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Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 < aeroteca.com > Depósito Legal B 9066-2016 Título: Los Motores Aeroespaciales A-Z. © Parte/Vers: 14/12 Página: 3901 Autor: Ricardo Miguel Vidal Edición 2018-V12 = Rev. 01 -Ya en 1968 se hizo el RS-22 conocido como Flexem por su capacidad de variar el empuje entre casi 270 a 4000 lbs. y funcionando con C1F3 / Hydrazine. “RS-19” -El RS-2100, de diseño reciente en 1999 previsto para proyectos actuales y futuros. Para ser utilizado como boos- ters o ayuda para los vehículos portadores. Utiliza “RS-22” LOX y LH2. “RS-23” -De 1972, el RS-23 que vemos sin la tobera, sólo la cá- mara de combustión. Podía llevar varias toberas según utilización, de 2700 Kgf aprox. “RS-2100” (PeT) -Sin embargo el motor RS-2101A es del año 1968, de- rivado del RS-14. Tenía una evolución en el RS-2101C. “RS-2101A” (PeT) “RS-27 y RS-27A” (PeT) * * * Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 Este facsímil es < aeroteca.com > Depósito Legal B 9066-2016 ORIGINAL si la Título: Los Motores Aeroespaciales A-Z. © página anterior tiene Parte/Vers: 14/12 Página: 3902 el sello con tinta Autor: Ricardo Miguel Vidal VERDE Edición: 2018-V12 = Rev. 01 -El RS-27 hizo el primer vuelo en 1972 y el último hacia 1990 (el RS-27A de 1989 a 1999). de unos 105000 Kgf de empuje, funcionando con Lox/keroseno fué utilizado en los misiles Delta. -El RS-28 era un pequeño motor de 270 Kgf. utilizado en el Space Shuttle para control en orbita. Diseñado hacia 1972. “RS-36” (PeT) -En 1981 se hace el RS-41 para naves espaciales, de 1220 Kgf. De éste mismo año es el RS-42 de sólo 45 Kgf, para control axial. Y lo mismo el RS-43 para control de actitud y sólo 2 Kgf de empuje. “RS-28” -El RS-32 ya salió en páginas anteriores como de etapas superiores del Minuteman, derivado a su vez del RS-14. -El RS-34 es un motor cohete de 1200 kgf para empujes axiales, del año 1978. Existe la versión de control de Acti- tud (Attitude) con sólo 31 Kgf. Es un RS-34 Att. Control. “RS-41, RS-42 y RS-43” “RS-34 y RS-34 A-C” -El motor RS-36, utilizado en experimentos de propulsión axial, con algo más de 5’5 ton. de empuje y utilizando N2O4 y MMH. Se conocía como “Motor Sostenedor”. “RS-45, motor de control” * * * Blue Prints -Antes no existían los actuales “Plotters” para reproducir grandes planos. Durante muchos años se han utilizado -y todavia se utilizan- los famosos “Blue Prints”. Vemos a un operario haciendo una. Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 < aeroteca.com > Depósito Legal B 9066-2016 Título: Los Motores Aeroespaciales A-Z. © Parte/Vers: 14/12 Página: 3903 Autor: Ricardo Miguel Vidal Edición 2018-V12 = Rev. 01 -El RS-51, del año 1984 y con 1178 Kgf de empuje en el -Los motores RS-56 OSA y OBA, son los MA-5A mencio- vacio para naves o estaciones espaciales. nados al principio del capítulo y utilizados en los cohetes Atlas II A. Con unos 40000 Kgf en el vacio. Utilizados en los misiles Delta IV. “Motor RS-51” “RS-68” -El RS-71 es un motor experimental del tipo “Aerospike” del que buscamos más información. -El RS-72 construído en conjunción (Joint-Venture?) con la DASA (Daimler-Aerospace alemana. Para estaciones superiores de cohetes portadores. Con 5650 Kgf. “RS-52” -El RS-52 es un Thruster de 11 kgf. para Estacion Espa- cial como motor de estabilización. Basado en tecnología “resistojet” . “Delta IV, con RS-68” “DASA / Rocketdyne RS-72” (PeT) * * * Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 Este facsímil es < aeroteca.com > Depósito Legal B 9066-2016 ORIGINAL si la Título: Los Motores Aeroespaciales