GB2225742A - Moulding a fibre reinforced composite, into a hollow structure comprising outer and inner skins connected by ribs - Google Patents
Moulding a fibre reinforced composite, into a hollow structure comprising outer and inner skins connected by ribs Download PDFInfo
- Publication number
- GB2225742A GB2225742A GB8828841A GB8828841A GB2225742A GB 2225742 A GB2225742 A GB 2225742A GB 8828841 A GB8828841 A GB 8828841A GB 8828841 A GB8828841 A GB 8828841A GB 2225742 A GB2225742 A GB 2225742A
- Authority
- GB
- United Kingdom
- Prior art keywords
- mould tool
- tool parts
- parts
- composite
- hollow
- 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.)
- Withdrawn
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D24/00—Producing articles with hollow walls
- B29D24/002—Producing articles with hollow walls formed with structures, e.g. cores placed between two plates or sheets, e.g. partially filled
-
- 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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/44—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
- B29C33/52—Moulds or cores; Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles soluble or fusible
-
- 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
- B29C70/34—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 and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—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 and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
-
- 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
- B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
- B29C43/02—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
- B29C43/10—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies
- B29C43/12—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies using bags surrounding the moulding material or using membranes contacting the moulding 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
- 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
Abstract
The structure (11) preferably comprises a hollow leading edge aerofoil, in which the ribs (15) define passages (17, 18) for fluid circulation in use. The composite is wrapped around hollow mould tool parts (25, 31) which are nested together between inner and outer composite skins (13, 12) within external mould tool parts (33, 34), and moulded under heat, and pressure which may partly be applied by internal pressurisation of the hollow mould tool parts, which may be of aluminium and may be removed from the cooled structure by etching. The composite is preferably fibre reinforced thermoplastic. The ends of the hollow mould tool parts (25, 31) may be rectangular, to provide aerofoil end regions for support and attachment of trailing edge skins, and attachment of fluid circulation supply means. <IMAGE>
Description
Description of Invention
Title: Method for Manufacturing a Hollow Structure
This invention relates to a method for manufacturing a hollow structure and is particularly concerned with a method for manufacturing a hollow leading edge aerofoil structure.
Both thermosetting and thermoplastic fibre-reinforced materials are now widely used in industry due to their ability to be readily formed into complex shapes by moulding. The very good strength to weight ratios of such composite materials has attracted the attention of the aircraft industry and composite materials are now widely used in the production of structural components and aerofoil structures both for fixed and rotary wing aircraft.
There is a requirement in the aircraft industry for a composite hollow aerofoil leading edge structure having chordwise extending ribs defining fluid tight channels through which a desired fluid can be passed during operation. Such a structure has heretofore proved extremely difficult to manufacture.
Accordingly, this invention provides a method for manufacturing a hollow structure of composite material and having inner and outer skins joined by rib portions comprising the steps of:
wrapping a desired thickness of composite material around a plurality of mould tool parts,
nesting the mould tool parts together between inner and outer composite skins so as to form the interconnecting webs,
locating the assembly in a mould tool,
curing the assembly and removing from the mould tool, and
removing the mould tool parts.
The mould tool parts may have complementarily changing cross sectional shapes throughout their length which may include central regions providing the appropriate configuration for forming the rib portions.
The sculd tool parts may comprise first and second mould tool parts nested end-to-end in at least two stacked rows and in overlapping relationship to each other.
The central regions may have a cross sectional shape having sloping converging side surfaces extending away from a planar surface extending throughout the length of the tool part. The planar surface of the first tool part may correspond to an external surface of the structure and that of the second tool part may correspond to an internal surface thereof.
The or each mould tool part may be curved throughout its length to provide a curved hollow structure.
Preferably the mould tool parts are hollow and are constructed of aluminium to permit removal from the cured assembly by etching.
In another aspect the invention provides a method for manufacturing a hollow aerofoil shaped leading edge structure comprising spaced-apart inner and outer skins joined by chordwise extending rib members forming individual chordwise extending channels, characterised by the steps of:
preforming a plurality of first outer mould tool parts and a plurality of second inner mould tool parts,
wrapping a desired thickness of composite material around each of the first and second tool parts,
locating a composite inner skin on an external part of a mould tool,
nesting the inner mould tool parts end-to-end on said inner skin,
nesting the outer mould tool parts end-to-end on the inner mould tool parts and in overlapping relationship with said inner parts, whereby complementarily shaped parts of said inner and outer mould tool parts combine to form said joining rib members,
locating the outer composite skin on said outer mould tool parts,
heating the assembly and closing the mould tool,
allowing the mould tool to cool to form the structure,
removing the structure from the mould tool, and
removing the mould tool parts from within the formed structure.
