Made available in DSpace on 2014-06-11T19:28:33Z (GMT). No. of bitstreams: 0 Previous issue date: 2011-08-22Bitstream added on 2014-06-13T20:58:28Z : No. of bitstreams: 1 melo_hht_me_guara.pdf: 1759227 bytes, checksum: 3dfd437259b41c05e4944f9e56da28d5 (MD5) / Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES) / A utilização de imagens digitais para extrair informações de objetos tem sido uma solução amplamente empregada em pesquisas científicas e em processos industriais. A contínua redução nos preços de equipamentos, a facilidade do uso de softwares e a simples integração com recursos de informática tem feito que muitos processos migrem para esta solução mais ágil, confiável e econômica. A indústria aeroespacial, que possui uma cadeia de produção não contínua e exige a avaliação de todos os seus componentes para obtenção de um nível de confiança elevado, encontra no emprego do processamento digital de imagens uma solução versátil e eficaz para análise das características de cada componente. Neste trabalho é apresentado um programa, desenvolvido em LabVIEW™, para medição dos sprays cônicos de jatos de injetores de motor foguete utilizando um sistema de processamento digital de imagens para sua análise. São apresentadas também as metodologias até então utilizadas para efetuar este tipo de medida. Os sprays dos jatos são desenvolvidos na saída do injetor, são exibidos visualmente durante o teste hidráulico a frio e tem influência direta no desempenho do motor foguete. A utilização desta nova ferramenta permitiu a realização desta medida de forma automática, com o fornecimento da incerteza de medição em níveis de confiança pré-estabelecido e mostrou-se ser mais exata e precisa que as metodologias anteriores / The usage of digital images to extract information from objects has been a solution widely used in scientific research and in industrial processes. The continued reduction in prices of equipment, the facility of software manipulation and the simple integration with computing resources has done many processes to migrate to this more flexible, reliable and economical solution. The aerospace industry, which has a chain of production that is not continuous and requires the evaluation of all its components to obtain a high confidence level, finds in the usage of digital image processing a versatile and effective solution for analysis of the characteristics of each component . This paper presents a program developed in LabVIEW™, to measure the rocket engine conic spray jet by using a digital image processing system for analysis. It is also presented the methodologies previously used to perform this type of measurement. The jet sprays are developed at the exit of the injector, are displayed visually during the cold hydraulic test and it has directly influences on the performance of the rocket engines. The usage of this new tool allowed us to make the measurement automatically with the supply of uncertainty together with a pre-established confidence level and it proved to be more accurate and precise than previous methodologies

This work presents a preliminary design of a liquid rocket engine test platform to support research into liquid propulsion systems and rocket engine components, including injectors, ignition systems, combustion chambers and engine cooling systems. The liquid propellants, specifically liquid oxygen and ethanol, are pressure-fed using gaseous nitrogen. The test platform supports engine thrust values up to 1 kN, as well as varying oxidizer/fuel ratios up to 4.0 and varying ethanol concentrations between 70 and 100%. The test platform will integrate with a mobile control centre, which was designed concurrently, and provides remote control of the test procedures and data acquisition of all relevant pressure, temperature, mass flow and thrust data. The propellant feed assembly can support both cold and hot fire testing campaigns and is equipped with numerous safety features including inert gas purge lines, emergency drain lines and emergency shut-down and de-pressurization procedures.

