ES2171729T3 - Estructura metalica, hueca, monobloque y disimetrica tal como un borde de fuga de un frente de ataque de un ala de aeronave y su procedimiento de fabricacion. - Google Patents
Estructura metalica, hueca, monobloque y disimetrica tal como un borde de fuga de un frente de ataque de un ala de aeronave y su procedimiento de fabricacion.Info
- Publication number
- ES2171729T3 ES2171729T3 ES96934900T ES96934900T ES2171729T3 ES 2171729 T3 ES2171729 T3 ES 2171729T3 ES 96934900 T ES96934900 T ES 96934900T ES 96934900 T ES96934900 T ES 96934900T ES 2171729 T3 ES2171729 T3 ES 2171729T3
- Authority
- ES
- Spain
- Prior art keywords
- monoblock
- hollow
- disimetrica
- metal structure
- manufacturing procedure
- 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.)
- Expired - Lifetime
Links
- 238000004519 manufacturing process Methods 0.000 title abstract 2
- 239000002184 metal Substances 0.000 title 1
- 239000012528 membrane Substances 0.000 abstract 3
- 238000009792 diffusion process Methods 0.000 abstract 1
- 238000000465 moulding Methods 0.000 abstract 1
- 238000004804 winding Methods 0.000 abstract 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
- B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
- B21D26/053—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure characterised by the material of the blanks
- B21D26/055—Blanks having super-plastic properties
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
- B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
- B21D26/021—Deforming sheet bodies
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/02—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating by means of a press ; Diffusion bonding
- B23K20/023—Thermo-compression bonding
-
- 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
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
-
- 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
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
-
- 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
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
- Laser Beam Processing (AREA)
Abstract
UNA ESTRUCTURA METALICA HUECA, MONOBLOQUE Y ASIMETRICA, TAL COMO UN BORDE DE FUGA DE UN LARGUERO DE ATAQUE DE UN ALA DE AERONAVE, QUE COMPRENDE DOS MEMBRANAS EXTERNAS (16, 18) QUE PRESENTAN CURVATURAS DIFERENTES, UNIDAS ENTRE SI POR UN BORDE (20) Y QUE SE ALEJAN PROGRESIVAMENTE UNA DE OTRA. LA ESTRUCTURA COMPRENDE TAMBIEN REFUERZOS INTERNOS QUE DEFINEN PARES DE ALVEOLOS (26, 28) SEPARADOS POR UN TABIQUE MEDIANO. LA FABRICACION SE EFECTUA POR SOLDADURA POR DIFUSION Y MOLDEO SUPERPLASTICO, SIN ABERTURA DEL EQUIPO. PARA TENER EN CUENTA LA ASIMETRIA, SE REALIZAN CORTES (40, 42) EN LA MEMBRANA (18) QUE SE ALARGA MAS DURANTE LA CONFORMACION Y LAS PIEZAS RECORTADAS (44, 46) SE INSERTAN EN LA OTRA MEMBRANA (16).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9511975A FR2739832B1 (fr) | 1995-10-12 | 1995-10-12 | Structure metallique creuse monobloc et dissymetrique telle qu'un bord de fuite d'un bec d'attaque d'une voilure d'aeronef et son procede de fabrication |
Publications (1)
Publication Number | Publication Date |
---|---|
ES2171729T3 true ES2171729T3 (es) | 2002-09-16 |
Family
ID=9483463
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
ES96934900T Expired - Lifetime ES2171729T3 (es) | 1995-10-12 | 1996-10-11 | Estructura metalica, hueca, monobloque y disimetrica tal como un borde de fuga de un frente de ataque de un ala de aeronave y su procedimiento de fabricacion. |
Country Status (9)
Country | Link |
---|---|
US (1) | US5975465A (es) |
EP (1) | EP0800474B1 (es) |
JP (1) | JP3874423B2 (es) |
AU (1) | AU7304396A (es) |
CA (1) | CA2208435C (es) |
DE (1) | DE69618760T2 (es) |
ES (1) | ES2171729T3 (es) |
FR (1) | FR2739832B1 (es) |
WO (1) | WO1997013683A1 (es) |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP3647612B2 (ja) * | 1997-07-24 | 2005-05-18 | 富士重工業株式会社 | 航空機の前縁構造及びその製造方法 |
BE1014570A4 (fr) | 2002-01-11 | 2004-01-13 | Sonaca Sa | Procede de fabrication d'une structure cannelee et structure obtenue par ce procede. |
FR2867096B1 (fr) * | 2004-03-08 | 2007-04-20 | Snecma Moteurs | Procede de fabrication d'un bord d'attaque ou de fuite de renforcement pour une aube de soufflante |
