a supersonic plug nozzle concept that could be integrated to the refrigerant-based cold-gas propulsion system to possibly improve its performance.

As documented in this thesis, CFD analysis showed that the outlined nozzle design method resulted in a feasible nozzle concept that has the ability to out-perform a conventional nozzle of the same area ratio.

Based on the information presented in this thesis, university-based satellite teams can manipulate the inputs of the design and analysis methods to investigate the use of an aerospike nozzle design concept to meet their design goals"--Abstract, page iii.

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.

A two-dimensional model was initially used because of the axisymmetrical characteristic of the flow in this study. His research interests are in the area of combustion instabilities of rocket and jet propulsions.

The optimal nozzle was designed for the operation of a test facility at Mach number 2.3 and altitude of 7 km. from Mandalay Technological University (MTU, Myanmar) in 2004 and M. in Mechanical Engineering from Yangon Technological University (YTU, Myanmar) in 2006. D candidate for Aerospace Information Engineering at Konkuk University in Seoul, Korea. However, such systems are still in an early development phase and one of the key areas requiring further investigations is the operation of the magnetic nozzle, the device meant to...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.In this thesis a practical investigation on cryogenic tank pressurization is conducted together with DARE. 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.We use cookies to make interactions with our website easy and meaningful, to better understand the use of our services, and to tailor advertising.For further information, including about cookie settings, please read our Cookie Policy .To predict structural massof a launch vehicle more accurate at a conceptual design phase, a structural mass model was developed.The modelpredicts a launch vehicle’s structural mass, thickness, center of mass and mass moment of inertia. Unlike a liquid rocket-engine, it is not possible to actively throttle the overall combustion of a solid rocket-motor.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...Accurate dry mass prediction is essential in early design phases of a launch system.


Comments Rocket Nozzle Design Thesis

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