EP2618992A1 - Procédé de formation de bords nets - Google Patents

Procédé de formation de bords nets

Info

Publication number
EP2618992A1
EP2618992A1 EP11764258.7A EP11764258A EP2618992A1 EP 2618992 A1 EP2618992 A1 EP 2618992A1 EP 11764258 A EP11764258 A EP 11764258A EP 2618992 A1 EP2618992 A1 EP 2618992A1
Authority
EP
European Patent Office
Prior art keywords
stack
component
cured
portions
sub
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Withdrawn
Application number
EP11764258.7A
Other languages
German (de)
English (en)
Inventor
Andrew Chiverton
Bob ALLANSON
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.)
GKN Aerospace Services Ltd
Original Assignee
GKN Aerospace Services 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 GKN Aerospace Services Ltd filed Critical GKN Aerospace Services Ltd
Publication of EP2618992A1 publication Critical patent/EP2618992A1/fr
Withdrawn legal-status Critical Current

Links

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
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/545—Perforating, cutting or machining during or after moulding

Definitions

  • the present invention relates to an improved method of manufacturing composite components. Specifically the invention provides a method which improves manufacturing efficiencies and reduces the finishing process steps required for a given composite component.
  • Characteristics of composite materials have meant that composite components are employed in an increasing range of applications from aerospace to automotive parts.
  • composite materials have been used for a number of years owing to their strength to weight ratio.
  • the term composite materials are used to describe materials comprising for example glass fibre or carbon fibres and an epoxy resin (or similar). These are also known as glass reinforced plastic or carbon fibre reinforced composites.
  • the carbon fibre reinforced composite material offers improved properties such as lower weight, improved fatigue/damage resistance, corrosion resistance and negligible thermal expansion.
  • Aerodynamic as well as structural components are formed of composite materials and particularly carbon fibre materials.
  • Composite components have to be layed-up using a cloth or the like pre-impregnated with resin into a stack corresponding to the desired shape of the part to be formed. The stack is then cured either at ambient temperature and pressure or at elevated temperature and pressure in an autoclave to create a hardened component. Industry standard machinery is required to cut the pre-impregnated cloth so as to correspond to the desired shape. Once the part has been cured the component is then frequently machined in a finishing process to the desired final dimensions and tolerances. This requires additional manufacturing equipment and consequently increases the lead time of manufacture and also the overall manufacturing costs.
  • the present invention aims to provide a method of manufacturing a composite component which negates or minimises the need for edge finishing steps in the manufacture of composite components.
  • a method of forming a composite component comprising the steps of machining a stack of pre-impregnated composite material to form a first portion defining the component and a second portion surrounding at least a part of said first portion; wherein the machining step separates said first portion from said second portion; and maintaining the relative position of said first to said second portion of said stack whilst said stack is cured.
  • the machining step separates the desired component from the surrounding material of the stack.
  • This surrounding material is termed 'trim allowance' and is a sacrificial part of the stack.
  • the second portion may extend around all of the first portion or only a portion thereof.
  • the machining creates a small gap or separation between the first and second portion which is maintained until the cure step of the manufacturing process. As the stack is cured resin from the pre-impregnated cloth flows into the gap separating the first and second portions.
  • a discontinuity is created in the resulting cured component.
  • the component comprises a first and second portion of cured resin and fibre and a fracture or break line formed of cured resin void of any cloth or carbon fibres separating the two.
  • the method defines a frangible divide between the portion of the stack defining the desired component and the portion of the stack defining the trim allowance.
  • the stack once machined, is positioned in the curing apparatus in the same configuration as on or in the machining apparatus i.e. the relative position of the first portion to the second portion is maintained.
  • the inventors have established that completely separating the first and second components (that is cutting through the cloth or the like fibres) using the machining step (and before the cure step) and only then curing the component provides significant advantages for manufacture.
  • the fracture line can conveniently be broken by the application of a force along the machined line.
  • the cured resin is conveniently brittle resulting in a surprisingly clean fracture through the resin and along the fracture line.
  • the desired component can be separated from the trim allowance portion of the stack and exhibits clean and straight edges requiring minimal if any further edge finishing.
  • the carbon material may advantageously be a Bismaleimide (BMI) resin which can be conveniently utilised in high temperature environments. This particular resin requires a second (post) cure to harden it. This resin system is advantageously harder and more brittle and this therefore facilitates the breaking of the resin post (second) cure.
  • BMI Bismaleimide
  • the method of the present invention not only provides a clean fracture between the two portions but additionally maintains substantially uniform cross- section dimensions of the component right up to component's edge.
