ES2560896T3 - Parte trasera del fuselaje con un escudo para una aeronave con motores montados en el fuselaje y método para la determinación del área del escudo - Google Patents
Parte trasera del fuselaje con un escudo para una aeronave con motores montados en el fuselaje y método para la determinación del área del escudo Download PDFInfo
- Publication number
- ES2560896T3 ES2560896T3 ES11382409.8T ES11382409T ES2560896T3 ES 2560896 T3 ES2560896 T3 ES 2560896T3 ES 11382409 T ES11382409 T ES 11382409T ES 2560896 T3 ES2560896 T3 ES 2560896T3
- Authority
- ES
- Spain
- Prior art keywords
- fuselage
- shield
- aircraft
- rear part
- internal shield
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000012634 fragment Substances 0.000 abstract 2
- 238000010521 absorption reaction Methods 0.000 abstract 1
- 239000002131 composite material Substances 0.000 abstract 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/10—Bulkheads
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type
- B64D27/14—Aircraft characterised by the type or position of power plants of gas-turbine type within, or attached to, fuselages
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
- B64D27/20—Aircraft characterised by the type or position of power plants of jet type within, or attached to, fuselages
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D2027/005—Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Laminated Bodies (AREA)
Abstract
Parte trasera de una aeronave que tiene un sistema de propulsión compuesto por dos motores (13) montados en cada uno de sus lados; teniendo la parte trasera del fuselaje (11) al menos un plano de simetría vertical (A-A); estando fabricada la parte trasera del fuselaje (11) con un material compuesto, e incluyendo un escudo interno (41) caracterizado por que: - el escudo interno (41) está ubicado en dicho plano de simetría vertical (A-A) y extendido en un área que cubre las posibles trayectorias de un conjunto pre-definido de fragmentos desprendidos de uno de dichos motores (13) en un evento de fallo que impactarían en elementos críticos del motor opuesto; - el escudo interno (41) tiene una forma plana y una capacidad de absorción de energía que permite detener dichos fragmentos.
Description
-El escudo no conlleva problemas de acústica y/o vibración, ya que no está conectado directamente a las zonas acústicamente excitadas del fuselaje.
-La fabricación del escudo es fácil debido a su configuración plana (no es necesario ajustar el escudo a la curvatura del fuselaje) y al casi constante ángulo de impacto que implica un espesor 5 constante del escudo.
-El escudo interno ubicado en el plano de simetría de la aeronave también ofrece una arquitectura segura para cualquier tipo de segregación de sistemas. De hecho, algunos sistemas segregados, como por ejemplo controles de vuelo, pueden estar ubicados a ambos lados del escudo.
Aunque se ha descrito la presente invención en conexión con varias realizaciones, puede apreciarse a 10 partir de la descripción que pueden hacerse varias combinaciones de elementos, variaciones o mejoras en ellas y que están dentro del alcance de la invención.
7
Claims (1)
-
imagen1 imagen2
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP11382409.8A EP2610164B1 (en) | 2011-12-28 | 2011-12-28 | Rear fuselage with a shield for an aircraft with fuselage-mounted engines and method for determining the area of the shield |
Publications (1)
Publication Number | Publication Date |
---|---|
ES2560896T3 true ES2560896T3 (es) | 2016-02-23 |
Family
ID=45418572
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
ES11382409.8T Active ES2560896T3 (es) | 2011-12-28 | 2011-12-28 | Parte trasera del fuselaje con un escudo para una aeronave con motores montados en el fuselaje y método para la determinación del área del escudo |
Country Status (6)
Country | Link |
---|---|
US (1) | US9359085B2 (es) |
EP (1) | EP2610164B1 (es) |
CN (1) | CN103183128B (es) |
CA (1) | CA2800452A1 (es) |
ES (1) | ES2560896T3 (es) |
RU (1) | RU2608983C2 (es) |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9845159B2 (en) * | 2013-03-07 | 2017-12-19 | United Technologies Corporation | Conjoined reverse core flow engine arrangement |
FR3020347B1 (fr) * | 2014-04-28 | 2016-05-20 | Airbus Operations Sas | Procede d'assemblage d'une partie arriere d'aeronef |
FR3032942B1 (fr) * | 2015-02-19 | 2018-11-23 | Safran Aircraft Engines | Ensemble propulsif pour aeronef comprenant un turboreacteur a soufflante non carenee et un pylone d'accrochage |
