GB2378961A - Composite structure with fibres orientated along primary stress lines - Google Patents
Composite structure with fibres orientated along primary stress lines Download PDFInfo
- Publication number
- GB2378961A GB2378961A GB0120473A GB0120473A GB2378961A GB 2378961 A GB2378961 A GB 2378961A GB 0120473 A GB0120473 A GB 0120473A GB 0120473 A GB0120473 A GB 0120473A GB 2378961 A GB2378961 A GB 2378961A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fibres
- laid
- core
- correct orientation
- laid down
- 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- Withdrawn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
- 239000002131 composite material Substances 0.000 title claims abstract description 8
- 239000000835 fiber Substances 0.000 claims abstract description 9
- 239000006260 foam Substances 0.000 claims abstract description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 3
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 3
- 239000011162 core material Substances 0.000 claims abstract 7
- 239000004744 fabric Substances 0.000 claims description 7
- 238000010276 construction Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 4
- 239000002759 woven fabric Substances 0.000 claims description 3
- 239000004760 aramid Substances 0.000 claims 1
- 229920003235 aromatic polyamide Polymers 0.000 claims 1
- 239000011521 glass Substances 0.000 claims 1
- 239000007787 solid Substances 0.000 claims 1
- 238000004458 analytical method Methods 0.000 abstract description 2
- 239000003822 epoxy resin Substances 0.000 abstract description 2
- 229920000647 polyepoxide Polymers 0.000 abstract description 2
- 229920005989 resin Polymers 0.000 description 4
- 239000011347 resin Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000003993 interaction Effects 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
-
- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
- E04C2/00—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels
- E04C2/30—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure
- E04C2/34—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts
- E04C2/36—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels
- E04C2/365—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure composed of two or more spaced sheet-like parts spaced apart by transversely-placed strip material, e.g. honeycomb panels by honeycomb structures
-
- 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
- B29C70/06—Fibrous reinforcements only
- B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
- B29C70/086—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers and with one or more layers of pure plastics material, e.g. foam layers
-
- 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
- B29C70/56—Tensioning reinforcements before or during shaping
-
- 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
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
- B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
-
- E—FIXED CONSTRUCTIONS
- E04—BUILDING
- E04C—STRUCTURAL ELEMENTS; BUILDING MATERIALS
- E04C2/00—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels
- E04C2/02—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials
- E04C2/26—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials composed of materials covered by two or more of groups E04C2/04, E04C2/08, E04C2/10 or of materials covered by one of these groups with a material not specified in one of the groups
- E04C2/284—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials composed of materials covered by two or more of groups E04C2/04, E04C2/08, E04C2/10 or of materials covered by one of these groups with a material not specified in one of the groups at least one of the materials being insulating
- E04C2/296—Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials composed of materials covered by two or more of groups E04C2/04, E04C2/08, E04C2/10 or of materials covered by one of these groups with a material not specified in one of the groups at least one of the materials being insulating composed of insulating material and non-metallic or unspecified sheet-material
Landscapes
- Engineering & Computer Science (AREA)
- Architecture (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
A composite structure based on a core material such as foam or honeycomb comprises fibres laid along the primary stress lines found through the structure. The fibres may be stretched or tensioned so that the structure as a whole is pre-loaded. The fibres may be wet laid directly to the core, or stored between two disposable films and laid on to a core at a later date. In one embodiment carbon fibre tows are laid down on a foam core and then consolidated with epoxy resin which is subsequently cured under a vacuum. Preferably the orientation of the fibres is determined by stress analysis carried out by a computer. The composite structure may be formed as a panel or laid straight on to a shaped mould. The fibres may be laid by hand or by a mechanical device.
Description
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Stress distribution using composite fibres in structures Description This invention produces a structure that has specific fibre orientation to improve the transmitting and receiving of stresses through a structure.
Laminated composite structures produced at the moment are formed using woven or stitched fibres, which have a limited fibre orientation. This limits the maximum load carrying capabilities of the structure to certain orientations; currently a maximum of four directions in one layer is possible using a quadraxial fabric. This means that any loads occurring at a different orientation to the fibres are carried through the resin matrix of the laminate and not the intended fibres.
