Rocket Engines
Mostrando 1-10 de 10 artigos, teses e dissertações.
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1. Phase Separation and Development of the Microstructure for Stainless Steel to Copper Alloy Weld Joints Using a Fiber Laser
ABSTRACT Stainless steel and copper alloys joints are often applied in aerospace, marine and power industries where both high thermal and electrical conductivity (Cu) and corrosion resistance (steel) are required. In the aerospace industry, in particular for the combustion chamber of rocket engines, copper and steel combinations offer perfect materials selec
J. Aerosp. Technol. Manag.. Publicado em: 10/10/2019
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2. Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine
ABSTRACT: Accurate determination of heat flux is an important task not only in the designing aspect, but also in the performance analysis of rocket engines. In this purpose, this work deals with the heat flux determination in a combustion chamber through the inverse method. In this approach, the transient heat flux is determined from the experimental tempera
J. Aerosp. Technol. Manag.. Publicado em: 26/08/2019
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3. Stability Characteristics of a Model Trim Adjustment System for Open Loop Active Control of Thermoacoustic Instability
ABSTRACT Thermoacoustic instability in liquid rocket engines can have potentially catastrophic consequences. Active control based on feedback promises improved stability margin over a wider range of operating conditions than passive control. In the present work, the thermoacoustic characteristics of a trim adjustment active control system based on variable v
J. Aerosp. Technol. Manag.. Publicado em: 14/01/2019
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4. Modeling and Analysis of a LOX/Ethanol Liquid Rocket Engine
ABSTRACT This work studies the performance and dry mass of the under development LOX/Ethanol L75 liquid rocket engine. To this end, an object-oriented program written in C++ was developed. The program is intended to be versatile and easily extensible in order to analyze different configurations of liquid rocket engines. The UML (Unified Modeling Language) to
J. Aerosp. Technol. Manag.. Publicado em: 14/06/2018
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5. Swirl Injection Effects on Hybrid Rocket Motors
ABSTRACT: In the last decades, hybrid rocket engines have been increasingly studied and used in space vehicles. However, the low regression rates and specific impulses still represent major drawbacks to this technology. The objective of this study was to quantify the relative improvement of regression rate values with the use of a swirling flow injector in c
J. Aerosp. Technol. Manag.. Publicado em: 2015-12
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6. Evaluation of Chemical Equilibrium and Non-Equilibrium Properties for LOX/LH2 Reaction Schemes
ABSTRACT: Nine chemical reaction models for equilibrium schemes and six chemical models for non-equilibrium ones are studied, considering different conditions found in real liquid oxygen/liquid hydrogen rocket engines. Comparisons between two eight-species models have shown that the most complex is the best one. Besides, it was also verified that the most co
J. Aerosp. Technol. Manag.. Publicado em: 2015-03
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7. An Optimized Hybrid Rocket Motor for the SARA Platform Reentry System
Abstract: This paper has described a system design process, based on a multidisciplinary optimization technique, of a conceptual optimized hybrid propellant rocket motor. The proposed engine could be a technological option for the reentry maneuvering system of the Brazilian recoverable satellite (SARA), which was designed by the Brazilian Institute of Aerona
J. Aerosp. Technol. Manag.. Publicado em: 2012-09
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8. Development of test stand for experimental investigation of chemical and physical phenomena in Liquid Rocket Engine
Abstract The main objective of this work was to present the specification of an experimental firing test stand for liquid rocket engines (LRE) and develop a program for control and acquisition of data. It provides conditions to test rocket engines with thrust from 50 to 100 kgf. A methodology for laboratory work implementation using information technology, w
J. Aerosp. Technol. Manag.. Publicado em: 2011-08
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9. Modelo matemático de câmaras de combustão bipropelentes / Mathematical model of bipropellant combustion chambers
A mathematical model of the combustion chamber of a liquid propellant rocket was developed. The combustion process is assumed to be one-dimensional and controlled by the vaporization of the droplets, since the rates of mixture and reaction in the gaseous phase are fast in comparison to the vaporization rates of the propellants. It was considered a non unifor
Publicado em: 2004
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10. Modelo matemático de câmaras de combustão bipropelentes / Mathematical model of bipropellant combustion chambers
Desenvolveu-se um modelo matemático unidimensional de uma câmara de combustão de foguete utilizando propelentes líquidos. O processo de combustão é controlado pela vaporização das gotas, uma vez que as taxas de mistura e de reação na fase gasosa são consideradas rápidas em comparação às taxas de vaporização dos propelentes. Considerouse uma
Publicado em: 2004