GB2222974A - Manufacturing metal/fibre composite materials - Google Patents

Manufacturing metal/fibre composite materials Download PDF

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Publication number
GB2222974A
GB2222974A GB8915981A GB8915981A GB2222974A GB 2222974 A GB2222974 A GB 2222974A GB 8915981 A GB8915981 A GB 8915981A GB 8915981 A GB8915981 A GB 8915981A GB 2222974 A GB2222974 A GB 2222974A
Authority
GB
United Kingdom
Prior art keywords
layer
metal
fibres
composite material
explosive
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
GB8915981A
Other versions
GB2222974B (en
GB8915981D0 (en
Inventor
Suresh Kumar Gupta
John Timothy Pinder
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of GB8915981D0 publication Critical patent/GB8915981D0/en
Publication of GB2222974A publication Critical patent/GB2222974A/en
Application granted granted Critical
Publication of GB2222974B publication Critical patent/GB2222974B/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
    • B23K20/06—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating by means of high energy impulses, e.g. magnetic energy
    • B23K20/08—Explosive welding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/30—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being formed of particles, e.g. chips, granules, powder
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2264/00—Composition or properties of particles which form a particulate layer or are present as additives
    • B32B2264/10—Inorganic particles
    • B32B2264/105—Metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2305/00—Condition, form or state of the layers or laminate
    • B32B2305/08—Reinforcements
    • 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
    • Y10T29/49805—Shaping by direct application of fluent pressure
    • Y10T29/49806—Explosively shaping

Description

MANUFACTURE OF COMPOSITE MATERIALS ' 2,.-'2 9 7 4 2 This invention relates
to a method of manufacturing composite materials comprising a matrix in which reinforcing material such as continuous fibres are embedded.
A major problem encountered in the production of metal matrix composites relates to the reactivity of the metal matrix with the reinforcing material during manufacture. This is particularly a problem where the fibres are carbon fibres. In some methods of manufacture, molten metal is poured over, or contacts, the fibres. In other prior known methods the matrix material and the reinforcing fibres are consolidated together for sufficient times at elevated pressures and temperatures to cause a significant reaction to take place between the fibres and the matrix.
There are other processes such as high temperature vapour deposition of metal on to carbon fibres or diffusion bonding of a metal matrix to the fibres where there is a chemical reaction between the fibres and the metal matrix.
In all of the known methods of manufacture the chemical reaction between the metal matrix and the fibres is unacceptable because it deleteriously lowers the strength of the composite and can degrade the fibres to an extent that the composite is of inferior quality.
An object of the present invention is to provide a method of manufacturing a composite material comprising a metal matrix and reinforcing fibres in which the chemical reaction between the matrix and the fibres is at least reduced to a.i acceptable level.
According to the invention a method of manufacturing a multi-layered composite material in which reinforcing fibres are embedded in a metal matrix comprises the steps of providing in contact with an anvil a first metal layer, laying onto said first metal layer a further layer of reinforcing fibres, locating adjacent the fibre layer a second metal body, providing on the side of the second layer remote from the fibre layer an explosive chzrge, and detonating the explosive thereby to drive the second layer towards the first layer forming the second layer around the fibres and joining the first, second and fibres layers together.
Preferably the anvil is shaped according to a shape required of the composite material. Also, the first and second layers may have complementary shapes to form with the composite material an article or body of predetermined shape.
An embodiment of the invention will be described, by way of an example, with reference to the accompanying drawing which illustrates, schematically, one way of manufacturing a composite in accordance with the present invention.
Referring to the drawing, the metal matrix is formed by fabricating a first sheet 10 of metal which is to form the matrix and laying the sheet on to a suitably shaped anvil 11. One or more layers of reinforcing carbon fibres 12, which lie in preferred directions or is in the form of a woven mat, is laid on to the f irst sheet 10 of metal. Care is taken to ensure that the face of the sheet 10 in contact with the carbon fibres 12, and the carbon fibres themselves are clean and free from contaminants. A second sheet 13 of metal is located a small distance away from the layer, or layers 11. An 1 explosive charge 14 is laid in contact with the sheet 13 on the side remote from the fibres 12.
The composite is formed by detonating the explosive 14 so as to cause the sheet 13 to be accelerated towards, and impact with, the fibres 12 and the sheet 10, and thereby explosively form the sheets 10 and 13 around the fibres and form an explosively welded composite.
The sheets 10, 13 and the layers of fibres 12 may be of complementary shapes so as to form a shaped composite.
The metal sheets 10, 13 may be conventional metal sheets or they could conceivably be green compacts comprising powdered metal particles bonded in a suitable binder. In this latter case the explosively formed composite could be sintered after forming, at a temperature which would keep the reaction of the metal matrix and carbon fibres as low as possible.
If it is desired to control the chemical reaction between the metal matrix and the reinforcing fibres the composite can be heat treated in a carefully controlled manner to achieve the desired result after the explosive bonding step.