The orientation of fibres, for example, in a warp and weft direction in a woven fabric, means that added weight is carried by the structure in the form of fibres and their surrounding resin matrixes that are not carrying their full stress/weight potential.
The proposed invented system is the laying down of fibres orientated to the stress lines calculated to run though the structure. This enables the possibility of not using warp and weft technology, woven and stitched fabric laminates, not that it completely eliminates their use, due to the capability of the interaction of multiple technologies in one laminate. The fibres, as they are laid down can be stretched or tensioned (stressed) so the structure as a whole is pre-loaded to the load that is going to be applied to it.
Individual tows of composite fibres are laid down corresponding to the principal forces running through to the structure. The process improves the stress distribution through the structure by providing specific fibres for the loads to travel down ; this reduces the weight and material cost of a laminate by reducing the number of redundant fibres and their associated resin having to be used in the laminate. There is also a significant reduction in the waste material that beforehand had to be cut to give the correct fibre orientation, this was due to the limited availability of certain widths of fabric or the expensive manufacture of customised cloth construction for each component.
Labour time and hence costs are reduced, as computers can process the stress analysis, the design of the laminate schedule and the laying down of the fibres in the correct orientation. This does not eliminate the potential of the fibre line structure being laid down by hand.
Materials of manufacture are unlimited but require certain characteristics. The load carrying material must be available in a fibre form that can be laid down in varying orientation and can be bounded with a resin system. The core, if used, should provide an adequate bonding surface for the fibres. For example a carbon tow of fibres laid down on a foam core, consolidated with epoxy resin and cured under vacuum.
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The said system is also capable of being applied to panelled work for larger structures, such as buildings. The panels can be prefabricated on a flat bed or shaped mould with the fibres laid down as before, following the calculated principle forces running through the panel. The fibres on each panel are co-ordinated to the neighbouring panel so that fibre lines can continue through the complete structure. The panels can then be joined using traditional wet-lay/prepreg woven fabric strips on the laminate edges or an overlap within the fibre lines is allowed for so that they can then be connected at the construction site to enable continuous transferral of the loads from one panel to the next.
The fibres can either be laid straight on to the core and stored or between two layers of disposable film, as used at the moment with prepreg fibres, this allows the panel to be rolled up and stored so that it can be laid on to the core at the construction site at a later date. This allows panels to be stored taking up less space and the whole schedule of each panel to be laid up at once and then stored until construction can begin.
Claims (16)
- Claims 1) A composite structure that is based on a core material such as foam or honeycomb that can be manufactured in sections as set panels or as a whole structure. The composite structure is of fibre form, with fibres being laid along the primary stress lines found through the structure or panel.
- 2) The structure as defined in claim 1) but laid down with a stitched or woven fabric incorporated within the structure.
- 3) The structure as defined in claim 1) with varying thread diameter and thread count along the stress lines.
- 4) The structure as defined in claim 1) in which the fibres are laid down in correct orientation prior to construction and stored until used either on the core or between two film layers ready to be laid onto the core once construction has begun.
- 5) The structure as defined in claim 1) in which the fibres are carbon.
- 6) The structure as defined in claim 1) in which the fibres are aramid.
- 7) The structure as defined in claim 1) in which the fibres are glass.
- 8) The structure as defined in claim 1) in which the fibres are any suitable material.
- 9) The structure as defined in claim 1) in which the fibres are a combination/hybrid of any suitable fibres.
- 10) The structure as defined in claim 1) in which the fibres are laid down in the correct orientation by hand.
- 11) The structure as defined in claim 1) in which the fibres are laid down in the correct orientation by a mechanical device.
- 12) The structure as defined in claim 1) in which the fibres correct orientation is calculated by a computer.
- 13) The structure as defined in claim 1) in which the fibres correct orientation is calculated by a designer and/or architect and/or engineer within areas of stress related structures.
