Rocket Nozzle Design Thesis

Rocket Nozzle Design Thesis-76
An igniter for a LOX/CH4 rocket engine is designed and a CFD model is developed which is used to model the designed igniter.Verification and validation methods are discussed.... 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.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...

Preliminary design optimal techniques were adopted to reduce nozzle length while keeping the exit area constant in the design.

Optimization produced a smooth flow by generating a parallel and uniform flow at the exit. in Aeronautical Engineering from Seoul National University in 19, respectively. D from the University of Illinois in Urbana-Champaign in 1992. Lee is currently a Professor at the Department of Aerospace Engineering in Konkuk University in Seoul, Korea.

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.

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.the trajectory which costs the least amount of propellant.First some background information as well as the differences between thrust limited and power limited rockets will be discussed.Although many studies have been conducted on nozzle design, none of these present a robust yet practical and simple method for designing supersonic nozzles.This research attempts to develop such design for supersonic nozzles by combining method of characteristics (MOC), optimization algorithm, and computational fluid dynamics analysis for design verification.Three spray characteristics were chosen as a measure of Atomization quality: the Sauter Mean Diameter (SMD), the drop size distribution, and the cone angle....The influence of using different chemistry model and different chemical kinetics schemes on modeling combustion inside a rocket engine igniter are investigated.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 .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.


Comments Rocket Nozzle Design Thesis

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