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Diseño Preliminar De Un Flexwing Trike (Ultraliviano) Biplaza

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Diseño Preliminar De Un Flexwing Trike (Ultraliviano) Biplaza DISEÑO PRELIMINAR DE UN FLEXWING TRIKE (ULTRALIVIANO) BIPLAZA JORGE LUIS CALDERON PEREZ IVAN FELIPE CAÑON GONZALEZ UNIVERSIDAD DE SAN BUENAVENTURA FACULTAD DE INGENIERÍA PROGRAMA INGENIERÍA AERONÁUTICA BOGOTÁ 2008 DISEÑO PRELIMINAR DE UN FLEXWING TRIKE (ULTRALIVIANO) BIPLAZA JORGE LUIS CALDERON PEREZ IVAN FELIPE CAÑON GONZALEZ Trabajo presentado como requisito parcial para optar al título de profesional en Ingeniería aeronáutica. Asesor Temático, Carlos Bohórquez Ingeniero Mecánico UNIVERSIDAD DE SAN BUENAVENTURA FACULTAD DE INGENIERÍA PROGRAMA INGENIERÍA AERONÁUTICA BOGOTÁ 2008 NOTA DE ACEPTACIÓN _______________________ _______________________ _______________________ _______________________ _______________________ ___________________________________ Firma del presidente del jurado ___________________________________ Firma del Jurado ___________________________________ Firma del Jurado Bogotá D.C. 31, 10,2008 DEDICATORIA Esta tesis la dedico a toda mi familia que a la distancia me apoyó en todo lo que pudo en todo momento, a mi papá, a mi mamá y a mis dos hermanos que aunque no estuvieron presentes en la mayor parte de este proceso educativo su apoyo a la distancia fue importante. También dedico esta tesis a mis tías y mi abuela que me apoyaron en todo momento desde el primer día que llegué a estudiar a la universidad de San Buenaventura, hasta estos últimos días de estudio. JORGE LUIS CALDERON PEREZ DEDICATORIA Ha sido un proceso largo que comenzó hace cinco años en el cual hubo grandes esfuerzos pero también grandes satisfacciones. Este trabajo no es más que la culminación de un proceso y el comienzo de otro lleno de desafíos y responsabilidades. Este trabajo lo dedico a mi familia que ha hecho un gran esfuerzo al permitirme estudiar y darme esta gran oportunidad que pocos tienen, a ellos les dedico este proyecto. IVAN FELIPE CAÑON GONZALEZ AGRADECIMIENTOS Al ingeniero Carlos Bohórquez que nos ayudó en la elaboración de este documento y en el tema que le compete que es el tema de las estructuras, al ingeniero Jaime Alberto Escobar, por su aporte en la parte de simulación, al ingeniero pedro por sus recomendaciones y por último a nuestro amigo compañero e ingeniero aeronáutico Cesar Augusto Rozo Jiménez, que sin su ayuda hubiese sido imposible la realización de este proyecto. TABLA DE CONTENIDO Pag INTRODUCCIÓN 1 1 PLANTEAMIENTO DEL PROBLEMA 3 1.1 ANTECEDENTES 3 1.2 DESCRIPCIÓN Y FORMULACIÓN DEL PROBLEMA 4 1.3 JUSTIFICACIÓN 5 1.4 OBJETIVOS 6 1.4.1 Objetivo general. 6 1.4.2 Objetivos específicos. 6 1.5 ALCANCES Y LIMITACIONES 6 1.5.1 Alcances. 6 1.5.2 Limitaciones. 7 2 MARCO DE REFERENCIA 8 2.1 MARCO TEÓRICO CONCEPTUAL 8 2.1.1 Descripción general. 11 2.1.2 Componentes principales. 12 2.1.3 El ala. 12 2.1.4 La estructura del trike. 16 2.1.5 Aerodinámica del trike. 