GB2040790A - Moulding hollow articles - Google Patents

Moulding hollow articles Download PDF

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Publication number
GB2040790A
GB2040790A GB8001990A GB8001990A GB2040790A GB 2040790 A GB2040790 A GB 2040790A GB 8001990 A GB8001990 A GB 8001990A GB 8001990 A GB8001990 A GB 8001990A GB 2040790 A GB2040790 A GB 2040790A
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GB
United Kingdom
Prior art keywords
mandrel
sheets
article
plastics material
fibre
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.)
Granted
Application number
GB8001990A
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GB2040790B (en
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Westland Group PLC
Original Assignee
Westland Aircraft Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Westland Aircraft Ltd filed Critical Westland Aircraft Ltd
Priority to GB8001990A priority Critical patent/GB2040790B/en
Publication of GB2040790A publication Critical patent/GB2040790A/en
Application granted granted Critical
Publication of GB2040790B publication Critical patent/GB2040790B/en
Expired legal-status Critical Current

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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
    • 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
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • B29C70/446—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
    • 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
    • B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
    • B29C53/56—Winding and joining, e.g. winding spirally
    • B29C53/58—Winding and joining, e.g. winding spirally helically
    • B29C53/60—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels
    • B29C53/602—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels for tubular articles having closed or nearly closed ends, e.g. vessels, tanks, containers
    • 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
    • B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
    • B29C53/80—Component parts, details or accessories; Auxiliary operations
    • B29C53/82—Cores or mandrels
    • B29C53/821—Mandrels especially adapted for winding and joining
    • 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
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
    • B29L2031/082—Blades, e.g. for helicopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B64C2027/4733—Rotor blades substantially made from particular materials
    • B64C2027/4736—Rotor blades substantially made from particular materials from composite materials

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

In a method of producing hollow articles of fibre-reinforced plastics material, individual sheets 13 are wrapped around an inflatable mandrel 10 with edges overlapped longitudinally so as to permit unrestrained expansion of the mandrel when the assembly is located in a tool having an internal profile corresponding to a desired external profile of the articles. The individual sheets may be assembled as a flat pre-form before wrapping around the mandrel. Sheets and a pre-cured nose 15 may be assembled as in the Figure to manufacture a hollow spar of a helicopter rotor blade. After location in a female tool, the mandrel is inflated and the tool heated to cure the article. <IMAGE>

