WO2011086220A2 - Disposición de unión de dos cajones de material compuesto con una pieza intermedia y procedimiento de fabricación de dicha pieza intermedia - Google Patents
Disposición de unión de dos cajones de material compuesto con una pieza intermedia y procedimiento de fabricación de dicha pieza intermedia Download PDFInfo
- Publication number
- WO2011086220A2 WO2011086220A2 PCT/ES2011/070018 ES2011070018W WO2011086220A2 WO 2011086220 A2 WO2011086220 A2 WO 2011086220A2 ES 2011070018 W ES2011070018 W ES 2011070018W WO 2011086220 A2 WO2011086220 A2 WO 2011086220A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- drawers
- double
- piece
- manufacturing
- preforms
- Prior art date
Links
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 23
- 239000002131 composite material Substances 0.000 title claims abstract description 12
- 238000005304 joining Methods 0.000 title abstract description 11
- 238000000034 method Methods 0.000 claims abstract description 11
- 239000003381 stabilizer Substances 0.000 claims description 13
- 230000002787 reinforcement Effects 0.000 claims description 5
- 238000000576 coating method Methods 0.000 claims description 4
- 239000003292 glue Substances 0.000 claims 1
- 238000007493 shaping process Methods 0.000 abstract 1
- 230000010354 integration Effects 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000005253 cladding Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- LNEPOXFFQSENCJ-UHFFFAOYSA-N haloperidol Chemical compound C1CC(O)(C=2C=CC(Cl)=CC=2)CCN1CCCC(=O)C1=CC=C(F)C=C1 LNEPOXFFQSENCJ-UHFFFAOYSA-N 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000001721 transfer moulding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
- B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
- B29C65/5064—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like of particular form, e.g. being C-shaped, T-shaped
- B29C65/5078—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like of particular form, e.g. being C-shaped, T-shaped and being composed by several elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
- B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
- B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
- B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
- B29C66/54—Joining several hollow-preforms, e.g. half-shells, to form hollow articles, e.g. for making balls, containers; Joining several hollow-preforms, e.g. half-cylinders, to form tubular articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
- B29C66/721—Fibre-reinforced materials
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
- B29C66/725—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being hollow-walled or honeycombs
- B29C66/7252—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being hollow-walled or honeycombs hollow-walled
- B29C66/72523—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined being hollow-walled or honeycombs hollow-walled multi-channelled or multi-tubular
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/302—Details of the edges of fibre composites, e.g. edge finishing or means to avoid delamination
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/05—Particular design of joint configurations
- B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
- B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
- B29C66/112—Single lapped joints
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/05—Particular design of joint configurations
- B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
- B29C66/13—Single flanged joints; Fin-type joints; Single hem joints; Edge joints; Interpenetrating fingered joints; Other specific particular designs of joint cross-sections not provided for in groups B29C66/11 - B29C66/12
- B29C66/131—Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
- B29C66/721—Fibre-reinforced materials
- B29C66/7212—Fibre-reinforced materials characterised by the composition of the fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
- B29C66/721—Fibre-reinforced materials
- B29C66/7214—Fibre-reinforced materials characterised by the length of the fibres
- B29C66/72141—Fibres of continuous length
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
- B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
-
- 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
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/4998—Combined manufacture including applying or shaping of fluent material
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/53—Means to assemble or disassemble
Definitions
- the present invention relates to an arrangement for joining two drawers of composite material with an intermediate piece and to the method of manufacturing said intermediate piece and in particular to an arrangement for joining the lateral drawers of a horizontal stabilizer of an aircraft with a intermediate piece in the shape of double T.
- composite materials of organic matrix and continuous fibers mainly based on epoxy resins and carbon fibers are used in a wide variety of structural elements.
- Aeronautical structures require, as is well known, the integration of various structural elements.
- the fuselages require the integration of the cladding with various structural elements such as beams, frames or stringers.
- various structural elements such as beams, frames or stringers.
- the composite materials allow that integration can also be carried out by chemical joints.
- these and other objects are achieved by means of a manufacturing process of a double T-shaped piece with a core and upper and lower wings used as an intermediate connecting piece of two drawer-shaped structural components, comprising coverings upper and lower, said union being made between the coatings upper and lower parts of said components and the upper and lower wings of said part, said part as well as said drawers being made of composite material, comprising the following steps:
- said flat preforms are arranged in a central area of the wings of the intermediate piece in the form of double T without extending over its entire width with two or more segments staggered towards its longitudinal axis. This achieves an efficient process for the manufacture of an intermediate piece in the form of a double T that facilitates the gradual transfer of loads between the drawers.
- said flat preforms comprise local reinforcement zones at one of their ends. In this way, an efficient process for manufacturing a double T-shaped intermediate part is configured in an appropriate manner for the reception of local loads such as loads derived from trim mechanisms of the horizontal tail stabilizer.