18 2.2 MARCO LEGAL 20 3. METODOLOGÍA 21 3.1 ENFOQUE DE LA INVESTIGACIÓN 21 3.2 LINEA DE INVESTIGACIÓN DE LA UNIVERSIDAD 21 3.3 TÉCNICAS DE RECOLECCIÓN DE DATOS 21 4. DESARROLLO INGENIERIL 22 4.1 RECOLECCIÓN DE DATOS 22 4.2 MISIÓN DE LA AERONAVE 26 4.3 DISEÑO CONCEPTUAL DEL TRIKE 27 4.3.1 Determinación Conceptual De Pesos 27 4.3.2 Comparación entre peso- área alar (w/s) y la velocidad de pérdida. 29 4.4 SELECCIÓN DEL PERFIL 41 4.4.1 Perfil aerodinámico. 42 4.4.2 Análisis en software para la selección del perfil. 43 4.4.2.1 Validación del perfil en análisis computacional. 44 4.4.2.2 Comparación de varios perfiles en un software confiable (xfoil). 46 4.5 DIMENSIONAMIENTO Y CONFIGURACIÓN DEL ALA 49 4.6 AERODINÁMICA DEL ALA. 55 4.6.1 Coeficiente de sustentación (lift) para alas convencionales. 55 4.6.2 Distribución de la sustentación a lo largo de ala. 58 4.6.3 Coeficiente de sustentación (lift) para alas volantes. 63 4.6.4 Coeficientes de momento. 68 4.6.5 Coeficiente de resistencia al avance (drag). 70 4.7 ANÁLISIS DEL ALA EN FLUJO COMPUTACIONAL AVL 75 4.7.1 Validación del programa AVL. 75 4.7.2 Análisis del ala en flujo computacional AVL. 79 4.7.3 Analisis del ala en flujo computacional y comparacion con el analisis teorico. 79 4.7.4 Comparación de resultados aerodinámicos. 82 4.8 DINÁMICA DE VUELO 83 4.8.1 Estabilidad longitudinal. 83 4.8.2 Estabilidad lateral. 86 4.8.3 Derivada debido al cabeceo del ala. 90 4.8.4 Derivada debido a los efectos de la hélice. 90 4.8.5 Estabilidad direccional. 91 4.9 DIMENCIONAMIENTO DEL FUSELAJE 93 4.10 ESTIMACIÓN DEL COEFICIENTE DE RESISTENCIA AL AVANCE 96 EN EL FUSELAJE 4.10.1 Coeficiente de resistencia paracito del fuselaje. 96 4.10.2 Coeficiente de resistencia al avance del tren de aterrizaje. 97 4.11 CENTROS DE GRAVEDAD 98 4.12 ANÁLISIS ESTRUCTURAL DE LA AERONAVE PENDULAR 102 4.12.1 Estructura del fuselaje. 102 4.12.2 Estimación de los factores de carga para aeronaves tipo pendular. 104 4.12.3 Diagrama de V-N. 105 4.12.4 Modelación de la estructura en SOLID EDGE. 110 4.12.5 Análisis de elementos finitos en software ANSYS. 110 4.12.6 Estructura del ala modelación en SOLID EDGE. 114 4.12.7 Análisis de elementos finitos en software ANSYS para el ala. 115 4.12.8 Modelación de otras partes principales de la aeronave. 117 4.13 TREN DE ATERRIZAJE 120 4.13.1 Ubicación del tren de aterrizaje respecto al centro de gravedad y las 120 cargas a soportar. 4.13.2 Selección de las llantas. 122 4.13.3 Estimación del track del tren principal. 123 4.13.4 Esfuerzos resistidos y amortiguamiento del Tren principal. 125 4.13.5 Esfuerzos resistidos y amortiguamiento del tren de nariz. 128 4.13.6 Sistema de frenado. 131 4.14 SELECCIÓN DE INDICADORES DE VUELO Y RADIO NAVEGACION 135 4.14.1 La selección de los indicadores de vuelo. 135 4.14.2 Radio navegación y comunicaciones. 139 4.15 SELECCIÓN DEL MOTOR Y LA HÉLICE 143 4.15.1 Selección del motor. 143 4.15.2 Selección de la hélice. 148 4.16 EVALUACIÓN DE DESEMPEÑO 151 4.16.1 Desempeño de la aeronave estático. 151 4.16.2 Desempeño de la aeronave dinámico. 157 4.16.2.1 Desempeño de la aeronave en un banqueo. 158 4.16.2.2 Desempeño de pull-up y de pull-down. 160 5 PRESENTACIÓN Y ANÁLISIS DE RESULTADOS 167 5.1 PERFORMANCE 167 5.1.2 Geometría del ala. 167 5.1.3 Velocidades de operación. 