  • the method may be applied to a variety of composite materials.
  • the composite may be an epoxy or Bismaleimide (BMI) resin system with a woven glass, carbon or Kevlar composite cloth.
  • BMI Bismaleimide
  • the present prevents delamination of the layers forming the stack when trim allowance is removed. Conventional finishing techniques are prone to cause delamination of the layers reducing the structural integrity of the component and the edge finish thereof.
  • the inventors have recognised that machining the component from a stack in a conventional manner and then subsequently curing the component causes flow of the resin around the periphery of the part.
  • the resulting part does not therefore have sharp and clean edges but rather is formed with curve or sloping edges caused by resin flow at the component edge.
  • edge finish obtained using the present invention negates the need for complex and expensive post-cure machining.
  • components are finished or cut from a cured stack using a multi axis drilling and rout machine.
  • Machinery of this type is expensive to purchase adding to the unit cost of component manufacture and also adds an additional time component to the overall unit production time.
  • a composite component can be made of a predetermined shape with a line in of weakness in its structure corresponding to the shape of the part to be made. Applying a breaking force to this line conveniently fractures the resin providing a surprisingly clean edge finish requiring no or minimal edge finishing.
  • the separating or fracture load may be applied at any time after the part has been cured. Maintaining the trim allowance portion of the stack allows for convenient storage and transportation of the component before the desired component is separated from the trim allowance. This advantageously ensures the part is not damage.
  • the second portion of the stack may itself be sub-divided into multiple parts wherein each part has its own separation or fracture line. This advantageously allows the trim allowance to be broke away from the desired part in a number of steps. This is particularly advantageous when the desired part has a complex profile since multiple sub-components can be broken away from the desired part leaving the part undamaged.
  • the sub-portions may be separated by a fracture line which does not separate the two sub-parts in their entirety.
  • the separation lines separating adjacent sub- portions of the second portion of the stack (the trim allowance portion) may be provided with a small portion where the cloth fibres are retained i.e.
  • the two adjacent parts are machined to be separated with the exception of a small portion or tab having a cross-section substantially smaller than the cross-section of the respective separation line.
  • the sub-parts of the trim allowance can be conveniently secured together additionally protecting the component and allowing the trim allowance to be removed as one piece.
  • the invention can be conveniently used with both autoclave resin materials and also out of autoclave materials. The latter materials cure at ambient or near ambient conditions.
  • the machining step according to the present invention can be achieved using any suitable manufacturing process. It should be recognised that the term 'machining' is not limited to a particular process or 'machine'.
  • the machining step may be achieved using an ultrasonic cutting apparatus or a drag cutting apparatus.
  • the machining step may also be performed by ablation, for example laser ablation.
  • a method of forming a composite component comprising a hole extending therethrough, said method comprising the steps of machining a stack of pre-impregnated composite material to form a first portion defining the component and a second portion defining a hole to be formed in said component wherein the first portion is separated from said second portion; and maintaining the relative positions of said first and second portions of said stack whilst said stack is cured.
  • a method of forming a component comprising a hole.
  • the trim allowance is therefore arranged to be surrounded by the desired component and the frangible separating line defines the perimeter of the hole to be formed in the part.
  • the stack may of course be formed with both a trim allowance surround at least a portion of the component and a trim allowance defining a hole to be formed.
  • the stack may be provided with two frangible lines created by separating the component from the inner and outer trim allowance portions before curing.
  • a method of manufacturing a component comprising the steps of laying-up a stack of pre-impregnated plies to form a composite stack, forming a separation line within said stack corresponding to a desired component shape and curing said stack to form a frangible line extending along said line and around the periphery of said component.
  • aspects of the invention extend to aerospace and aerodynamic component manufactured according to the method and so cosmetic or facia panels manufactured according to the method.
  • Figure 1 shows a laminate stack in a pre-cure condition
  • Figure 2 shows a stack and cutting machine and the resultant component shape
  • Figures 3A and 3B show a separation line between the two stack parts and the resulting post-cure frangible line
  • Figure 4 shows a method of separating the trim allowance from the component
  • Figure 5 A shows a component with a sub-divided trim allowance
  • Figure 5B shows a retaining tab connecting adjacent trim allowance portions
  • Figure 6 shows a component comprising a hole
  • Figure 7 shows a method of formed a component with a hole formed therein.
  • Figure 1 shows a series of pre-impregnated layers 1 forming a stack 2.
  • the dimensions of the stack are selected so as to provide sufficient material to surround the desired component, discussed below.