The invention will now be described by way of example only and with reference to the accompanying drawings in which,
Figure 1 is a fragmentary perspective view of a hollow aerofoil leading edge structure,
Figure 2 is a perspective illustration of a first mould tool part used in the construction of the structure of Figure 1 and in a method according to this invention,
Figure 3 is a perspective illustration of a second mould tool part used in the inventive method,
Figure 4 comprises three sectioned views taken on lines A-A, B-B, and C-C of Figure 2,
Figure 5 comprises three sectioned views taken on lines D-D, E-E and F-F of Figure 3,
Figure 6 is a schematic illustration taken in thé direction of arrow G of Figure 1 modified to show the location of the assembled first and second mould tool parts,
Figure 7 is a sectioned view taken on lines H-H of Figure 6, and
Figure 8 is a scrap sectioned view taken on lines J-J of Figure 7 illustrating features of the method of the invention.
Referring now to Figure 1, a hollow aerofoil section 11 suitable for use as the leading edge of a fixed or rotary wing is constructed of thermoplastic composite materials. Spaced-apart inner and outer skins 12 and 13 respectively are supported by chordwise extending ribs generally indicated at 14 comprising sloping wall portions 15 joined by flat land portions 16 bonded alternately to the inner and outer skins 12 and 13.
The sloping wall portions 15 define alternate chordwise extending channels 17 and 18 which during operation may be connected to a source of fluid. As shown in Figure 1 the walls 15 of channels 17 converge towards the outer skin 12 and the walls 15 of channel 18 converge towards the inner skin 13.
Figures 2 and 3 illustrate first and second mould tool parts 19 and 20 respectively each comprising a hollow thin walled preformed aluminium mould. In operation a plurality of first mould tool parts 19 are used to form channels 18 of Figure 1 and a plurality of second mould tool parts 20 are used to form the alternate channels 17.
Referring now to Figure 2, first mould part 19 comprises upper and lower end regions 21 and 22 of generally rectangular cross sectional shape joined via upper and lower transition regions 23 and 24 by a central region 25.
As show~ in Figure 4, the cross sectional shape of the first mould tool part 19 changes from the rectangular shape of end regions 21 and 22 gradually in the transition regions 23 and 24 where side walls 33 slope inwardly and the depth of the section is increased into the cross sectional shape of the central region 25 where the side walls 33 slope further inwardly so that the depth of the section is further increased to correspond to the internal shape of the channels 18 of Figure 1. It will be noted that a planar external surface 26 of mould tool part 19 remains constant throughout its length and that the side walls 33 converge as they extend from the surface.
Figure 3 and 5 provide details of the second mould tool part 20 which likewise has generally rectangular end regions 27 and 28 joined through transition regions 29 and 30 to a central region 31 having a cross sectional shape which corresponds to the internal shape of the channels 17 of Figure 1. In the second mould tool part 21, a planar internal surface 32 remains constant throughout its length and side walls 34 again converge as they extend from the surface.
As shown in Figures 6 and 7 and ignoring for the moment the necessary provision of the fibre-reinforced thermoplastic material from which the structure 11 is to be produced, a plurality of the first mould tool parts 19a, b, c, d, etc. are located end-to-end within the outer skin 12 and a plurality of the second mould tool parts 20a, b, c, d, etc. are located end-to-end internally of the first tool parts 20 and in an overlapping relationship. The internal skin 13 is located internally of the surface 32 of the second mould tool parts 21.