FR2906320B1 (fr) * | 2006-09-26 | 2008-12-26 | Snecma Sa | Aube composite de turbomachine a renfort metallique |
FR2929539B1 (fr) * | 2008-04-08 | 2010-05-21 | Airbus France | Dispositif d'alimentation perfectionne pour systeme de pressage a chaud superplastique |
EP2110189A1 (de) * | 2008-04-18 | 2009-10-21 | ETH Zürich | Verfahren zur werkzeuglosen Umformung von Blech |
US9289816B2 (en) | 2009-01-22 | 2016-03-22 | Ihi Corporation | Production method of leading edge reinforcement of fan blade |
GB0913061D0 (en) * | 2009-07-28 | 2009-09-02 | Rolls Royce Plc | A method of manufacturing a reinforcing edge for a turbo machine aerofoil |
WO2012061573A1 (en) | 2010-11-05 | 2012-05-10 | Barnes Group Inc. | Hybrid metal leding edge part and method for making the same |
CN102825427B (zh) * | 2012-08-19 | 2015-04-22 | 什邡市明日宇航工业股份有限公司 | 飞行器舵组件扩散焊的制造方法 |
US9083160B2 (en) | 2012-09-24 | 2015-07-14 | Wisman Enterprises, Llc | Multi-function high voltage wire service handtool |
US9914533B2 (en) * | 2013-12-05 | 2018-03-13 | Sikorsky Aircraft Corporation | In-wing device retention |
US11453477B2 (en) * | 2019-02-28 | 2022-09-27 | Airbus Operations Gmbh | Wing leading edge device and a wing having such a wing leading edge device |
US20220388090A1 (en) * | 2021-06-04 | 2022-12-08 | The Boeing Company | Fabrication of thick stock via diffusion bonding of titanium alloys |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1380431A (en) * | 1920-03-22 | 1921-06-07 | William C Kidder | Propeller |
US1808842A (en) * | 1930-08-18 | 1931-06-09 | Fedor John Paul | Aeroplane wing |
US2097599A (en) * | 1934-12-31 | 1937-11-02 | Pavlecka John | Cellular structure |
US2248221A (en) * | 1937-03-20 | 1941-07-08 | Dornier Werke Gmbh | Propeller blade |
US2372510A (en) * | 1943-03-22 | 1945-03-27 | Robert W Mitchell | Structural unit for aircraft and the like |
US4530197A (en) * | 1983-06-29 | 1985-07-23 | Rockwell International Corporation | Thick core sandwich structures and method of fabrication thereof |
US4916027A (en) * | 1988-01-21 | 1990-04-10 | Rockwell International Corporation | Primary structure multi-layer insulation |
FR2647373B1 (fr) * | 1989-05-26 | 1993-12-17 | Dassault Breguet Aviation | Procede de formage par deformation par pression de fluide |
FR2672826B1 (fr) * | 1991-02-20 | 1995-04-21 | Snecma | Procede de fabrication d'une aube creuse pour turbomachine. |
US5243758A (en) * | 1991-12-09 | 1993-09-14 | General Electric Company | Design and processing method for manufacturing hollow airfoils (three-piece concept) |
US5330092A (en) * | 1991-12-17 | 1994-07-19 | The Boeing Company | Multiple density sandwich structures and method of fabrication |
US5544847A (en) * | 1993-11-10 | 1996-08-13 | The Boeing Company | Leading edge slat/wing combination |
-
1995
- 1995-10-12 FR FR9511975A patent/FR2739832B1/fr not_active Expired - Fee Related
-
1996
- 1996-10-11 ES ES96934900T patent/ES2171729T3/es not_active Expired - Lifetime
- 1996-10-11 DE DE69618760T patent/DE69618760T2/de not_active Expired - Fee Related
- 1996-10-11 WO PCT/FR1996/001594 patent/WO1997013683A1/fr active IP Right Grant
- 1996-10-11 US US08/849,694 patent/US5975465A/en not_active Expired - Fee Related
- 1996-10-11 EP EP96934900A patent/EP0800474B1/fr not_active Expired - Lifetime
- 1996-10-11 CA CA002208435A patent/CA2208435C/fr not_active Expired - Fee Related
- 1996-10-11 AU AU73043/96A patent/AU7304396A/en not_active Abandoned
- 1996-10-11 JP JP51478097A patent/JP3874423B2/ja not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
DE69618760T2 (de) | 2002-08-22 |
US5975465A (en) | 1999-11-02 |
FR2739832B1 (fr) | 1997-12-26 |
AU7304396A (en) | 1997-04-30 |
EP0800474B1 (fr) | 2002-01-23 |
JP3874423B2 (ja) | 2007-01-31 |
WO1997013683A1 (fr) | 1997-04-17 |
JPH10511623A (ja) | 1998-11-10 |
CA2208435A1 (fr) | 1997-04-17 |
CA2208435C (fr) | 2005-08-23 |
FR2739832A1 (fr) | 1997-04-18 |
EP0800474A1 (fr) | 1997-10-15 |
DE69618760D1 (de) | 2002-03-14 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
FG2A | Definitive protection |
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