168 5.1.4 Pesos calculados para la aeronave pendular. 168 5.1.5 Datos aerodinámicos del ala. 169 5.1.6 Desempeño de la aeronave. 173 5.2 ESTABILIDAD Y CONTROL 175 5.3 ESTRUCTURAS 175 5.4 ANÁLISIS DE DATOS DEL TREN DE ATERRIZAJE. 177 5.5 ANALISIS DE DISTANCIA DE DESPEGUE Y ATERRIZAJE. 180 5.6 ANALISIS DE COSTOS 180 6. CONCLUSIONES 183 7. RECOMENDACIONES 185 8. BIBLIOGRAFÍA 186 LISTA DE FIGURAS Pag. FIGURA 1. Esquema simplificado de un trike visto de perfil. 11 FIGURA 2. Partes que conforman el ala. 13 FIGURA 3. Partes que conforman la estructura del trike. 17 FIGURA 4. Tendencia entre W/S y velocidad de pérdida. 31 FIGURA 5. Tendencia de trike diseñados entre índice de poder y velocidad 36 de crucero. FIGURA 6. Área de diseño del trike. 38 FIGURA 7. Perfiles más utilizados para aeronaves tipo pendular. 43 FIGURA 8. Perfil Naca 1408. 44 FIGURA 9. Resultados obtenidos por Xfoil del perfil utilizado para la 45 validación del perfil Naca 1408. FIGURA 10. Gráfica de datos experimentales del perfil naca 1408. 46 FIGURA 11. Comparación del perfil EPPLER 182 y el NACA 1408. 47 FIGURA 12. Comparación de varios perfiles validados en el software. 48 FIGURA 13. Diferentes tipos de alas deltas. 49 FIGURA 14. Geometría del ala. 53 FIGURA 15. Vorticidad que genera sustentación. 54 FIGURA 16. Pendiente del coeficiente de sustentación versus el ángulo de 56 ataque analizado como ala convencional. FIGURA 17. Geometría que describe el ala con sus respectivas ecuaciones. 57 FIGURA 18. Distribución básica del ala izquierda a diferentes ángulos de 59 ataque. FIGURA 19. Distribución adicional del ala debido al ángulo de torsión. 60 FIGURA 20. Distribución debido a la torsión generando una sustentación de 61 cero. FIGURA 21. Distribución total del ala a lo largo de la envergadura 62 parte izquierda del ala. FIGURA 22. Coeficiente de Sustentación generada a un ángulo de 63 5 grados. FIGURA 23. Comparación de pendientes de teoría alas deltas y teoría de 64 alas convencionales. FIGURA 24. Comparación entre alas convencionales y alas delta. 66 FIGURA 25. Pendiente de sustentación de gráficos experimentales de la 67 NASA. FIGURA26. Validación delas teorías de pendientes de sustentación con papers 68 de la NASA sobre alas delta. FIGURA27. Factor de drag inducido versus la relación de cuerdas. 72 FIGURA 28. Gráfica experimental NASA a cero grados; la grafica usa forma 76 de círculo para cero grados. FIGURA 29. Modelación en flujo computacional del ala que se va a validar en 77 AVL. FIGURA 30. Datos dados por el programa de flujo computacional del ala que 78 se va a validar. FIGURA 31. Comparación del coeficiente de sustentación de la validación y el 78 del paper de la NASA. FIGURA 32. Modelación del ala en flujo computacional. 80 FIGURA 33. Pendiente y coeficiente de momento obtenidos en flujo 82 computacional a diferentes ángulos de ataque. FIGURA 34. Comparación resultados teóricos y resultados computacional. 83 FIGURA 35. Área de región de la aeronave. 84 FIGURA 36. Variación del coeficiente de momento a diferentes ángulos de 86 ataque variando el centro de gravedad.
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