Publication: Diseño y construcción de un motor cohete híbrido
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2013-06
Defense date
2013-06-26
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Abstract
Este trabajo práctico tiene como finalidad el diseño y la construcción de un motor de
propulsión tipo cohete. Así mismo, el estudio de la idoneidad del motor cohete tipo
híbrido para el propósito docente del proyecto.
Para su diseño, partimos del motor cohete de demostración del Departamento de
Aeronáutica y Aeroespacial del Instituto Tecnológico de Massachusetts (MIT).
El diseño 3D de las piezas se ha realizado con el programa Solid Edge (Siemens).
Para el cálculo de las dimensiones de los diferentes elementos, se han realizado
diferentes suposiciones, las cuales se especifican en los apartados correspondientes al
diseño del elemento en cuestión, como son:
· Flujo estacionario y condiciones próximas a las de remanso aguas arriba de la
tobera, la cual se ha diseñado como tobera sónica.
· En el cálculo de resistencias mecánicas, se utiliza tanto la suposición de pared
delgada como de pared gruesa para asegurar coeficientes de seguridad aceptables.
· En algunos casos se han tomado valores extraídos de otros trabajos de manera que
se asegure el correcto funcionamiento del sistema.
Los resultados de este proyecto han sido:
· Diseño y construcción de un motor cohete híbrido de demostración con un nivel de
empuje del orden de magnitud requerido por los objetivos del proyecto.
· Diseño modular el cual permite continuar, mediante trabajos futuros, el estudio de
los diferentes parámetros geométricos que afectan las actuaciones de este tipo de
motores cohete.
· Construcción de una estructura auxiliar, la cual permite desplazar de manera
cómoda y albergar tanto el motor como todos los sistemas necesarios para su
funcionamiento
The aim of this project is the designing and building of a rocket propulsion engine, as well as the study of hybrid rocket type engine. For the design, we start from the demonstration hybrid rocket engine of the Aeronautics and Aerospace Department of the Massachusetts Institute of Technology (MIT). The 3D design of the parts was made with the program Solid Edge (Siemens). For the calculation of the dimensions of the different elements, different assumptions have been made, which are specified in the sections corresponding to the design of the element in question, such as: • Stationary flow conditions, stagnation conditions upstream of the nozzle, which is designed as sonic nozzle. • In the calculation of mechanical resistances, the thin wall assumption is used as well as thick wall to ensure acceptable safety factors. • In some cases they have taken values extracted from other works so that it ensure proper system operation. The results of this project were: • Design and construction of a demonstration hybrid rocket motor with thrust level of the order of magnitude required by the project's objectives. • Modular design which allows continuing through future works the study of the different geometric parameters that affect this type of rocket engines performance. • Construction of an auxiliary structure, which allows you to move comfortably and hold both the engine and all the systems required for operation
The aim of this project is the designing and building of a rocket propulsion engine, as well as the study of hybrid rocket type engine. For the design, we start from the demonstration hybrid rocket engine of the Aeronautics and Aerospace Department of the Massachusetts Institute of Technology (MIT). The 3D design of the parts was made with the program Solid Edge (Siemens). For the calculation of the dimensions of the different elements, different assumptions have been made, which are specified in the sections corresponding to the design of the element in question, such as: • Stationary flow conditions, stagnation conditions upstream of the nozzle, which is designed as sonic nozzle. • In the calculation of mechanical resistances, the thin wall assumption is used as well as thick wall to ensure acceptable safety factors. • In some cases they have taken values extracted from other works so that it ensure proper system operation. The results of this project were: • Design and construction of a demonstration hybrid rocket motor with thrust level of the order of magnitude required by the project's objectives. • Modular design which allows continuing through future works the study of the different geometric parameters that affect this type of rocket engines performance. • Construction of an auxiliary structure, which allows you to move comfortably and hold both the engine and all the systems required for operation
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Keywords
Cohetes, Turbomaquinaria