Claims (7)

  1. We claim:
    A method of manufacturing a multi-layered composite material in which reinforcing fibres are embedded in a metal matrix comprises the steps of providing in contact with an anvil a first metal layer, laylay onto said first metal layer a further layer of reinforcing fibres, locating adjacent the fibre layer a second metal body, providing on the side of the second layer remote from the fibre layer an explosive charge, and detonating the explosive thereby to drive the second layer towards the first layer forming the second layer around the fibres and joining the first, second and fibres layers together.
  2. 2 A method as claimed in claim 1 wherein the first and second layers have complementary shapes to form with the composite material an article or body of predetermined shape.
  3. 3 A method as claimed in claim 1 or claim 2 wherein the anvil is shaped according to the shape required of the composite material.
  4. 4 A method as claimed in any preceding claim wherein at least one of the metal layers comprises a green compact of powdered metal particles bonded together by means of a suitable binder.
  5. A method as claimed in claim 4 further comprising after the explosive forming step, a further step of sintering the explosively formed composite at a temperature below the reaction temperature of the -1 1 metal with the material of the reinforcing fibres.
  6. A method of manufacturing a multi-layered composite material substantially as hereinbefore described with reference to the particular example.
  7. 7 An article of composite material manufactured in accordance with a method as claimed in any one of claims 1 to 6.
    Published 1990at The PatentOffice. State House. 66 71 HigliHolborn, LondonWClR4TP. Further copies maybe obtained from The Patent Office Sales Branch. St Ma-y Cray. Orpington. Kent BR5 3RD. Printed by Multiplex techniques ltd, St Mary Cray, Kent. Cop.. 1187
GB8915981A 1988-09-23 1989-07-12 Manufacture of composite materials Expired - Fee Related GB2222974B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/248,188 US4881314A (en) 1988-09-23 1988-09-23 Method of explosively forming a multilayered composite material

Publications (3)

Publication Number Publication Date
GB8915981D0 GB8915981D0 (en) 1989-08-31
GB2222974A true GB2222974A (en) 1990-03-28
GB2222974B GB2222974B (en) 1992-09-02

Family

ID=22938067

Family Applications (1)

Application Number Title Priority Date Filing Date
GB8915981A Expired - Fee Related GB2222974B (en) 1988-09-23 1989-07-12 Manufacture of composite materials

Country Status (2)

Country Link
US (1) US4881314A (en)
GB (1) GB2222974B (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7354659B2 (en) * 2005-03-30 2008-04-08 Reactive Nanotechnologies, Inc. Method for fabricating large dimension bonds using reactive multilayer joining
US11084122B2 (en) * 2017-07-13 2021-08-10 Ohio State Innovation Foundation Joining of dissimilar materials using impact welding

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1282316A (en) * 1968-09-23 1972-07-19 Nitro Nobel Ab Method of forming reinforced metal articles

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3165826A (en) * 1962-05-16 1965-01-19 Synoctics Inc Method of explosively forming fibers
US3261088A (en) * 1963-01-23 1966-07-19 Du Pont Process for explosively bonding metal layers
US3419951A (en) * 1966-04-25 1969-01-07 Battelle Development Corp Fabrication of metal structures
US3614827A (en) * 1969-04-24 1971-10-26 Aerojet General Co Process for explosively bonding dissimilar metals
US3737976A (en) * 1971-04-15 1973-06-12 Whittaker Corp Method of forming filament reinforced metallic sheets
EP0060083B1 (en) * 1981-03-05 1985-05-29 Asahi Kasei Kogyo Kabushiki Kaisha Titanium clad steel plate
US4713871A (en) * 1984-12-12 1987-12-22 Nippon Oil & Fats Co., Ltd. Method for producing amorphous alloy shaped articles

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1282316A (en) * 1968-09-23 1972-07-19 Nitro Nobel Ab Method of forming reinforced metal articles

Also Published As

Publication number Publication date
GB2222974B (en) 1992-09-02
GB8915981D0 (en) 1989-08-31
US4881314A (en) 1989-11-21

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee

Effective date: 19930712