Description

SPECIFICATION Method of producing hollow articles of fibrereinforced plastics materials This invention relates to a method of producing hollow articles of fibre-reinforced plastics materials and to articles produced thereby, particularly but not exclusively to such articles for use as the load carrying spar of helicopter rotor blades.
One method of producing such articles is by winding composite tape of filament material either longitudinally or helically on an inflatable mandrel, the mandrel then being located in a female tool and inflated whilst the article is cured, usually by the application of heat and pressure.
Difficulties may be experienced with this method especially if the external profile of the article is important since the wrapping of the composite material on the mandrel tends to bind the mandrel tightly thereby preventing the necessary expansion of the wrapped material to ensure that the external shape of the article corresponds to the interior shape of the female tool. Furthermore, since the desired expansion of the wrapped material is prevented there may be a tendency for individual fibres to become buckled in the cured article and this can cause blemishes in the external profile and a reduction in the strength of the article.
Also, the winding operation requires the provision of complex and costly machinery.
Composite articles are finding ever increasing use in aircraft manufacture by reason of their high strength and good damage tolerance characteristics.
One area in which hollow composite articles have been proposed is as the main load carrying spar of helicopter rotor blades. Usually the external surface of the hollow spar forms a part of the aerodynamic profile of the blade chord, and it will therefore be apparent that the external surface of the spar has to be produced to extremely accurate tolerances and with a high quality surface finish. Also, of course, due to the requirements to match sets of rotor blades it is important in any production technique that the surface finish and dimensions of the spars as well as the weight distribution is consistently repeatable.
For the reasons previously mentioned, existing winding techniques may not satisfactorily fulfil these requirements.
Accordingly, in one aspect, the invention provides a method of producing a hollow article of fibrereinforced plastics material, comprising the steps of cutting a desired number of individual flat sheets of fibre-reinforced plastics material to predetermined width and length dimensions, locating the sheets longitudinally of an inflatable mandrel, wrapping the sheets circumferentially around the mandrel so that edges of each sheet overlap, locating the assembled mandrel in a female tool having an internal profile corresponding to the desired external profile of the article, inflating the mandrel, and curing the article by the application of heat.
Preferably, the position of the overlap in each sheet is staggered circumferentially of the mandrel.
The desired number of sheets may be assembled as a pre-form before location on the mandrel by laying the sheets one on top of the other with a desired stagger of the width dimension of each sheet. The pre-form may be partially cured prior to location on the mandrel.
A wall of the article may be made up to a required thickness by adding a suitabie number of further individual packing sheets of fibre-reinforced plastics material longitudinally of the mandrel on top of the overlapped sheets. Conveniently, in such an arrangement the method includes the further step of wrappping a desired number of longitudinally overlapping sheets on top of the packing sheets.
In another aspect the invention provides a method of producing a hollow article of fibre-reinforced plastics material using an inflatable mandrel, comprising the steps of cutting a desired number of individual flat sheets of fibre-reinforced plastics material to a desired length dimension and to a width dimension greater by a predetermined amount than the circumferential dimension of said inflatable mandrel, locating each sheet in turn longitudinally of the mandrel and wrapping the sheet circumferentially around the mandrel so that edges of individual sheets overlap, locating the assembled mandrel in a female tool having an internal profile corresponding to a desired external profile of the article, inflating the mandrel, curing the article and removing the article from the tool.