In the production of the structure of Figure 1 according to the method of this invention, the individual first and second mould tool parts 19 and 20 are wrapped throughout their length with a number of sheets of fibre-reinforced thermoplastic material until the required thickness is obtained. Sheets of fibre-reinforced thermoplastic material forming inner skin 13 are similarly laid on an external surface of a mould tool 33 and the wrapped tools 19 and 20 are nested together and over inner skin 13 as shown in Figure 6 and Figure 8. The outer skin 12 comprising a number of sheets of fibre-reinforced thermoplastic material is laid over the nested first and second tool parts 19 and 20.It will be understood that in the aforementioned lay-up procedure it may be necessary to apply heat locally to the individual sheets of fibre-reinforced thermoplastic material to assist in forming the sheets to the required profiles. The assembly is heated as the tool is closed by external tool part 34 to apply a consolidating pressure in conventional manner to form the structure 11, and pressure is also applied internally of the first and second mould tool parts 19 and 20 to assist consolidation.
The assembly is allowed to cool to set the thermoplastic material and removed from the tool parts 33 and 34.
The first and second mould tool parts 19 and 20 are then removed by etching.
It will be apparent in the described method that the assembly includes protruding end regions because of the wrapping of the thermoplastic material around the end regions 21, 22 and 27, 28 of the first and second mould tool parts 19 and 20. These protruding end regions are useful in providing for support and attachment of the trailing edge skins (not shown) of an aerofoil assembly and for facilitating attachment of the aforementioned supply of fluid that is desired to flow through some or all of the channels 17 and 18 of structure 11. In that respect it will be noted that adjoining walls of the protruding end regions can easily be removed as required to provide communication between any desired number of the channels 17 or the channels 18.
Whilst one embodiment has been described and illustrated it will be understood that many modifications may be made without departing from the scope of the invention. For example, the nesting cross sectional shapes of the central regions 25 and 31 of mould tool parts 19 and 20 respectively can be chosen to provide alternative cross sectional shapes for channels 17 and 18. The mould tool parts 19 and 20 can be of uniform cross sectional shape throughout their lengths and can be simply nested end-to-end in a single row rather than the end-to-end overlapping inner and outer rows of the described and illustrated embodiment. The invention can be used in the manufacture of hollow structures from thermosetting fibre-reinforced materials.
Claims (11)
1. A method for manufacturing a hollow structure of composite material having inner and outer skins joined by rib portions comprising the steps of:
wrapping a desired thickness of composite material around a plurality of mould tool parts,
nesting the mould tool parts together between inner and outer composite skins so as to form the interconnecting webs,
locating the assembly in a mould tool,
curing the assembly and removing from the mould tool, and
removing the mould tool parts.
2. A method according to Claim 1, wherein said mould tool parts have complementarily changing cross sectional shapes throughout their length including central regions providing the appropriate configuration for forming the rib portions.
3. A method as claimed in Claim 1 or Claim 2, wherein said mould tool parts comprise first and second mould tool parts nested side by side in at least two stacked rows and in overlapping relationship to each other.
4. A method as claimed in Claim 2 or Claim 3, wherein said central regions in cross section include sloping converging side surfaces extending away from a planar surface extending throughout the length of the mould tool part.
5. A method as claimed in Claim 4, wherein the planar surface of each first mould tool part corresponds to an external surface of the structure and the planar surface of the second mould tool part corresponds to an internal surface of the structure.
6. A method as claimed in any preceding Claim, wherein said mould tool parts are curved throughout their lengths to provide a hollow curved structure.
7. A method as claimed in any preceding claim, wherein said mould
tool parts are hollow aluminium mould tool parts, the method including
the step of applying pressure internally to plastically deform the
parts and assist consolidation of the structure.
8. A method as claimed in Claim 7, wherein said aluminium mould tool
parts are removed by etching.
9. A composite structure manufactured by the method according to any
one of Claims 1 to 8 inclusive.
10. A method for manufacturing a hollow aerofoil shaped leading edge
structure comprising inner and outer skins joined by chordwise
extending rib members forming individual chordwise extending channels
comprising the steps of:
preforming a plurality of hollow aluminium first outer mould tool
parts and second inner mould tool parts,
wrapping a desired thickness of composite material around each of
the first and second mould tool parts,
locating a composite inner skin on an external part of a mould
tool,
nesting the inner mould tool parts side by side on said inner skin,
nesting the outer mould tool parts side by side on said inner
mould tool parts and in overlapping relationship whereby
complementarily shaped parts of said inner and outer mould tool parts
combine to form said joining rib members,
locating the outer composite skin on said outer mould tool parts,
heating the assembly and closing the mould tool,
pressurising the interior of the mould tool parts to plastically
deform the parts to assist consolidation,
allowing the mould tool to cool,
removing the structure from the mould tool, and
etching the aluminium mould tool parts from within the formed
structure.