  • the material forming the stack may be any suitable pre-impregnated cloth material.
  • this process can be applied to any pre-impregnated material with either a fibre of carbon, glass or Kevlar impregnated with an epoxy resin or BMI resin system.
  • the stack may be formed of any suitable number of layers, each layer being optionally layed at a particular angle relative to the adjacent layer(s) dependent on the application. Additionally an optional peel ply layer may be applied to one or both outer planar surfaces. This may advantageously provide a matt finish to allow for painting of the part for example.
  • Figure 2 shows the stack 2 and a suitable cutting machine 3. This may for example be an ultrasonic cloth cutting machine.
  • the cutting head is controlled to cut a path 5 through and along the composite stack 2.
  • the path in effect divides the stack 2 into a first portion 6 corresponding to the desired component and a second portion 7 which is a sacrificial portion of the stack called a trim allowance portion.
  • the trim allowance portion has been divided into two portions by a further cut 8 extending to the periphery of the stack.
  • the cure apparatus This might for example be an Autoclave, Oven, via heated tooling or heater blankets. In each case a vacuum would be applied to withdraw volatiles as is known in the art. In the case of an Autoclave an external pressure may also additionally be applied to improve consolidation of the component.
  • the positions of the first and second portions of the stack are maintained within the curing apparatus i.e. the first portion defining the part remains surrounded by the second portion defining the trim allowance of second portion of the stack.
  • the curing process is well know to the person skilled in the art (both autoclave and out of autoclave) and will not therefore be explained here.
  • Figures 3A and 3B illustrate the separation line formed by the cutting process before and after the curing process.
  • Figure 3A shows the separation formed by the cutting (alternatively termed machining) step of the method.
  • the machining step involves cutting through the entirety of the stack 2 i.e. to cut through all of the cloth material that constitutes the layers.
  • Figure 3B shows the same cross-section after the cure step where the resin has been consolidated during the cure to flow and harden.
  • the separation step creates a cavity 9 into which the resin can flow during the cure step. As the resin flows the cavity is filled up with resin which then hardens to form a frangible portion 10 or line extended around the path formed by the cutting step.
  • Figure 4 illustrates one method of separating the component 6 from the trim allowance 7. As shown the stack 2 has been cured and now comprises the frangible line 10 extending around the component and to the exterior of the stack.
  • the strength of the frangible line 10 depends on the resin used during the cure but will consistently be weaker than the component and trim allowance portions which each comprise consolidate resin and fibres (either carbon or glass).
  • To separate the component force 1 1 is applied to the trim allowance portion 7 whilst the part is restrained. The force causes the frangible line to snap releasing the trim allowance from the component. It will be recognised that the component could be removed from the trim allowance in a variety of ways using manual or automated techniques. Breaking the brittle resin in this way results in a surprisingly clean separation of the two parts requiring no or minimal surface finishing such as deburring. This advantageously minimises non-recurring costs for component manufacture and negates the need for edge finishing processes that might cause component damage.
  • FIG 5A shows another example of a component 6 and trim allowance 7.
  • the trim allowance has been sub-divided into 4 portions 7 A to 7D.
  • the machining step has retained a small tab 13 connected adjacent trim allowance portions.
  • the frangible path 10 created during the cure step has interruptions 13 where a small portion of fibre is permitted to connect the adjacent trim allowance portions.
  • the tab 13 need only be small compared with the overall cross-section of the frangible line having a suitable cross- section sufficient to connect the two adjacent portions of trim allowance together without fracture.
  • the tab 13 is small compared to the overall size of the cavity 9 prior to curing.
  • Figure 6 shows a more complex shape manufactured according to the present invention.
  • the component 6 comprises an integral hole 14 within its boundary.
  • the component is itself machined to create a frangible line 15 within its boundary.
  • the outer frangible line 9 defines the outer periphery of the part and in the inner frangible line 15 defines the inner boundary i.e. the hole.
  • the component can be separated from the trim allowance by breaking the frangible line 9 around the perimeter.
  • the frangible line 15 can be broken by punching the portion 16 out to create the hole 14.
  • the portion 16 may itself be provided with a central hole and further comprise frangible lines extending from the line 15 to the inner hole so that the edges can be broken off as described above. This is illustrated in Figure 7.
  • the inner hole portion 16 is surrounded by a first frangible line 15 which can be broken to release the central portion 16.
  • the central portion (shown as a hatched area) is itself provided with a sub hole 17 formed by the machining step. The edges of this portion serve no purpose for the component i.e. this portion is also sacrificial.
  • frangible lines 18A to 18D are provided extending to the corners of the portion 16. Once the stack has been cured these lines 18A to 18D can themselves be fractured together with the frangible line 15 to create a net finished inner hole exhibiting the same improved edge surface characteristics of the outer surface as described above.