In yet another aspect the invention provides a method of producing a hollow article of fibrereinforced plastics material using an inflatable mandrel comprising the steps of cutting a desired number of individual flat sheets of pre-impregnated fibre-reinforced plastics material to a desired length dimension and to a width dimension greater by a predetermined amount than the circumferential dimension of said inflatable mandrel, assembling a pre-form of said sheets by laying the sheets one on top of the other with the width edges of adjacent sheets staggered, locating the pre-form longitudinally of the inflatable mandrel, wrapping the pre-form around the mandrel so that the edges along the width dimension of individual sheets overlap along the length of the sheet, locating the assembled mandrel in a female tool having an internal profile corresponding to a desired external profile of the article inflating the mandrel, curing the article and removing the article from the tool.
In yet another aspect the invention provides a method of producing a hollow spar for a helicopter rotor blade using an inflatable mandrel having a length corresponding approximately to a length of the finished rotor blade and a known circumferential dimension, comprising the steps of cutting a desired number of individual sheets of fibre-reinforced plastics material to a desired length and to a width dimension greater than the peripheral dimension of the mandrel by a predetermined amount, locating the sheets longitudinally of the mandrel, wrapping the sheets circumferentially around the mandrel so that edges of each sheet overlap, locating the assembly in a female tool having an internal profile corresponding to the desired external profile of the blade spar, inflating the mandrel curing the spar, and removing the spar from the tool.
The invention will now be described by way of example only and with reference to the accompanying drawings in which: Figure 1 is a cross-sectioned view of the mandrel for use in the production of a hollow spar for a helicopter rotor blade showing the first stage of manufacture according to one embodiment of the invention; Figures 2 and3 are views similar to Figure 1 showing subsequent stages of the manufacture; Figure 4 is a cross-sectioned view of the assembly of Figures 1 to 3 located in a female tool, and Figure 5 is an end view of a modified stage of manufacture according to a further embodiment.
In the accompanying drawings, the various individual sheets of fibre-reinforced plastics material are shown spaced-apart for clarity.
Referring now to Figure 1, an inflatable mandrel 10 for use in the production of an elongated hollow spar for a helicopter rotor blade comprises a shaped core 11 surrounded by a flexible airtight bag 12. Means (not shown) are provided for connecting a supply of pressurised air to the interior of the bag 12, and the mandrel 10 is of a length corresponding to the required length of the finished spar.
A sheet of pre-impregnated woven glass fibrereinforced plastics material 13 is cut to a required length and to a width dimension greater than the circumferential dimension of the mandrel 10 by about 1.0 inch. The sheet 13 is then laid longitudinally on the mandrel 10 and wrapped circumferentially around the mandrel 10 so that the edges overlap as shown atA in Figure 1, by an amount approximately corresponding to the excess of the width dimension, i.e. about 1.0 inch. Subsequently, additional sheets 13 (one only being shown in Figure 1) are laid on top of previous sheet 13 in a similar manner except that the position on the mandrel of the overlap A in each successive sheet is staggered circumferentially as shown in Figure 1. The lapped joints can be in any desired position around the mandrel 10; however it will be apparent that if the shape so permits, it will aid the laying-up procedure if the joints are located along a generally flat side of the mandrel.
In the illustrated embodiment relating to the manufacture of a hollow spar for a helicopter main rotor blade, a desired thickness of side and rear walls of the spar is obtained by adding individual packing sheets of pre-impregnated unidirectional fibrereinforced plastics material cut to a suitable width and length, in appropriate positions.
Thus, in Figure 2, it will be seen that packing sheets 14 (two only being illustrated) are laid on the sheets 13 along each side of the mandrel 10, one of the sheets 14from each side of the mandrel 10 being extended forwardly to meet at the front of a pre-cured nose moulding 15 of fibre-reinforced plastics material. The thickness of the rear wall is made up of packing sheets 16 (two only being illustrated) laid on the overlapping sheets 13.
The spar lay-up is completed as shown in Figure 3 buy a plurality of sheets 17 (two only being illustrated) of pre-impregnated woven material cut to a desired length, and to a width dimension sufficient to ensure that the edges overlap as shown at B in Figure 3. As with the inner sheets 13, the overlaps B in successive outer sheets 17 are staggered as shown in Figure 3.