EP3106381B1 (en) * | 2015-06-15 | 2018-10-24 | Airbus Operations, S.L. | Aircraft with a protective shield against an engine blade release |
US9725155B2 (en) * | 2015-12-30 | 2017-08-08 | General Electric Company | Method and system for open rotor engine fuselage protection |
FR3048957B1 (fr) * | 2016-03-15 | 2018-03-09 | Airbus Operations | Ensemble moteur pour aeronef, comprenant des dispositifs souples de transmission d'efforts agences entre les capots d'inversion de poussee et le moteur |
US10934938B2 (en) | 2016-07-22 | 2021-03-02 | Raytheon Technologies Corporation | Boundary layer cooling air for embedded engine |
US20210284348A1 (en) * | 2016-08-08 | 2021-09-16 | Lord Corporation | Mounting systems, devices, and methods for aircraft engines |
ES2794623T3 (es) * | 2016-09-14 | 2020-11-18 | Airbus Operations Sl | Blindaje balístico desprendible integrado |
EP3335982B1 (en) * | 2016-12-16 | 2020-09-30 | Airbus Operations, S.L. | Aircraft having a rear section with a continuous skin for the fuselage and the vertical tail plane |
EP3375706B1 (en) * | 2017-03-15 | 2022-05-18 | Airbus Operations S.L. | Impact resistant fuselage |
US10487684B2 (en) * | 2017-03-31 | 2019-11-26 | The Boeing Company | Gas turbine engine fan blade containment systems |
US10550718B2 (en) * | 2017-03-31 | 2020-02-04 | The Boeing Company | Gas turbine engine fan blade containment systems |
FR3080837B1 (fr) * | 2018-05-02 | 2020-05-29 | Safran Aircraft Engines | Aeronef avec un module propulsif a helices non carenees agence a l'arriere d'un fuselage |
DE102019129998B4 (de) * | 2019-11-07 | 2022-04-28 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Flugzeug mit Strahltriebwerken oberhalb der Tragflügel und mit einer lokalen Erweiterung des Rumpfs zur Reduktion aerodynamischer Widerstände bei transsonischen Fluggeschwindigkeiten |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1402431A (en) * | 1918-03-15 | 1922-01-03 | Melville W Mix | Airplane fuselage |
FR1460060A (fr) * | 1965-10-15 | 1966-06-17 | Nord Aviation | Fuselage de grande capacité et aérodyne correspondant |
US4674712A (en) * | 1985-01-22 | 1987-06-23 | The Boeing Company | Double-lobe fuselage composite airplane |
US5114097A (en) * | 1991-04-29 | 1992-05-19 | Williams International Corporation | Aircraft |
US5866272A (en) * | 1996-01-11 | 1999-02-02 | The Boeing Company | Titanium-polymer hybrid laminates |
GB2320525A (en) * | 1996-12-18 | 1998-06-24 | British Aerospace | Mounting of powerplant in aircraft |
JP2003104298A (ja) * | 2001-10-01 | 2003-04-09 | Yoshito Takeshima | 旅客機 |
US7261257B2 (en) * | 2004-11-23 | 2007-08-28 | Helou Jr Elie | Cargo aircraft |
FR2892705B1 (fr) * | 2005-11-03 | 2009-04-24 | Airbus France Sas | Aeronef a impact environnemental reduit. |
RU2299838C1 (ru) * | 2005-12-08 | 2007-05-27 | Михаил Михайлович Кононенко | Устройство для защиты космических аппаратов и станций от высокоскоростного ударного воздействия частиц космической среды |
ES2342866B1 (es) * | 2007-11-30 | 2011-05-18 | Airbus España, S.L. | Fuselaje de aeronave resistente a impactos. |
FR2935953B1 (fr) * | 2008-09-18 | 2010-10-29 | Airbus France | Partie arriere d'aeronef comprenant deux semi-structures de support de moteurs rapportees l'une sur l'autre au sein d'un espace interieur d'aeronef. |
RU2489322C2 (ru) * | 2009-03-16 | 2013-08-10 | Эйрбас Оперэйшнз Гмбх | Охлаждающее устройство для системы охлаждения воздушного судна, система охлаждения воздушного судна и способ ее эксплуатации |
ES2398287B1 (es) | 2010-03-29 | 2014-01-29 | Airbus Operations S.L. | Fuselaje de aeronave resistente al impacto y tolerante al daño. |
US20130001356A1 (en) * | 2011-07-01 | 2013-01-03 | Airbus Operations, S.L. | Reinforced aircraft fuselage |
-
2011
- 2011-12-28 ES ES11382409.8T patent/ES2560896T3/es active Active
- 2011-12-28 EP EP11382409.8A patent/EP2610164B1/en not_active Not-in-force
-
2012
- 2012-12-21 US US13/724,360 patent/US9359085B2/en not_active Expired - Fee Related
- 2012-12-27 RU RU2012157756A patent/RU2608983C2/ru active
- 2012-12-28 CN CN201210587545.8A patent/CN103183128B/zh active Active
- 2012-12-28 CA CA2800452A patent/CA2800452A1/en not_active Abandoned
Also Published As
Publication number | Publication date |
---|---|
RU2608983C2 (ru) | 2017-01-30 |
EP2610164B1 (en) | 2015-10-28 |
EP2610164A1 (en) | 2013-07-03 |
US20130214090A1 (en) | 2013-08-22 |
US9359085B2 (en) | 2016-06-07 |
CN103183128A (zh) | 2013-07-03 |
CN103183128B (zh) | 2017-07-18 |
CA2800452A1 (en) | 2013-06-28 |
RU2012157756A (ru) | 2014-07-10 |
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