11. Every novel feature and every novel combination of features
disclosed herein.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8828841A GB2225742A (en) | 1988-12-09 | 1988-12-09 | Moulding a fibre reinforced composite, into a hollow structure comprising outer and inner skins connected by ribs |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8828841A GB2225742A (en) | 1988-12-09 | 1988-12-09 | Moulding a fibre reinforced composite, into a hollow structure comprising outer and inner skins connected by ribs |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB8828841D0 GB8828841D0 (en) | 1989-01-18 |
| GB2225742A true GB2225742A (en) | 1990-06-13 |
Family
ID=10648270
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB8828841A Withdrawn GB2225742A (en) | 1988-12-09 | 1988-12-09 | Moulding a fibre reinforced composite, into a hollow structure comprising outer and inner skins connected by ribs |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2225742A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2242389A (en) * | 1990-03-21 | 1991-10-02 | Short Brothers Plc | Cellular structural component |
| EP0773099A1 (en) * | 1993-09-27 | 1997-05-14 | Rockwell International Corporation | Composite structural truss element |
| FR2766407A1 (en) * | 1997-07-22 | 1999-01-29 | Aerospatiale | PROCESS FOR MANUFACTURING LARGE-DIMENSIONAL PARTS IN COMPOSITE MATERIAL WITH A THERMOPLASTIC MATRIX, SUCH AS FUSELAGE TRUNKS OF AIRCRAFT |
| EP0916464A2 (en) * | 1997-11-12 | 1999-05-19 | Sakura Rubber Co., Ltd. | Method of manufacturing structure by using biodegradable mold |
| WO2002020256A1 (en) * | 2000-09-08 | 2002-03-14 | Lockheed Martin Corporation | Unitized fastenerless composite structure |
| WO2003103933A1 (en) * | 2002-06-07 | 2003-12-18 | Short Brothers Plc | A fibre reinforced composite component and method to produce such component |
| US8979500B2 (en) | 2009-07-31 | 2015-03-17 | Rolls-Royce Plc | Method of manufacture of aerofoil leading edge strip |
| US9701391B2 (en) | 2010-11-29 | 2017-07-11 | Airbus Operations Limited | Aircraft structure comprising a skin panel |
| EP3219458A1 (en) * | 2016-03-14 | 2017-09-20 | Airbus Operations, S.L. | Method, injection moulding tool for manufacturing a leading edge section with hybrid laminar flow control for an aircraft, and leading edge section with hybrid laminar flow control obtained thereof |
| CN107521124A (en) * | 2017-07-31 | 2017-12-29 | 江苏恒神股份有限公司 | Carbon fiber dual platen reinforced structure part and its manufacture method |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB545090A (en) * | 1940-11-22 | 1942-05-11 | Boulton Aircraft Ltd | Improvements in and relating to the forming of tubular or like members from impregnated fibrous material |
| GB546686A (en) * | 1940-08-16 | 1942-07-27 | Ernest Platton King | Improvements in or relating to panel members for use in the construction of hollow bodies |
| GB577790A (en) * | 1938-08-29 | 1946-05-31 | Norman Adrian De Bruyne | Improvements relating to the manufacture of light non-metallic structural material or components |
| GB587282A (en) * | 1943-08-11 | 1947-04-21 | Ford Motor Co | Improvements in the moulding of hollow bodies from plastic |
| GB702992A (en) * | 1950-09-19 | 1954-01-27 | Horace Keeble | Improvements in or relating to a method of moulding hollow articles of self-setting materials |
| GB1166604A (en) * | 1965-10-06 | 1969-10-08 | Bolkow Gmbh | Improved Method of Manufacturing a Hollow Article of Plastics Material |
| GB1409736A (en) * | 1971-10-01 | 1975-10-15 | Boeing Co | Methods for fabricating laminated fluted structures |
-
1988
- 1988-12-09 GB GB8828841A patent/GB2225742A/en not_active Withdrawn
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB577790A (en) * | 1938-08-29 | 1946-05-31 | Norman Adrian De Bruyne | Improvements relating to the manufacture of light non-metallic structural material or components |
