Keywords
IEM-M (KL0-mecanica), Cohete, lanzador espacial, frecuencia propia, modo propio, reconstrucción superficie libre., Rocket, space launcher, natural frequency, eigenfrequency mode, reconstruction of free surface.
“Comportamiento dinámico del combustible líquido en un cohete experimental:estudio y realización de un experimento”
Abstract
Hoy en día, los motores de propulsor (combustible) líquido se utilizan en la mayoría de las naves espaciales y cohetes porque tienen muchas ventajas sobre los motores de propulsor sólido. Entre estas ventajas se encuentran principalmente: la capacidad de ser reencendidos varias veces, la capacidad de variar el empuje y una mayor eficiencia.
Los cohetes diseñados hasta ahora para este proyecto estaban equipados con motores de propulsión sólida, por lo que el diseño de un lanzador de propulsión líquida debe tener en cuenta y resolver nuevos problemas para este proyecto. Uno de ellos es el sloshing, un fenómeno recurrente en el ámbito del transporte de fluidos: aeronáutico y aeroespacial, naval y terrestre. La oscilación puede causar unas vibraciones adicionales y unas fuerzas suplementarias en la estructura, lo que puede perjudicar su correcto funcionamiento y llegar a dañarla. Este fenómeno está documentado, pero los medios para cuantificarlo son bastante complejos y generalmente disponibles con un acceso muy limitado.
Por lo tanto en este proyecto es necesario poder evaluar los fenómenos de sloshing dentro del lanzador ASTREOS. Para ello, primero se debe modelar el fenómeno, para luego observarlo y medirlo en condiciones reales. Posteriormente se realizará un experimento en el laboratorio para el que habrá que buscar un método de medición de fuerzas y un método capaz de reconstruir digitalmente la superficie libre del fluido para visualizar y analizar su comportamiento.
Nowadays, liquid propellant (fuel) engines are used in most spacecraft and rockets because they have many advantages over solid propellant engines. Among these advantages are mainly: the ability to be switched on several times, the ability to vary the thrust and greater efficiency. The rockets designed so far for this project were equipped with solid propulsion engines, so the design of a liquid propulsion launcher must take into account and solve new problems for this project. One of them is sloshing, a recurrent phenomenon in the field of fluid transport: aeronautic and aerospace, naval and terrestrial. The oscillation can cause additional vibrations and forces on the structure, which can impair its proper functioning and damage it. This phenomenon is documented, but the means to quantify it are quite complex and generally available with very limited access. Therefore, in this project it is necessary to be able to evaluate the sloshing phenomena inside the ASTREOS launcher. To do this, the phenomenon must first be modeled, then observed and measured under real conditions. Subsequently, an experiment will be carried out in the laboratory to find a force measurement method and a method capable of digitally reconstruct the free surface of the fluid to visualize and analyze its behaviour.
Nowadays, liquid propellant (fuel) engines are used in most spacecraft and rockets because they have many advantages over solid propellant engines. Among these advantages are mainly: the ability to be switched on several times, the ability to vary the thrust and greater efficiency. The rockets designed so far for this project were equipped with solid propulsion engines, so the design of a liquid propulsion launcher must take into account and solve new problems for this project. One of them is sloshing, a recurrent phenomenon in the field of fluid transport: aeronautic and aerospace, naval and terrestrial. The oscillation can cause additional vibrations and forces on the structure, which can impair its proper functioning and damage it. This phenomenon is documented, but the means to quantify it are quite complex and generally available with very limited access. Therefore, in this project it is necessary to be able to evaluate the sloshing phenomena inside the ASTREOS launcher. To do this, the phenomenon must first be modeled, then observed and measured under real conditions. Subsequently, an experiment will be carried out in the laboratory to find a force measurement method and a method capable of digitally reconstruct the free surface of the fluid to visualize and analyze its behaviour.
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