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Universidad Politécnica De Madrid ETSI Aeronáuticos ANÁLISIS DE Universidad Politécnica de Madrid ETSI Aeronáuticos ANÁLISIS DE LA EMBARCABILIDAD DE AVIONES DE COMBATE TERRESTRES Tesis Doctoral Marzo de 2016 Doctorando: D. José Luis Hernando Díaz Director: D. Rodrigo Martínez-Val Peñalosa A mis padres, por su ejemplo. A mi esposa e hijos, por su cariño. Gracias por estar aquí, a mi lado. Agradecimientos Me gustaría expresar mi especial gratitud a tres de mis compañeros de Unidad Docente, los Sres.: D. Enrique de la Fuente Tremps, D. Román Torres Sánchez, y D. Ricardo Callado Sanz. Ellos han sido los que han estado día tras día animándome a seguir adelante. Quisiera mencionar también a los Sres. D. Manuel Ortega Pérez, y a D. José Manuel Casteleiro Villalba, que ya no están en activo, y a mis también compañeros de Escuela, los Sres.: D. Eugenio Guillem Alonso, D. Miguel Ángel Sanz Gómez, D. Jorge Llamaza- res González, Dña. María Eugenia Nieto de Antonio, y D. David Pérez Jara. Conozco a todos ellos desde hace muchos años, y gracias a su generosidad he ido enriqueciéndome alasombradesuconocimientoyexperienciaprofesional. También y especialmente, agradezco a mi director de tesis D. Rodrigo Martínez-Val Peñalosa, su confianza en mí y su tesón en todo el desarrollo de este trabajo. Sin su ayuda y amplia experiencia no sé si habría podido encauzar adecuadamente la idea original. Y por último, gracias a las Sras. Dña. Laura Hernando Guadaño y Dña. Consuelo Fernández Jiménez, cuyos comentarios en los momentos de desaliento supusieron una auténtica brisa de aire fresco. Gracias a todos, de corazón. Gracias. José Luis Hernando Díaz Madrid, marzo de 2016 Índice Resumen 1 Summary 3 1. Planteamiento general 5 1.1.Motivación.................................. 5 1.2. Ámbito científicodelatesis......................... 6 1.3.Objetivos................................... 7 1.4.Precedentes.................................. 10 1.5.Aportaciones................................. 11 2. Maniobra de lanzamiento 13 2.1.Introducción.................................. 13 2.2.Análisismecánicodelproceso........................ 13 2.2.1. Ángulos que afectan al empuje . 14 2.2.2.Fuerzadelacatapulta........................ 16 2.3.Consideracionesdinámicasyenergéticas.................. 26 2.3.1. Incremento de velocidad debido a la planta propulsora . 35 2.4.Actituddelaviónsobrecubierta...................... 37 3. Maniobra de impulsión 45 3.1.Análisismecánicodelproceso........................ 47 3.1.1.Tramorectosobrecubierta..................... 50 3.1.2.Tramocurvodelacubierta..................... 51 3.1.3.Trayectoriasemibalística....................... 54 3.2.Vientoencubierta.............................. 57 3.2.1.Tramorecto.............................. 57 3.2.2.Tramocurvo............................. 60 3.2.3.Tramodevuelosemibalístico.................... 63 3.3.Análisisdelainteracciónconeltrendeaterrizaje............. 63 i ii ÍNDICE 3.3.1.Modelomecánicode2gdl...................... 63 3.3.2.Modelomecánicode3gdl...................... 76 4. Maniobra de recuperación 79 4.1.Planteamientodelproblema......................... 79 4.2.Consideracionesenergéticas......................... 80 4.2.1.Correcciónporelmovimientodelbuque.............. 82 4.2.2. Energía mínima y energía máxima . 86 4.3. Consideraciones específicasdelacubiertadesalineada.......... 106 4.3.1.Persecucióndelarampa....................... 107 4.3.2.Persecucióndelaproa........................ 108 4.4.Detenciónsobrecubierta........................... 110 4.4.1. Empleo de un motor de detención . 116 4.5.Ganchodeapontaje............................. 125 4.5.1. Caso de diseño: Eurofighter Typhoon ................ 135 4.5.2.Dispositivoabsorbedor-mantenedor................. 144 5. Tren de aterrizaje 149 5.1.Introducción.................................. 149 5.1.1. Configuracióngeneral........................ 149 5.2.Compatibilidadconelsistemadelanzamiento............... 151 5.3.Consideracionesdelarecuperación/toma................. 151 5.3.1.Requisitos............................... 151 5.3.2. Modelización del conjunto neumático-amortiguador . 155 5.3.3. Ecuación dinámica vertical simplificada.............. 157 5.3.4.Consideracionesenergéticas..................... 160 5.3.5.Consideracionesgeométricas..................... 165 6. Disposición replegada 177 6.1. Definición................................... 177 6.2.Introducción.................................. 178 6.3. Consideraciones mecánicas y arquitectónicas . 183 6.3.1.Plegadodeplanos.......................... 187 6.3.2.Giro.................................. 202 6.3.3.Abatimientomixto.......................... 205 6.4.Impactoeneldiseño............................. 210 6.4.1.Incrementodepeso.......................... 212 ÍNDICE iii 7. Análisis de embarcabilidad 239 7.1.Introducción.Metodología.......................... 