- 14) The structure as defined in claim 1) is a solid laminate structure and is not intended to change shape, or be a flexible cloth or fabric once cured.
- 15) The structure as defined in claim 1) if built in panel form can be joined by overlapping the fibres following the stress lines.
- 16) The structure as defined in claim 1) if built in panel form can be joined by strips of warp weft fabric over the joint of the two panels.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0120473A GB2378961A (en) | 2001-08-23 | 2001-08-23 | Composite structure with fibres orientated along primary stress lines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0120473A GB2378961A (en) | 2001-08-23 | 2001-08-23 | Composite structure with fibres orientated along primary stress lines |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB0120473D0 GB0120473D0 (en) | 2001-10-17 |
| GB2378961A true GB2378961A (en) | 2003-02-26 |
Family
ID=9920851
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB0120473A Withdrawn GB2378961A (en) | 2001-08-23 | 2001-08-23 | Composite structure with fibres orientated along primary stress lines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2378961A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1552298A (en) * | 1976-12-21 | 1979-09-12 | Messerschmitt Boelkow Blohm | Link |
| EP0040757A1 (en) * | 1980-05-22 | 1981-12-02 | Messerschmitt-Bölkow-Blohm Gesellschaft mit beschränkter Haftung | Windsurf board |
| DE3127017A1 (en) * | 1981-07-09 | 1983-01-27 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Process for producing short-fibre prepregs |
| US4378394A (en) * | 1981-03-16 | 1983-03-29 | Nissan Motor Company, Limited | Reinforcing member |
| US5139843A (en) * | 1988-11-24 | 1992-08-18 | Tonen Kabushiki Kaisha | Elongated lightweight fiber reinforced composite resin pultrusion-formed piece |
| US5196212A (en) * | 1990-05-08 | 1993-03-23 | Knoblach Gerald M | Electric alignment of fibers for the manufacture of composite materials |
| GB2276119A (en) * | 1993-03-18 | 1994-09-21 | Secr Defence | Hybrid composite materials |
| EP0696500A2 (en) * | 1994-08-09 | 1996-02-14 | Technoform Caprano + Brunnhofer KG | Extruded profile bar made of thermoplastic material destined to resist predetermined loads |
| WO1999001186A1 (en) * | 1997-06-30 | 1999-01-14 | Dakuga Holding Ltd. | Planks used for sliding on snow |
-
2001
- 2001-08-23 GB GB0120473A patent/GB2378961A/en not_active Withdrawn
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1552298A (en) * | 1976-12-21 | 1979-09-12 | Messerschmitt Boelkow Blohm | Link |
| EP0040757A1 (en) * | 1980-05-22 | 1981-12-02 | Messerschmitt-Bölkow-Blohm Gesellschaft mit beschränkter Haftung | Windsurf board |
| US4378394A (en) * | 1981-03-16 | 1983-03-29 | Nissan Motor Company, Limited | Reinforcing member |
| DE3127017A1 (en) * | 1981-07-09 | 1983-01-27 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Process for producing short-fibre prepregs |
| US5139843A (en) * | 1988-11-24 | 1992-08-18 | Tonen Kabushiki Kaisha | Elongated lightweight fiber reinforced composite resin pultrusion-formed piece |
| US5196212A (en) * | 1990-05-08 | 1993-03-23 | Knoblach Gerald M | Electric alignment of fibers for the manufacture of composite materials |
| GB2276119A (en) * | 1993-03-18 | 1994-09-21 | Secr Defence | Hybrid composite materials |
| EP0696500A2 (en) * | 1994-08-09 | 1996-02-14 | Technoform Caprano + Brunnhofer KG | Extruded profile bar made of thermoplastic material destined to resist predetermined loads |
| WO1999001186A1 (en) * | 1997-06-30 | 1999-01-14 | Dakuga Holding Ltd. | Planks used for sliding on snow |
Also Published As
| Publication number | Publication date |
|---|---|
| GB0120473D0 (en) | 2001-10-17 |
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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) |