Ingeniería Mecánica

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Subject: search.filters.subject.FIBRA DE CARBONO

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    Análisis de la resistencia de la junta traslapada simple, entre el acero estructural, resina epóxica y fibra de carbono unidireccional, utilizado para reforzamiento de vigas de acero
    (Universidad Técnica de Ambato. Facultad de Ingeniería Civil y Mecánica, Carrera de Ingeniería Mecánica, 2022-09) Guerra Chiquito, Carlos Daniel; Tigmasa Paredes, Luis Giovanni; Peña Jordán, Francisco Agustín
    Carbon fiber is a material that provides excellent properties in different situations, one of these is structural reinforcement, due to the fact that it increases the resistance and stiffness of the structure without adding dead loads. One way to bond carbon fiber to steel is by means of epoxy resin which will create an adhesive bond; however, detachment can occur. According to previous research, spalling occurs because of the shear strength of the adhesive. Therefore, we proceeded to improve the shear strength of the adhesive bond by applying four surface treatments to the steel layer, these were manual cleaning, grinding disc, sanding disc and sandblasting. Comparing the results obtained, it was demonstrated, through real tests, that the roughness of the steel is directly proportional to the shear strength of the bond. Due to this, the Sandblasting treatment was the one with the best results due to its high degree of roughness with an average value of 10.79 μm and a maximum shear stress of 10.72 MPa.
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    Diseño y construcción estructural de un prototipo de avión no tripulado táctico con sistema modular desmontable para el centro de investigación y desarrollo de la Fuerza Aérea Ecuatoriana de la ciudad de Ambato
    (Universidad Técnica de Ambato. Facultad de Ingeniería Civil y Mecánica, Carrera de Ingeniería Mecánica, 2019) Chipantiza Bombon, Alex Daniel; Espín Guerrero, Víctor Rodrigo
    This project was carried out at the Development Research Center of the Ecuadorian Air Force, which aims to design and build the structure of a Tactical UAV prototype using a detachable modular system as a requirement of the research center. The detachable system seeks a better way to transport the UAV to different missions, reducing the space to be occupied in the means of transport that is chosen, in addition to the ease of assembling and removing the wing and tail of the aircraft. To design the prototype, parameters such as weight, dimensions of both the fuselage, wing and tail were considered, as well as the speeds of loss and cruiser to know the behavior of the UAV through an aerodynamic analysis, observing its behavior in cruise-flying conditions, in addition to minimal losses due to aircraft friction when it comes into contact with air particles. The safety factor of 1.5 sec was applied in the structural calculation and analysis, according to federal aviation standards (FAR/AIM), which allows disasters to be avoided if a force exceeds the limit is required. The structure was developed using composite materials such as carbon fiber and epoxy resin that was used for the lamination of the cab, and the composite material consisting of fiberglass, carbon and epoxy resin for the wing skin, providing a less weight in addition to high impact resistance. Finally, the structure of the UAV prototype was obtained; the wing and tail are disassembled easily, fulfilling the requirements established by the Research Center.