239 7.2.Embarcabilidad................................ 239 7.2.1.Niveldeembarcabilidadinicial................... 240 7.3.Estimacióndelniveldeembarcabilidad................... 241 7.3.1. Calificadores............................. 241 8. Selección de sistemas objeto de estudio 245 8.1.Adaptacióndeltrendeaterrizaje...................... 245 8.2. Adaptación/implementación del gancho . 245 8.3. Implementación de dispositivos de replegado . 256 8.3.1.Plegadodeplanos.Abisagramiento................. 260 9. Estudio de casos seleccionados 271 9.1. Eurofighter Typhoon ............................. 272 9.1.1.EFA:trendeaterrizaje....................... 277 9.1.2. EFA: embarcabilidad inicial de la configuración.......... 296 9.2. Saab Gripen .................................. 314 9.2.1. Gripen:trendeaterrizaje...................... 319 9.2.2. Gripen: embarcabilidad inicial de la configuración........ 322 10.Conclusiones 335 11.Futuras líneas de investigación 337 A. Acrónimos y abreviaturas 339 B. Aviación embarcada y buques portaaviones 343 B.1.Lasoperacionesaeronavales......................... 343 B.1.1.Capacidaddedisuasión....................... 347 B.1.2. Agilidad y flexibilidaddeutilización................ 347 B.1.3.Versatilidadypotenciadefuego.................. 349 B.2.Consideracionescolaterales.......................... 350 B.3.Panoramainternacional........................... 352 B.3.1.EE.UU................................. 352 B.3.2.Francia................................ 353 B.3.3.Rusia................................. 356 B.3.4.ReinoUnido............................. 358 B.3.5.EspañaeItalia............................ 366 B.3.6.India.................................. 370 B.3.7.China................................. 374 B.3.8.Brasil................................. 376 B.3.9.Australia............................... 378 iv ÍNDICE B.3.10.Argentina............................... 380 B.3.11.Tailandia............................... 380 Resumen La retirada de los aviones Harrier, en servicio en operaciones embarcadas con Ar- madas de diferentes países, está basada en la perspectiva de poder sustituirlos por el F-35B, versión de operación vertical del controvertido programa Joint Strike Fighter. Este proyecto en realidad engloba el diseño de tres aviones de combate muy distintos entre sí, que, a pesar de tener una considerable parte en común, y dados sus muy dife- rentes requisitos, es un proyecto tremendamente complejo. Como consecuencia de todo esto, y ante el sobrecoste y los continuos retrasos acumulados en el desarrollo de un pro- yecto tan ambicioso, se plantean numerosas incertidumbres temporales y económicas, que hacen atractivo el estudio de posibles alternativas de menor riesgo. Esta tesis es un trabajo de investigación tecnológica que plantea el estudio de la modificación de determinados diseños de aviones de combate de operación terrestre, con idea de que puedan satisfacer los exigentes requisitos de operación desde un buque. Tras estudiar las peculiaridades de dichas operaciones, y analizar los tipos de buque y sus necesidades de modificación asociadas más importantes, se propone qué accio- nes a realizar, y se identifican las áreas de mayor interés, permitiendo establecer un procedimiento objetivo de comparación, con el fin de poder seleccionar los potenciales candidatos para su adaptación. Se aplica esta metodología, en particular, a dos casos de diseño de especial interés; el Eurofighter Typhoon yelSaab Gripen. En ambos, y por lo que respecta a las modi- ficaciones planteadas, no se aprecian especiales dificultades que permitan descartar las posibilidades técnicas de su adaptación. Por último, y dada la complejidad de la conse- cución del objetivo final, se sugieren posibles líneas de investigación, desde completar y extender la filosofía de trabajo a otros subsistemas, al análisis de los costes de las modificaciones. 1 Summary The Harrier fleet has been in active service in several Navies from different countries as a carrier-based aircraft. However, this aircraft may be withdrawn and replaced by the F-35B, a vertical capability version of the controversial Joint Strike Fighter (JSF) programme, which great complexity and constant development delays raise numerous uncertainties from a temporal and economical point of view. In fact, this program encompasses the design of three different fighter aircraft which, at the same time, share many similarities. All these aspects led us to undertake the analysis of other lower-risk alternatives. This thesis is a technological research work aimed at studying those design changes required for several fighter aircraft, initially designed for ground operation, in order to make them fullfil the highly demanding requirements for operating from aircraft carriers. After analizing the peculiarities
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