The completed spar lay-up, indicated at 18 in Figure 4, is located in a female tool 19 having an internal profile 20 corresponding precisely to the desired finished profile of the hollow composite spar. The tool is closed and air pressure admitted to inflate the closed flexible bag 12. This causes the various layers of the spar to move outwardly, and it is an important feature of the invention that the method of laying-up the spar ensures that the circumferentially wrapped sheets 13 and 17 are free to expand outwardly by movement at the lapped joints A and B respectively, thereby ensuring that tha composite lay-up fills exactly the internal profile 20 of the tool 19, the pressure applied being such as is required to fully consolidate the composite lay-up 18.
The hollow spar is then cured by heating the tool, allowed to cool and removed from the tool. The mandrel 10 is then removed.
It will also be noted that the layers 14 and 16 used to provide a desired wall thickness in the illustrated embodiment are arranged so as to provide no circumferential restraint to movement of the sheets 13.
Thus, in the method according to the present invention, inflation of the mandrel is unrestricted since each of the individual sheets is free to move in an appropriate manner. This results in a hollow composite article having an external profile corresponding exactly to the internal shape of the tool, and which is readily repeatable. Furthermore, since all movement is outwards, the individual fibres in each sheet are stretched during inflation of the tool, thereby preventing buckling of the fibres and resulting in a strong article having a smooth external surface finish.
The number of sheets 13 used in a particular lay-up will of course depend on the requirements of the finished component, similarly the number of packing sheets 14 and 16 may be varied as required and may be dispensed with altogether in some applications. For example, the required wall thickness of a particular composite hollow spar for a tail rotor blade may be achieved entirely by a plurality of individual overlapped sheets laid-up on a mandrel according to this invention. The dimensions of lap portions A and B may also be varied; however, it should be noted that these dimensions should preferably be sufficient to ensure coninuity of load path in each sheet of the lay-up.
In a further embodiment, illustrated in Figure 5, the individual sheets 13 are first laid flat one on top of the other with a longitudinal stagger of the width edges so as to provide a pre-form. Additional desired sheets are arranged as illustrated in broken line at 13a in Figure 5. If desired the pre-form may be partially cured before location on the mandrel.
Similarly, the additional sheets 14 and 16 may be assembled as a pre-form and may also be partially cured prior to location on the mandrel.
When the edge 1 3D of the lowest sheet 13 of the pre-form (Figure 5) is laid on the mandrel 10 in a position corresponding to that shown in respect of the first sheet 13 in the embodiment of Figure 1, and the pre-form wrapped circumferentially around the mandrel 10, the edge 13e overlaps edge 13b in a manner similar to that illustrated in Figure 1. Furthermore, corresponding edges of subsequent sheets 13 will also overlap and the staggered arrangement of the pre-form ensures that the preferred circumferential staggering of the position of the overlaps of the previously described embodiment is obtained.
The finished length or an article manufactured according to this invention and the length of available sheets of composite material may determine whether single sheets extend throughout the whole of the finished length of whether it is made up of a plurality of discrete sheets. For example, in the manufacture of a spar for a tail rotor blade each of the sheets 13 may extend through the entire spar length, whereas in the manufacture of a spar for a main rotor blade, the spar length may be such as to require that it is achieved by a number of each of the sheets 13 and 17 located end-to-end. In the latter case, the longitudinal edges of adjacent sheets may be either overlapped or butt jointed.
In some cases, a hollow composite article laid-up according to this invention may comprise a part only of a further assembly, and the internal profile of the tool 19 may be arranged to caterforthis requirement. This applies particularly to the manufacture of composite rotor blades exemplified in the previous description in which the blade is normally comprised of the hollow spar and an aft trailing portion. Thus, in such an application, the tool 19 may be modified so as to have an internal profile corresponding to an external profile of the rotor blade, and the spar lay-up according to this invention may be located in the tool along with an aft trailing portion so as to cure the complete rotor blade in one operation.

Claims (16)

1. A method of producing a hollow article of fibre-reinforced plastics material, comprising the steps of cutting a desired number of individual flat sheets of fibre-reinforced plastics material to predetermined width and length dimensions, locating the sheets longitudinally of an inflatable mandrel, wrapping the sheets circumferentially around the mandrel so that edges of each sheet overlap, locating the assembled mandrel in a female tool having an internal profile corresponding to the desired external profile of the article, inflating the mandrel and curing the article by the application of heat.
2. A method as claimed in Claim 1 wherein a location of the overlap in each sheet is staggered circumferentially of said mandrel.
3. A method as claimed in Claim 1 of Claim 2 wherein said desired number of sheets are assembled as pre-form before location on the mandrel by laying the sheets one on top of the other with a stagger of the width dimension of each sheet.
4. A method as claimed in Claim 3, wherein said pre-form is partially cured before location on the mandrel.
5. A method as claimed in any preceding Claim, wherein a wail of the article is made up to a required thickness by adding a suitable number of individual packing sheets of fibre-reinforced plastics material longitudinally of the mandrel on top of the overlapped sheets.
6. A method as claimed in Claim 5, and including the further step of wrapping a desired number of longitudinally overlapping sheets on top of said packing sheets.
7. A method of producing a hollow article of fibre-reinforced plastics material using an inflatable mandrel, comprising the steps of cutting a desired number of individual flat sheets of fibre-reinforced plastics material to a desired length dimension and to a width dimension greater by a predetermined amount than the circumferential dimension of said inflatable mandrel, locating each sheet in turn, longitudinally of said mandrel and wrapping the sheet circumferentially around the mandrel so that edges of individual sheets overlap, locating the assembled mandrel in a female tool having an internal profile corresponding to a desired external profile of the article, inflating the mandrel, curing the article and removing the article from the tool.
8. A method of producing a hollow article of fibre-reinforced plastics material using an inflatable mandrel, comprising the steps of cutting a desired number of individual flat sheets of pre-impregnated fibre-reinforced plastics material to a desired length dimension and to a width dimension greater by a predetermined amount than the circumferential dimension of said inflatable mandrel, assembling a pre-form of said sheets by laying the shoots one on top of the other with the width edges of adjacent sheets staggered, locating the pre-form longitudinally of said inflatable mandrel, wrapping the pre-form around the mandrel so that the edges along the width dimension of individual sheets overlap along the length of the sheet, locating the assembled mandrel in a female tool having an internal profile corresponding to a desired external profile of the article, inflating the mandrel, curing the article and removing the article from the tool.
9. A method of producing a hollow article substantially as herein described and illustrated in the accompanying drawings.
10. A hollow article constructed of fibrereinforced plastics material in accordance with any one of the preceding claims.
11. A method of producing a hollow spar for a helicopter rotor blade using an inflatable mandrel having a length corresponding approximately to a length of the finished rotor blade and a known circumferential dimension, comprising the steps of cutting a desired number of individual sheets of fibre-reinforced plastics material to a desired length and to a width dimension greater than said. peripheral dimension of said mandrel by a predetermined amount, locating the sheets longitudinally of said mandrel, wrapping the sheets circumferentially around the mandrel so that edges of each sheet overlap, locating the assembly in a female tool having an internal profile corresponding to the desired external profile of the blade spar, inflating the mandrel, curing the spar and removing the spar from the tool.
12. A method as claimed in Claim 11, wherein a wall thickness of the spar is made up of a desired number of individual packing sheets of fibrereinforced plastics material laid longitudinally of the mandrel on top of the overlapped sheets.
13. A method as claimed in Claim 12, wherein at least one of the packing sheets from each side of the mandrel is extended forwardly so as to meet at the front of a pre-cured nose moulding located longitudinally of the mandrel.
14. A method as claimed in Claim 13 wherein said spar is completed by a further desired number of longitudinally overlapping sheets wrapped around said packing sheets.
15. In orfor.a helicopter rotor blade, a hollow spar constructed of fibre-reinforced plastics material in accordance with the method claimed in any one of Claims 11 to 14 inclusive.
16. Every novel feature and every novel combination of features disclosed herein.
GB8001990A 1979-02-05 1980-01-21 Moulding hollow articles Expired GB2040790B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB8001990A GB2040790B (en) 1979-02-05 1980-01-21 Moulding hollow articles

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB7903999 1979-02-05
GB8001990A GB2040790B (en) 1979-02-05 1980-01-21 Moulding hollow articles

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GB2040790A true GB2040790A (en) 1980-09-03
GB2040790B GB2040790B (en) 1982-10-13