- the intermediate joining pieces are applied to drawers with or without dihedral and to multi-rib or multi-stringer drawers. This achieves an effective procedure applicable to the manufacture of an intermediate piece in the form of a double T configured in an appropriate manner for the basic types of lateral drawers of horizontal aircraft tail stabilizers.
- the aforementioned objects are achieved by providing a joining arrangement of two drawer-shaped structural components comprising an upper liner, a lower liner, using an intermediate double T-shaped connecting piece and the connection being made between the coatings of said components and the upper and lower wings of said piece by rivets, said piece as well as said components being made of composite material, in which said piece is manufactured according to the aforementioned procedure.
- At least two rows of rivets are used in each zone of different thickness of the upper and lower wings of the piece. This results in a very efficient connection arrangement for the transfer of loads between the drawers.
- FIGURES Figure 1 shows a connection arrangement of two lateral drawers of a horizontal tail stabilizer of an aircraft with a T-shaped intermediate piece known in the art.
- Figure 2 shows a T-shaped intermediate part according to the present invention and Figure 3 the preforms used in the manufacturing process of that intermediate part according to the present invention.
- Figure 4 shows a cross-sectional view of a joining arrangement of two lateral drawers with dihedral of a horizontal tail stabilizer of an aircraft with a T-shaped intermediate piece according to the present invention.
- Figure 5 shows a cross-sectional view of a junction arrangement of two lateral drawers without dihedral of a horizontal tail stabilizer of an aircraft with a T-shaped intermediate piece according to the present invention.
- This joint arrangement requires a flattening of the end areas of the linings 15, 17; 15 ', 17' so that they sit on the flat wings 25, 27 of the piece.
- the joint arrangement of two lateral drawers 1 1, 1 1 'of a tail stabilizer of an aircraft with an intermediate piece 31 in the form of a double T, with a core 33 and two wings 35, 37 as shown in Figure 2 is based on the manufacture of the piece by an RTM ("Resin Transfer Molding") procedure, that is to say a closed molding process, with resin injection using the preforms shown in Figure 3: two preforms 41, 41 'C-shaped, with souls 43, 43' and wings 55, 57; 55 ', 57' and two flat preforms 45, 47 (as the person skilled in the art will well understand the term "flat” should not be strictly understood in its geometric sense).
- RTM Resin Transfer Molding
- the intermediate piece 31 manufactured according to said procedure has wings 35, 37 resulting from the union of wings 55, 55 '; 57, 57 'of the C preforms with the flat preforms 45, 47 which are specifically configured, on the one hand, to adapt to the particular configuration of the ends of the drawers 1 1, 1 1 'and, on the other hand, to facilitate a gradual transfer of the load in the joint.
- the aforementioned adaptability of the piece 31 to the configuration of the ends of the drawers 1 1, 1 1 allows the present invention to be applicable to drawers with or without dihedral as well as to multi-rib or multi-stringer drawers.
- preforms 45, 47 can be configured with segments of different thicknesses both longitudinally and transversely.
- the upper preform 45 comprises a base segment 61 on which the segment 63 that extends longitudinally over the entire upper wing but has a smaller width than the segment 61 is placed, on which, in turn, segments 65 and 67 are located at one of its ends.
- This configuration facilitates, on the one hand, the gradual transfer of loads between drawers 1 1, 1 1 'thanks to the staggering of segments 61, 63 and, on the other, a local reinforcement is provided with segments 65, 67 which It may be necessary.
- the upper preform 45 comprises a base segment 61 that does not extend over the entire upper wing of the piece 31 - which means that the first rows of rivets are applied to the joint of the linings 15, 15 'and the zones from 55, 55 'of the preforms in C- and over it, segments 63, 65 and 67 of decreasing width extend stepwise. With this step configuration, the gradual transfer of loads between the drawers 1 1, 1 1 'through the piece 31 is facilitated.
- a preferred embodiment with two rows of rivets 81 in each zone of different thickness is shown in Figure 4.
