Examinando por Autor "Bravo Mosquera, Pedro David"
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- ÍtemAnálisis experimental del efecto aerodinámico de dispositivos de punta de ala en una aeronave commuter tipo STOLAmaya Ospina, María Alejandra; Díaz Molina, Anny Isabella; Bravo Mosquera, Pedro DavidIn this investigation, the aerodynamic phenomena of wing tip devices, coupled to the wing of a STOL-type commuter aircraft, called VULTUR, were analyzed. This aircraft was designed by students and teachers of the Los Libertadores University Foundation in collaboration with the Sao Carlos School of Engineering of the University of Sao Paulo, for the Colombian Air Force (FAC). Wind tunnel experiments were performed to determine the best tip device based on the increase in aerodynamic efficiency and reduction of induced drag. These experiments were performed in the wind tunnel type blower located in the experimental aerodynamic laboratory (LAE), of the School of Engineering of Sao Carlos of the University of Sao Paulo, where the force measurement processes were carried out and aerodynamic coefficients under different angles of attack. The results indicated that of the three con fi gurations proposed, the winglet device is more suitable to be coupled to the aircraft wing, because it has the best aerodynamic efficiency since it has a high lift coefficient in which a better distribution of the lift on the surface of the wing and has a low drag and momentum coefficient. It should be noted that these results were validated with simulations of computational fluid dynamics (CFD) carried out by the main research group of the project.
- ÍtemDiseño conceptual, preliminar y análisis CFD de un avión jet ultra ligeroPulido Gonzalez, Anyelo Andrés; Flores Linares, Michael; Bravo Mosquera, Pedro DavidThe conceptual and preliminary design of an very-light jet (VLJ) is presented, covering all the concepts and design requirements that define the configuration of the aircraft, so that it is competitive in a promising market. Traditional methods of aircraft design were used to develop and analyze the suitability of the aircraft, seeking to improve aerodynamic efficiency byproposingtheimplementationofdifferentconfigurationsofwingletsinstalledatthetipsof the wings. The project addressed the study of size, weight, pilot ergonomics, aerodynamics, stability, systems, subsystems and performance. Later, computational analytical methods were used to design each of the components of the aircraft, together with the winglet deviviii ces, also called "Blended winglet", characterized by having the fin twisting towards the rear and a convenient incline with reference to the aircraft. Four winglet configurations were created, each one modifying the CANT angle and the wing span,todeterminetheaerodynamiccharacteristicsofferedbyeachofthemthroughastudyof computational fluid dynamics (CFD), solving the Reynolds-Averaged-Navier-Stokes(RANS) equations, using the turbulence model Shear Stress Transport (k-w). The parameters of the simulations were assumed based on the maximum operating altitude, studying exclusively the flow around the clean wing, winglet configurations and in the whole aircraft, in the most critical conditions before and after installing the devices. The coefficients of lift, induced drag, parasite drag, total drag and aerodynamic efficiency were analyzed. The results were fulfilled and validated, demonstrating that winglet devices remain the most promising alternative to improve the aerodynamic performance of the verylight jet.
- ÍtemDiseño de superficies de control y análisis de estabilidad de un UAV para monitoreo superficial de volcanes(Fundación Universitaria Los Libertadores. Sede Bogotá., ) Pulido Cano, Brayan Stip; Bravo Mosquera, Pedro DavidIn this project, the stability analysis of an unmanned aircraft is presented, whose main mission is the monitoring of volcanic activity. This aircraft, called URCUNINA-UAV, aims to mitigate volcanic catastrophes, and lacks a stability study for its future manufacture and operation. The URCUNINA-UAV dynamic stability study was carried out, which determined the behavior of the aircraft in disturbance situations generated by the conditions in which it will operate, specifically with regard to positioning, i.e. it was evaluated if the aircraft was able to eliminate and overcome the disturbances suffered in the course of his mission effectively. Stability is the conclusion of a chain of requirements that allow the aircraft to recover from the disturbance, or flight condition that it wants to analyze. For this, one of the aspects to take into account, is the distribution of weights that will determine the appropriate location ofthecenterofgravityoftheaircraft.Anotherimportant aspectisthecontroloftheaircraft, for this reason it is necessary to design the control surfaces of the same, because these modify the pressure distributions in the UAV, creating forces and moments that produce turning movements in the aircraft. In this project, the study of dynamic stability was carried out through a series of models with linear equations. These models allowed the analysis that was made to the aircraft in the different stages of its mission, giving priority to the following flight conditions: * Stability before and after takeoff. * Stability in the maximum ceiling of operation. (Cruise). * Behavior at different angles of attack. As the model presented changes in the control and state variables, it was necessary to estimate the stability and control derivatives, since they are the mathematical representation of the changes of forces and aerodynamic moments. It should be noted that the estimation of the stability derivatives was made through simulations in the Tornado software.
- ÍtemDiseño preliminar del fuselaje y tren de aterrizaje de una aeronave commuter tipo stolPérez, Julián Camilo; Velandia Castillo, Juan David; Bravo Mosquera, Pedro David
- ÍtemDiseño preliminar y conceptual de aeronave no tripulada para monitoreo de actividad volcánicaBravo Mosquera, Pedro David; Uribe Agudelo, Alvaro; Martins Abdalla, Alvaro
- ÍtemDiseño y fabricación de un vehículo aéreo no tripulado con energía solar para misiones de vigilancia civil(2016) Pedraza Betancourth, Nelson Javier; Parra Villamarín, Julio Enoc; Vaca Ríos, John Jairo; Bravo Mosquera, Pedro David; Cerón Muñoz, Hernán DaríoCon el fin de promover el desarrollo de las energías renovables y aprovechar las nuevas tecnologías en beneficio de la sostenibilidad, se presentan tanto el diseño como las metodologías de fabricación de un vehículo aéreo no tripulado experimental con energía solar para aplicaciones de vigilancia civil. A lo largo del documento, se proporciona el proceso histórico en torno al desarrollo de la aeronave. Por lo tanto, en la primera parte se muestra el diseño aerodinámico, que incluye los análisis 2-D y 3-D de la plataforma del ala mediante métodos numéricos y experimentales, el diseño analítico de la configuración del empenaje y las principales características del desempeño. análisis. Además, se describen los principales sistemas y componentes que caracterizan a la aeronave, como la configuración de las células solares fotovoltaicas, así como la electrónica y el sistema de control en el vehículo aéreo no tripulado. Por último, el modelado para la distribución de pesos de los componentes se realizó en una prueba preliminar utilizando herramientas CAD. Así, se obtuvo un proceso adecuado para la fabricación del vehículo aéreo no tripulado, considerando que la finalidad de la aeronave es ser lo más ligera y aerodinámica posible para cumplir con la misión para la que fue creada.