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Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2119305A (en) * 1982-04-26 1983-11-16 M & G Trailers Ltd Moulding hollow articles
GB2129365A (en) * 1982-09-07 1984-05-16 Fischer Gmbh Hollow tubular members and a method of making such members
FR2554078A1 (en) * 1983-10-26 1985-05-03 Agusta Aeronaut Costr HELICOPTER BLADE LONGITUDINAL ELEMENT AND CORRESPONDING MANUFACTURING METHOD
GB2191440A (en) * 1986-06-09 1987-12-16 Composite Dev Ltd Fibre reinforced plastics structure
EP0363744A2 (en) * 1988-10-14 1990-04-18 The Budd Company One piece molded composite part and method of manufacture
FR2638672A1 (en) * 1988-11-10 1990-05-11 Bertin & Cie Rigid tubular bar made of composite material, and its method of manufacture
EP0373729A2 (en) * 1988-12-14 1990-06-20 Shell Internationale Researchmaatschappij B.V. Method for strengthening a panel
EP0409354A2 (en) * 1989-07-21 1991-01-23 Shell Internationale Researchmaatschappij B.V. Method and apparatus for forming a composite structure
GB2250466A (en) * 1990-12-05 1992-06-10 Taylor Made Golf Co Moulding a hollow golf club shaft from composite fibre/resin material
US5350556A (en) * 1992-01-10 1994-09-27 Yamaha Corporation Method for manufacturing fiber reinforced thermoplastic resin molded article
EP0628402A1 (en) * 1993-06-14 1994-12-14 AEROSPATIALE Société Nationale Industrielle Method for manufacturing hollow objects from composite material by contact winding on an expandable mandrel and objects obtained by such a method
WO1996006776A1 (en) * 1994-08-31 1996-03-07 United Technologies Corporation Fiber reinforced composite spar for a rotary wing aircraft and method of manufacture thereof
US5814268A (en) * 1990-12-05 1998-09-29 Taylor Made Golf Company, Inc. Process of making a golf club shaft
EP1134069A1 (en) * 1998-09-30 2001-09-19 Toray Industries, Inc. Hollow structure of fiber-reinforced resin and method of manufacturing the same
WO2009083531A1 (en) * 2007-12-28 2009-07-09 Vestas Wind Systems A/S A tubular element, the related method and tools to produce it
EP2692511A1 (en) * 2011-03-28 2014-02-05 Mitsubishi Heavy Industries, Ltd. Forming method for composite material structure
WO2014070379A1 (en) * 2012-10-31 2014-05-08 The Boeing Company Over-molded vacuum barrier and inner mold line bag carrier with soluble details in trapped closed mold tooling
US9145203B2 (en) 2012-10-31 2015-09-29 The Boeing Company Natural laminar flow wingtip
US9199419B2 (en) 2012-10-31 2015-12-01 The Boeing Company System and method for facilitating fluid movement in close-molded composite parts
US9498903B2 (en) 2012-10-31 2016-11-22 The Boeing Company System and method for manufacturing monolithic structures using expanding internal tools
EP3318394A1 (en) * 2016-11-04 2018-05-09 Ratier-Figeac SAS Composite structure
CN108032533A (en) * 2017-12-05 2018-05-15 中山大学 Multi-cavity carbon fiber pipe and its molding die, forming method
GB2571088A (en) * 2018-02-14 2019-08-21 Composite Tech And Applications Limited A tool and method for forming an annular component
US11440652B2 (en) * 2018-08-07 2022-09-13 Textron Innovations Inc. All-fabric spar for aerodynamic components

Cited By (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2119305A (en) * 1982-04-26 1983-11-16 M & G Trailers Ltd Moulding hollow articles
GB2129365A (en) * 1982-09-07 1984-05-16 Fischer Gmbh Hollow tubular members and a method of making such members
US4693140A (en) * 1982-09-07 1987-09-15 Fischer Gesellschaft M.B.H. Hollow tubular members and a method of making such members
FR2554078A1 (en) * 1983-10-26 1985-05-03 Agusta Aeronaut Costr HELICOPTER BLADE LONGITUDINAL ELEMENT AND CORRESPONDING MANUFACTURING METHOD
GB2191440A (en) * 1986-06-09 1987-12-16 Composite Dev Ltd Fibre reinforced plastics structure
EP0363744A2 (en) * 1988-10-14 1990-04-18 The Budd Company One piece molded composite part and method of manufacture
EP0363744A3 (en) * 1988-10-14 1991-07-10 The Budd Company One piece molded composite part and method of manufacture
FR2638672A1 (en) * 1988-11-10 1990-05-11 Bertin & Cie Rigid tubular bar made of composite material, and its method of manufacture
EP0373729A3 (en) * 1988-12-14 1992-09-02 Shell Internationale Researchmaatschappij B.V. Method for strengthening a panel
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