Orientador: Fernando de Azevedo Silva / Banca: João Zangrandi Filho / Banca: Silvana Aparecida Barbosa / Resumo: A utilização de imagens digitais para extrair informações de objetos tem sido uma solução amplamente empregada em pesquisas científicas e em processos industriais. A contínua redução nos preços de equipamentos, a facilidade do uso de softwares e a simples integração com recursos de informática tem feito que muitos processos migrem para esta solução mais ágil, confiável e econômica. A indústria aeroespacial, que possui uma cadeia de produção não contínua e exige a avaliação de todos os seus componentes para obtenção de um nível de confiança elevado, encontra no emprego do processamento digital de imagens uma solução versátil e eficaz para análise das características de cada componente. Neste trabalho é apresentado um programa, desenvolvido em LabVIEW™, para medição dos sprays cônicos de jatos de injetores de motor foguete utilizando um sistema de processamento digital de imagens para sua análise. São apresentadas também as metodologias até então utilizadas para efetuar este tipo de medida. Os sprays dos jatos são desenvolvidos na saída do injetor, são exibidos visualmente durante o teste hidráulico a frio e tem influência direta no desempenho do motor foguete. A utilização desta nova ferramenta permitiu a realização desta medida de forma automática, com o fornecimento da incerteza de medição em níveis de confiança pré-estabelecido e mostrou-se ser mais exata e precisa que as metodologias anteriores / Abstract: The usage of digital images to extract information from objects has been a solution widely used in scientific research and in industrial processes. The continued reduction in prices of equipment, the facility of software manipulation and the simple integration with computing resources has done many processes to migrate to this more flexible, reliable and economical solution. The aerospace industry, which has a chain of production that is not continuous and requires the evaluation of all its components to obtain a high confidence level, finds in the usage of digital image processing a versatile and effective solution for analysis of the characteristics of each component . This paper presents a program developed in LabVIEW™, to measure the rocket engine conic spray jet by using a digital image processing system for analysis. It is also presented the methodologies previously used to perform this type of measurement. The jet sprays are developed at the exit of the injector, are displayed visually during the cold hydraulic test and it has directly influences on the performance of the rocket engines. The usage of this new tool allowed us to make the measurement automatically with the supply of uncertainty together with a pre-established confidence level and it proved to be more accurate and precise than previous methodologies / Mestre

Characteristics of impinging-jet atomizers in the context of application in liquid propulsion systems are studied in this thesis. A review of past studies on impinging jets revealed the necessity of a correlation in terms of injector parameters for predicting Sauter Mean Diameter (SMD) of a spray. So, an experimental study of atomization in doublet and triplet impinging jet injectors is conducted using water as the stimulant? The major injector parameters considered are orifice diameter, impingement angle and jet velocity. Relative influences of these parameters are explained in terms of a single parameter, specific normal momentum. SMD of the spray reduces as specific normal momentum is increased. A universal expression between non-dimensional SMD and specific normal momentum is obtained, which satisfactorily predicts SMD in doublets as well as triplets. Noting that practical impinging injectors are likely to have skewness (partial impingement), the study is extended to understand the behavior of such jets. In perfectly impinging doublet, a high aspect ratio ellipse-like mass distribution pattern is obtained with major axis normal to the plane of two jets whereas in skewed jets the major axis turns from its normal position. A simple correlation is obtained, which shows that this angle of turn is a function of skewness fraction and impingement angle only and is independent of injection velocity. Experimental data from both mass distribution and photographic technique validate this prediction. SMD is found to decrease as skewness is increased. This may be the combined effect of shearing of liquid sheet at the point of impingement and more sheet elongation. Hence, skewness turns out to be an important parameter in controlling drop size.

Within the SR Dorado-project, which started in July 2022, a sounding rocket and its corresponding ground support equipment and test facilities are being developed and manufactured. This work is done mainly by undergraduate students at Technische Universität Dresden in cooperation with STAR Dresden, the student Space Flight Working Group in Dresden. The rocket will utilize liquid oxygen (LOX) and ethanol as propellants and is currently in its development phase. The current development status of the rocket and its support systems is described. Details on specific subsystems like propulsion system, rocket structure, recovery and telemetry system are presented. This detailed system assessment is supplemented with insights into the test bench and ground support equipment design, which are needed for successfully testing engine and propulsion system as well as conducting the launch campaign. The planned launch is currently set for 2025 and will take place at ESRANGE in Kiruna, Sweden.:1 Introduction 2 The rocket 2.1 Recovery system 2.2 Flight computer(s) 2.2.1 PoC Flightmaster 2000 2.2.2 Altus Metrum TeleMega 2.3 Structure 2.3.1 Main airframe 2.3.2 Aerodynamics 2.4 Propulsion system 2.4.1 Rocket engine 2.4.2 Propellant feed system 2.4.3 Pyro valves 3 Ground support equipment 4 Test bench 5 Summary and outlook Acknowledgements References