- the present invention has the following advantages:
- the inner faces 55, 55 '; 57, 57 'of the intermediate piece 31 in contact with the linings 15, 15', 17, 17 'of the side drawers have, using an appropriate tool, an optimal finish, which facilitates compliance with the requirements of manufacturing and assembly tolerances, which is carried out by moving the intermediate piece 31, once the side drawers 1 1, 1 1 'are positioned in place, without any subsequent movement of the drawers 1 1, 1 one '.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Connection Of Plates (AREA)
- Lining Or Joining Of Plastics Or The Like (AREA)
- Body Structure For Vehicles (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN2011800115298A CN102781651A (zh) | 2010-01-14 | 2011-01-14 | 利用中间部件的用于两个复合材料箱的连接布置及用于制造该中间部件的方法 |
CA2787313A CA2787313A1 (en) | 2010-01-14 | 2011-01-14 | Joining arrangement for two boxes of composite material with an intermediate part and method for manufacturing said intermediate part |
EP11711107A EP2524795A2 (en) | 2010-01-14 | 2011-01-14 | Joining arrangement for two boxes of composite material with an intermediate part and method for producing said intermediate part |
RU2012134644/05A RU2012134644A (ru) | 2010-01-14 | 2011-01-14 | Соединительное устройство для двух корпусов из композитного материала с промежуточной деталью и способ изготовления упомянутой промежуточной детали |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ES201030026A ES2391102B1 (es) | 2010-01-14 | 2010-01-14 | Disposicion de union de dos cajones de material compuesto con una pieza intermedia y procedimiento de fabricacion de dicha pieza intermedia |
ESP201030026 | 2010-01-14 |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2011086220A2 true WO2011086220A2 (es) | 2011-07-21 |
WO2011086220A3 WO2011086220A3 (es) | 2011-10-06 |
Family
ID=44148886
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/ES2011/070018 WO2011086220A2 (es) | 2010-01-14 | 2011-01-14 | Disposición de unión de dos cajones de material compuesto con una pieza intermedia y procedimiento de fabricación de dicha pieza intermedia |
Country Status (7)
Country | Link |
---|---|
US (1) | US20110167614A1 (es) |
EP (1) | EP2524795A2 (es) |
CN (1) | CN102781651A (es) |
CA (1) | CA2787313A1 (es) |
ES (1) | ES2391102B1 (es) |
RU (1) | RU2012134644A (es) |
WO (1) | WO2011086220A2 (es) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ES2372849B1 (es) * | 2010-03-25 | 2012-12-13 | Airbus Operations, S.L. | Estructura de unión de cajones de torsión en una aeronave mediante un herraje triforme de materiales compuestos no metálicos. |
EP4089009A1 (en) * | 2021-05-14 | 2022-11-16 | Airbus Operations, S.L.U. | A method for assembling an aircraft lifting surface |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20090159742A1 (en) | 2007-12-21 | 2009-06-25 | Gonzalo Ramirez Blanco | Lifting structure for aircraft |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6217000B1 (en) * | 1996-10-25 | 2001-04-17 | The Boeing Company | Composite fabrication method and tooling to improve part consolidation |
US6889937B2 (en) * | 1999-11-18 | 2005-05-10 | Rocky Mountain Composites, Inc. | Single piece co-cure composite wing |
US6520706B1 (en) * | 2000-08-25 | 2003-02-18 | Lockheed Martin Corporation | Composite material support structures with sinusoidal webs and method of fabricating same |
US7138028B2 (en) * | 2001-07-26 | 2006-11-21 | The Boeing Company | Vacuum assisted resin transfer method for co-bonding composite laminate structures |
US6585298B2 (en) * | 2001-11-13 | 2003-07-01 | Flowtite Technology As | High-strength butt-wrap joint for reinforced plastic pipes |
US6945727B2 (en) * | 2002-07-19 | 2005-09-20 | The Boeing Company | Apparatuses and methods for joining structural members, such as composite structural members |
US20080072527A1 (en) * | 2006-08-01 | 2008-03-27 | Honda Motor Co., Ltd. | Fiber-reinforced composite member and method for producing structure using same |
ES2352941B1 (es) * | 2008-05-16 | 2012-01-25 | Airbus Operations, S.L. | Estructura integrada de aeronave en material compuesto |
-
2010
- 2010-01-14 ES ES201030026A patent/ES2391102B1/es not_active Expired - Fee Related
- 2010-07-07 US US12/831,614 patent/US20110167614A1/en not_active Abandoned
-
2011
- 2011-01-14 WO PCT/ES2011/070018 patent/WO2011086220A2/es active Application Filing
- 2011-01-14 CA CA2787313A patent/CA2787313A1/en not_active Abandoned
- 2011-01-14 CN CN2011800115298A patent/CN102781651A/zh active Pending
- 2011-01-14 RU RU2012134644/05A patent/RU2012134644A/ru not_active Application Discontinuation
- 2011-01-14 EP EP11711107A patent/EP2524795A2/en not_active Withdrawn
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20090159742A1 (en) | 2007-12-21 | 2009-06-25 | Gonzalo Ramirez Blanco | Lifting structure for aircraft |
Also Published As
Publication number | Publication date |
---|---|
CN102781651A (zh) | 2012-11-14 |
ES2391102B1 (es) | 2013-10-09 |
ES2391102A1 (es) | 2012-11-21 |
US20110167614A1 (en) | 2011-07-14 |
WO2011086220A3 (es) | 2011-10-06 |
EP2524795A2 (en) | 2012-11-21 |
CA2787313A1 (en) | 2011-07-21 |
RU2012134644A (ru) | 2014-02-20 |
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