Landscapes

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

Abstract

La présente invention porte sur un procédé qui améliore les rendements de fabrication et réduit les étapes des processus de finition nécessaires pour un élément composite donné. Un trajet de rupture (5) est créé dans un empilement durci d'une matière composite (2) qui peut être convenablement rompu pour obtenir un élément ayant un meilleur fini de la surface des bords.
EP11764258.7A 2010-09-22 2011-09-21 Procédé de formation de bords nets Withdrawn EP2618992A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1015951.5A GB2485758B (en) 2010-09-22 2010-09-22 Net edge method
PCT/GB2011/051784 WO2012038747A1 (fr) 2010-09-22 2011-09-21 Procédé de formation de bords nets

Publications (1)

Publication Number Publication Date
EP2618992A1 true EP2618992A1 (fr) 2013-07-31

Family

ID=43086753

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11764258.7A Withdrawn EP2618992A1 (fr) 2010-09-22 2011-09-21 Procédé de formation de bords nets

Country Status (3)

Country Link
EP (1) EP2618992A1 (fr)
GB (1) GB2485758B (fr)
WO (1) WO2012038747A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9579855B2 (en) * 2014-12-15 2017-02-28 Spirit Aerosystems, Inc. Secondary groove for work piece retention during machining
DE102015223364B4 (de) * 2015-11-26 2017-11-16 Bayerische Motoren Werke Aktiengesellschaft Vorrichtung und Verfahren zum Herstellen von Textilverbundmaterialvorformlingen
FR3080323B1 (fr) * 2018-04-19 2021-05-14 Airbus Operations Sas Procede de fabrication d'une piece en materiau composite comprenant au moins une decoupe et piece en materiau composite ainsi obtenue

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4130269C2 (de) * 1990-09-13 1996-05-23 Toshiba Machine Co Ltd Verfahren und Vorrichtung zum Herstellen laminierter Prepreg-Teile
GB9823018D0 (en) * 1998-10-22 1998-12-16 British Aerospace Die cutting composite laminate
GB0623328D0 (en) 2006-11-22 2007-01-03 Airbus Uk Ltd A method for forming a feature in a piece of composite material
AT505948B1 (de) * 2007-10-29 2010-09-15 Gfm Beteiligungs & Man Gmbh Verfahren zum herstellen eines zuschnitts aus einem kunststoffgebundenen fasergelege

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2012038747A1 *

Also Published As

Publication number Publication date
GB2485758A (en) 2012-05-30
GB2485758B (en) 2013-03-13
WO2012038747A1 (fr) 2012-03-29
GB201015951D0 (en) 2010-11-03

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