A-Z. © página anterior tiene Parte/Vers: 14/12 Página: 3904 el sello con tinta Autor: Ricardo Miguel Vidal VERDE Edición: 2018-V12 = Rev. 01 -Otro motor reciente, de 1999, el RS-74 es un booster para vehículos de lanzamiento considerado NG (Next Genera- tion), funcionando con LOX / LH2. “Nave SOTV y RS-77” -De las nuevas generaciones de motores, el RS-82 es considerado “Non-Toxic”, para estaciones superiores y utilizando H2O2 / Keroseno. “RS-74” (PeT) -En 1998 se desarrolla el RS-76, un motor reusable para ser utilizado en el Space Shuttle. “RS-82” (PeT) “RS-76” (PeT) -El RS-77 es original en el sentido de que difi ere totalmente del sistema de construcción y principio de funcionamiento de los anteriores. -Para el proyecto SOTV ó Vehículo de Tránsito en Orbita Solar. Utiliza la captación de la energia solar para el calen- tamiento del hidrógeno LH2. “Dos vistas del RS-83” (PeT) * * * NOTA : Mientras no se solicite y otorgue la autorización de POPMECH para reproducir algunas imagenes que aparecen en éste Suplemento 7, se considera el mismo no divulgable comercialmente. Solo se ofrecerá sin cargo a quién lo solicite de los poseedores del texto principal como forma de tener más completa ésta Tesis Post-Profesional del Autor de la “A-Z”. En tanto dicho trámite no ocurra, el autor considera éste Apéndice (Ammendment) como Restringido y sólo para consultas propias. (Apéndice Apócrifo). Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 < aeroteca.com > Depósito Legal B 9066-2016 Título: Los Motores Aeroespaciales A-Z. © Parte/Vers: 14/12 Página: 3905 Autor: Ricardo Miguel Vidal Edición 2018-V12 = Rev. 01 -Las dos vistas del RS-83 de la página anterior todavía son -Del Apendice 6: Pionera americana en el estudio y de diseño CAD-CAM. Para 650000 lbs de empuje y con desarrollo de los Scramjets o Aerospikes. Destaca el destino a los nuevos motores del programa SSME (Shu destinado al X-33, de forma rectangular y que vemos en ttle) en clara competencia con el Cobra de Aerojet/P&W. el siguiente dibujo. -Llegamos ahora a los más avanzados, los Aerospike RS-2200 y XRS-2200, el segundo conocido dentro de Rocketdyne como RS-69. (ver también RS-71). -No poseen la tobera clásica en forma de trompeta sino que son lineares. Diseños de 1998, y con empujes respetables, aptos ademas para las más altas velocidades conocidas. “El Aerospike funcionando -dibujo-” -Las cámaras de combustión dispuestas linealmente a ambos lados de dos superfi cies inclinadas algo concavas hacen que los chorros se peguen a ellas y se unan al tér- mino de las mismas. “RS-89 en pruebas” -El empuje del RS-2200 es de más de 224500 Kgf. en el vacio. Mientras que el del XRS-2200 es de más de 121500 Kgf en el vacio. Ambos con destino al X-33 (Cancelado). “Un SR-71 probando su Aerospike” -Un banco de pruebas real fué “La Máquina Bizarra” o el Lockheed-Martin SR-71, capaz de volar pos sí sólo a 3 Mach. -El X-33 de la Lockheed-Martin tiene dos cámaras Aero- spikes (ver Scramjets en éste mismo apéndice), tal como vemos en el siguiente dibujo que simula el aparato en “Salidas rectangulares del XRS-2200, en X-33” vuelo. * * * Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 Este facsímil es < aeroteca.com > Depósito Legal B 9066-2016 ORIGINAL si la Título: Los Motores Aeroespaciales A-Z. © página anterior tiene Parte/Vers: 14/12 Página: 3906 el sello con tinta Autor: Ricardo Miguel Vidal VERDE Edición: 2018-V12 = Rev. 01 “MB-3 ó LR79-N” (PeT) -Se ha recibido un dibujo del RS-84 que todavia no se había mencionado en el texto principal. Reusable. “El X-33 con sus dos motores en marcha” -Actualmente en el Grupo Pratt & Whitney. Antes de Boe- ing Company. Y antes de North American Aviation NAA que empezó sus estudios poco despues de la WWII, con las V-2 alemanas capturadas. -La North American fundó la Rocketdyne en en 1967. En el año 1996 fué adquirida por Boeing y fi nalmente en el 2005 pasa a la Pratt & Whitney. -En el texto principal se mencionan los motores MB-3 con sus equivalentes defi niciones ofi ciales de LR79. -En el Museo Pima Air de USA, vemos ratifi cada ésta equivalencia en los LR79-N que tienen expuestos. “Rocketdyne RS-84” -La NASA canceló el programa RS-84 en el 2004. El “MB-3 en la Sala de Exhibición” (PeT) motor tenía 1064 Klbf de empuje a nivel del mar y 1130 en el vacio. * * * Observación -Los motores de cada fotograma no guardan relación con la proporción del tamaño entre ellos ni con los motivos. Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 < aeroteca.com > Depósito Legal B 9066-2016 Título: Los Motores Aeroespaciales A-Z. © Parte/Vers: 14/12 Página: 3907 Autor: Ricardo Miguel Vidal Edición 2018-V12 = Rev. 01 -Constructivamente, dos conjuntos de pequeñas cámaras -El empuje específi co era de 324 segundos y consumía de combustión se encuentran alineadas a ambos lados de LOX/RP-1 (Oxígeno líquido y keroseno). Apto para 100 la estructura. Proveen el fl ujo primario al que se le sumará misiones, con empuje variable entre el 100% y el 65%. el secundario por la parte central inferior del motor. -Referente al Aerospike X-33 de Rocketdyne continúan los ensayos en la Nasa Lewis Research Center y en John Stennis Center. -Como se menciona en el texto principal, los aerospikes puede ser lineales o anulares. -El X-33 es lineal y como característica principal es que al contrario que los motores cohete normales en que la combustión se produce en una cámara, el aerospike tiene la combustión externa.
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  • 2019 UNIVERSAL REGISTRATION DOCUMENT Including the Annual Financial Report CONTENTS

    2019 UNIVERSAL REGISTRATION DOCUMENT Including the Annual Financial Report CONTENTS

    2019 UNIVERSAL REGISTRATION DOCUMENT Including the Annual Financial Report CONTENTS EXTRACT FROM THE INTEGRATED REPORT 2 5 NON-FINANCIAL SAFRAN AT A GLANCE 3 PERFORMANCE 241 EDITORIAL 4 5.1 Organization and management of non‑financial performance 242 GROUP PROFILE 6 5.2 Key non‑financial risks 246 ECOSYSTEM 12 5.3 Business ethics, export and customs controls 251 STRATEGY AND BUSINESS MODEL 18 5.4 Responsible purchasing 256 5.5 Climate and environment 258 CORPORATE GOVERNANCE 40 5.6 Health and safety 265 PERFORMANCE AND VALUE CREATION 46 5.7 Human resources 268 5.8 Social dialogue 275 5.9 Social impact 276 5.10 Methodological note and ITP report 278 5.11 Cross‑reference table for the Non‑financial Information Statement 284 PRESENTATION 1 OF THE GROUP 49 6 1.1 Safran overview 50 CORPORATE GOVERNANCE 287 1.2 Group businesses 54 6.1 Safran’s corporate governance structure 288 1.3 Competitive position 74 6.2 Membership structure of the Board Research and development 74 1.4 of Directors 291 1.5 Industrial investments 81 6.3 Operating procedures and work of Sites and production plants 83 1.6 the Board of Directors and the Board Safran performance and quality policy 84 1.7 Committees 324 6.4 Application of the AFEP‑MEDEF Corporate Governance Code 334 6.5 Directors’ interests in the Company’s share capital 334 2 REVIEW OF OPERATIONS IN 2019 6.6 Compensation policy and compensation AND OUTLOOK FOR 2020 87 packages for corporate officers 335 6.7 Cross‑reference table for the corporate 2.1 Comments on the Group’s performance governance report prepared