| GB546686A (en) * | 1940-08-16 | 1942-07-27 | Ernest Platton King | Improvements in or relating to panel members for use in the construction of hollow bodies |
| GB545090A (en) * | 1940-11-22 | 1942-05-11 | Boulton Aircraft Ltd | Improvements in and relating to the forming of tubular or like members from impregnated fibrous material |
| GB587282A (en) * | 1943-08-11 | 1947-04-21 | Ford Motor Co | Improvements in the moulding of hollow bodies from plastic |
| GB702992A (en) * | 1950-09-19 | 1954-01-27 | Horace Keeble | Improvements in or relating to a method of moulding hollow articles of self-setting materials |
| GB1166604A (en) * | 1965-10-06 | 1969-10-08 | Bolkow Gmbh | Improved Method of Manufacturing a Hollow Article of Plastics Material |
| GB1409736A (en) * | 1971-10-01 | 1975-10-15 | Boeing Co | Methods for fabricating laminated fluted structures |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2242389A (en) * | 1990-03-21 | 1991-10-02 | Short Brothers Plc | Cellular structural component |
| EP0773099A1 (en) * | 1993-09-27 | 1997-05-14 | Rockwell International Corporation | Composite structural truss element |
| FR2766407A1 (en) * | 1997-07-22 | 1999-01-29 | Aerospatiale | PROCESS FOR MANUFACTURING LARGE-DIMENSIONAL PARTS IN COMPOSITE MATERIAL WITH A THERMOPLASTIC MATRIX, SUCH AS FUSELAGE TRUNKS OF AIRCRAFT |
| WO1999004952A1 (en) * | 1997-07-22 | 1999-02-04 | Aerospatiale Societe Nationale Industrielle | Method for making parts in composite material with thermoplastic matrix |
| CN1077842C (en) * | 1997-07-22 | 2002-01-16 | 国家宇航工业公司 | Method for making parts in composite material with thermoplastic matrix |
| US6613258B1 (en) | 1997-07-22 | 2003-09-02 | Aerospatiale Societe Nationale Industrielle | Method for making parts in composite material with thermoplastic matrix |
| US6666941B2 (en) | 1997-11-12 | 2003-12-23 | Sakura Rubber Co. Ltd. | Method of manufacturing ribbed structure by using biodegradable mold |
| EP0916464A2 (en) * | 1997-11-12 | 1999-05-19 | Sakura Rubber Co., Ltd. | Method of manufacturing structure by using biodegradable mold |
| EP0916464A3 (en) * | 1997-11-12 | 2000-02-23 | Sakura Rubber Co., Ltd. | Method of manufacturing structure by using biodegradable mold |
| US6350337B1 (en) | 1997-11-12 | 2002-02-26 | Sakura Rubber Co., Ltd. | Method of manufacturing structure by using biodegradable mold |
| WO2002020256A1 (en) * | 2000-09-08 | 2002-03-14 | Lockheed Martin Corporation | Unitized fastenerless composite structure |
| WO2003103933A1 (en) * | 2002-06-07 | 2003-12-18 | Short Brothers Plc | A fibre reinforced composite component and method to produce such component |
| US8979500B2 (en) | 2009-07-31 | 2015-03-17 | Rolls-Royce Plc | Method of manufacture of aerofoil leading edge strip |
| US9701391B2 (en) | 2010-11-29 | 2017-07-11 | Airbus Operations Limited | Aircraft structure comprising a skin panel |
| EP3219458A1 (en) * | 2016-03-14 | 2017-09-20 | Airbus Operations, S.L. | Method, injection moulding tool for manufacturing a leading edge section with hybrid laminar flow control for an aircraft, and leading edge section with hybrid laminar flow control obtained thereof |
| US10377464B2 (en) | 2016-03-14 | 2019-08-13 | Airbus Operations, S.L. | Method, injection moulding tool for manufacturing a leading edge section with hybrid laminar flow control for an aircraft, and leading edge section with hybrid laminar flow control obtained thereof |
| CN107521124A (en) * | 2017-07-31 | 2017-12-29 | 江苏恒神股份有限公司 | Carbon fiber dual platen reinforced structure part and its manufacture method |
Also Published As
| Publication number | Publication date |
|---|---|
| GB8828841D0 (en) | 1989-01-18 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |