WO2010004324A1 - Electrical circuit assemblies and structural components incorporating same - Google Patents
Electrical circuit assemblies and structural components incorporating same Download PDFInfo
- Publication number
- WO2010004324A1 WO2010004324A1 PCT/GB2009/050800 GB2009050800W WO2010004324A1 WO 2010004324 A1 WO2010004324 A1 WO 2010004324A1 GB 2009050800 W GB2009050800 W GB 2009050800W WO 2010004324 A1 WO2010004324 A1 WO 2010004324A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- paths
- health monitoring
- structural health
- monitoring arrangement
- arrangement according
- Prior art date
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Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0016—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings of aircraft wings or blades
-
- 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
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
-
- 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
- B29C70/88—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
- B29C70/882—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding
-
- 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
- B29C70/88—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
- B29C70/882—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding
- B29C70/885—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding with incorporated metallic wires, nets, films or plates
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0041—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by determining deflection or stress
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0083—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by measuring variation of impedance, e.g. resistance, capacitance, induction
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01B—CABLES; CONDUCTORS; INSULATORS; SELECTION OF MATERIALS FOR THEIR CONDUCTIVE, INSULATING OR DIELECTRIC PROPERTIES
- H01B5/00—Non-insulated conductors or conductive bodies characterised by their form
- H01B5/14—Non-insulated conductors or conductive bodies characterised by their form comprising conductive layers or films on insulating-supports
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
Definitions
- This invention relates to electrical circuit assemblies and structural components incorporating the same, and in particular but not exclusively to structural health monitoring arrangements.
- the term 'structural health' is used to mean the health of the material in terms of extraneous damage caused by the impact by objects, erosion etc as well as internal damage such as stress-induced cracking, delamination and also simply the measurement of the local stresses and strains to which the composite is subjected.
- the navigation system may have an inertial platform that will determine and report the accelerations to which the airframe has been subject, but it will not report on the magnitude of local stresses and strains.
- a structural health monitoring arrangement comprising a component formed of a fibre reinforced composite material including a plurality of electrically conducting fibres defining electrical paths running through said composite material, and a detector for monitoring an electrical characteristic of one or more of said paths, thereby to determine a structural condition of said component.
- the electrically conducting fibres may be intrinsic to the structure as reinforcing fibres so that they perform a dual function and do not significantly compromise the structure integrity of the component.
- said paths may be arranged in groups in respective co-ordinate directions.
- said groups may extend in orthogonal linear directions in a two-dimensional array to allow detection in X and Y directions.
- said groups may be layered in a third orthogonal direction thereby to allow detection in a third Z direction.
- a grid is defined over an area or component to be monitored, and we provide two types of grid configuration.
- an open node network the electrical paths are not in electrical contact at the nodes or crossings of said co-ordinate directions.
- a closed node network the electrical paths are in electrical contact at the nodes of said co-ordinate directions thereby to provide a closed node network.
- the detector may monitor the continuity of one or more selected paths and thereby determine the co-ordinates of an event causing a break in continuity of one or more of said paths.
- the detector may monitor the network resistance between selected paths across the network thereby to deduce the location of an event causing a detectable change in resistance.
- the detector may monitor at spaced intervals to collect data pertaining to said paths, and determine if the changes in said data exceed a threshold value at one or more locations.
- the electrically conducting fibres are selected to be piezoresistive, whereby the resistance of a given fibre varies in accordance with the applied strain.
- selected paths are spaced from a neutral bending axis of the component, thereby to allow detection of bending of the component.
- suitable fibre arrangements may be designed to measure torsion.
- two groups of electrically conducting paths may be spaced one to either side of the neutral bending axis with the detector monitoring the change of resistance of each group and thereby classifying any strains in terms of a tensile load, a compressive load, bending in a first sense or bending in a second, opposite sense.
- the component may include an electrical screening element disposed adjacent at least one external surface of said component, and said electrical screening element may be connected to respective ends of one or more of said electrical paths, thereby serving as a ground, or return path.
- this invention provides a structural health monitoring arrangement comprising a component formed of a fibre reinforced composite material including a plurality of elongate conductors of a piezoresistive material running through said composite, and a detector for monitoring the resistance of one or more of said elongate conductors thereby to determine a structural condition of said component.
- each conducting fibre may have an electrically conducting surface.
- This surface may be an electrically conducting coating provided on the interior of the fibre, where the fibre is hollow. Additionally or alternatively, the electrically conducting surface may be provided on the exposed surface of the fibre. Still further, the or each fibre may be made of electrically conducting material itself. For example, the or each conducting fibre could be surrounded by glass fibres to electrically isolate it from the other conducting fibres.
- the fibres may be collected with other like fibres into conducting tows that are electrically isolated from other such tows in the structure.
- the electrically conducting coating, core or layer may be deposited on or in the fibre.
- the electrically conducting coating, core or layer may be deposited at least partially in the vapour phase.
- the electrically conducting coating, core or layer may be deposited by applying molten metal material to the fibre and allowing said metal material to solidify to create said electrically conducting layer or coating.
- Another method is to apply the coating, core or layer by means of electroless plating, by electroplating, or a combination of both.
- a first layer or layers may be deposited by electroless plating with a subsequent layer or layers being deposited by electroplating. This allows greater control of the overall plating process.
- the coating, core or layer may be selected from any suitable conducting material including amongst which are metals including, but not limited to silver, gold, copper, aluminium, chromium, nickel iron, gallium, indium and tin, and alloys including one or more of the aforesaid, and also conductive polymers, electrolytes and colloids.
- the fibres may be of any suitable fibre that can be used in the construction of a fibre reinforced composite material including carbon fibres, glass fibres, mineral fibres, ceramic fibres, polymeric fibres, and metal fibres.
- the matrix material preferably comprises a suitable material which is electrically insulating.
- the matrix material may be polymeric, elastomeric, metal, glass, and/or ceramic, or a mixture of these.
- electrically conducting and “electrically insulating” are relative and intended to be interpreted as meaning that a useful electrical signal is transmitted along a desired signal or power path.
- metal is used to include not only pure metals but metal alloys. Also included are semiconductors and semi-metals.
- the arrangement can monitor various physical, chemical, electrical or electro-magnetic influences to which the structural component is exposed.
- said component comprises a group of a plurality of spaced electrically conducting fibres extending in a first coordinate direction and a second group of a plurality of electrically conducting fibres extending in a second coordinate direction, and electrical monitoring means for monitoring the first and second groups to determine an electrical characteristic of the respective fibres and to provide an indication of the structural health of the component and to provide an indication of the location of an event that alters the said electrical characteristic of one or more fibres in both groups.
- Suitable methods include capacitance, reflectometry, and time domain reflectometry.
- the said first and second groups may be generally orthogonally arranged to provide columns and rows of electrically conducting fibres, and said electrical monitoring means may be adapted to detect changes in said electrical characteristic due to an event by reference to the row and column and thereby provide an indication of the location of the event.
- Figure 1 is a schematic view of an arrangement for infiltrating a composite coupon
- Figure 2 is a schematic view of an arrangement designed to allow detection and location of structural damage
- Figures 3a to 3c are detailed views of various coupling configurations for use in embodiments of the invention, using ohmic, and contactless capacitative and inductive coupling respectively;
- Figure 4 is a schematic view of the use of an arrangement of this invention for monitoring sensors over an extended surface area of an aircraft;
- Figure 5 is a schematic view of a composite structure in which a central core conductor is surrounded by a layer of screening fibres spaced from the core by intermediate fibres to allow the transmission characteristics to be varied;
- Figure 6 is a schematic view of a composite component with a closed node structural health monitoring system
- Figure 7 is a schematic view of a composite component with a piezoresistive structural health monitoring system.
- a hollow fibre is provided with an internal electrically conducting coating, layer or core so that a fibre composite material can be made which has electrically conducting fibres running through it to provide pathways for signals, power etc.
- a fibre composite structure can be provided in which the interface between the external fibre and the matrix material is unaffected, with the electrically conducting region being housed fully within the fibres.
- Direct infiltration with liquid metal provides a simple and straightforward approach to creating a metal cored fibre. It is desirable to use a metal with a conveniently low melting point so that both fibres and composites could be treated without risk of damage Electroless Plating
- a suitable plating technique uses the reduction of a chloroauhc acid solution (HAuCI 4 ) by glycerol as described by Takeyasu et al. [Takeyasu N,
- Reduction agent 0.5%vol.
- glycerol in Dl water Sensitizer 26mM SnCb +7OmM trifluoroacetic acid (TFA) in Dl water
- short composite coupons 18 of dimensions 30- 40mm long x 10-15mm wide x 2-3mm thick were prepared so that infiltration of full scale fibres could be investigated.
- the composite was made using a 0790° woven fabric and so the long edges 20 of the coupons were sealed to prevent ingress of materials into fibres running in the 90° direction.
- a polycarbonate reservoir 22 and a pressure fitting 24 were bonded over one of the open ends of the coupon to facilitate the introduction or removal of materials. This configuration allowed materials to be introduced by capillary action or through the use of positive and negative pressure differentials as with the single fibre test specimens..
- the composite test specimen was used to investigate the plating behaviour of the gold solution at full-scale
- the reservoir was filled with sensitizer and this was blown through using dry nitrogen at 2.5 bar until the open end of the specimen was seen to be wet. Typical filling times at 2.5 bar were of the order 5-10 seconds for a 40mm long panel.
- the excess sensitizer was removed from the reservoir by pipette and replaced with Dl water which was then blown through until the reservoir was empty.
- the rinsing process was repeated a second time in an attempt to ensure that any excess sensitizer had been removed. Blowing was continued until bubbles could be seen on the open edge of the panel indicating that most of the remaining fluid had been expelled.
- Freshly prepared ⁇ Xgold/ethylene glycol solution was introduced into the reservoir and blowing was started using 2.5 bar dry nitrogen as before. The reaction was seen to start immediately in the reservoir as the walls turned black in a few seconds. It was thought that this was possibly due to the presence of excess sensitizer as it is difficult to rinse the reservoir thoroughly due to its small size and narrow induction port. Blowing was continued for several minutes and the panel was observed to take on a pink appearance within a short time. After approximately 5 minutes, blowing was discontinued and the reservoir was vented to remove the pressure differential. The reservoir was still filled with excess plating solution as was the composite panel and the specimen was left in this condition for 2 hours to allow any remaining metal to plate out. During this time the pink colouring became progressively stronger. This discoloration was taken as an indication that gold was plating out onto the fibres as thin gold films observed on the pipettes also showed a pink/purple coloration before taking on a metallic appearance.
- sensitizer was introduced from the open end of the composite panel by dipping and 10 minutes was allowed for infiltration. Contamination of the reservoir was avoided as infiltration by capillary action would automatically stop at the far end of the panel inside the reservoir. After filling, the sensitizer was blown out using 2.5 bar nitrogen as before. The reservoir was then filled with Dl water and blown through to rinse out the panel. Two rinses were performed as before. The reservoir was filled with plating solution and blown through for ⁇ 4mins.
- the panel began to discolour from the open end almost immediately with the purple colour progressing to the other end of the panel over ⁇ 5 minutes. No discolouration was observed in the residual fluid in the reservoir for the first -20-30 minutes after filling after which it proceeded to darken at a rate similar to that observed for the pipettes. The panel was left full of plating solution overnight to finish plating. The composite panel was considerably darker than after the first attempt and the reservoir was almost completely free of discolouration and plating suggesting that the revised filling technique had been successful and that the majority of the potential metal had been deposited onto the fibres.
- the first panel (Example 3) demonstrated the ability to incorporate multiple parallel connections and was used to explore potential connection methods and for electrical tests.
- Conductive pins were added to the panel by drilling small holes normal to the surface directly over the location of the conductive fibre tows. Gold plated solder pins were push fitted into the holes to form electrical contacts. Several of the pins were also bonded into the panel using a silver loaded conductive epoxy resin for added robustness.
- a second panel (Example 4) was configured to give three parallel electrical connections. These were accessible via embedded connectors on the panel ends.
- the panel demonstrated the material's ability to carry power using a 9V battery and a LED.
- a bi-colour (red/green) LED was used to demonstrate the ability to carry multiple power rails.
- the second demonstrator was also used to investigate the feasibility of transferring data via the material.
- the three conductors allowed the panel to be configured to carry RS232 compatible serial data streams in both directions. Text and data files were transferred between two laptop computers at rates up to 56kbit/s.
- the third demonstrator (Example 5) consisted of a panel 30 approximately 150mm square containing an 8x8 array of parallel conductors 32 running in the X and Y planes. The conductors were spaced approximately 10mm apart and an in-plane insulating layer was formed between the X and Y conductors from several layers of woven glass fibre matting .
- the signal transmission properties of the conductors were tested by injecting a sine wave signal at one end and monitoring the far end for signs of attenuation or degradation.
- the test setup used two adjacent tracks on the X plane as signal conductor and return lines and the output was measured across a 56 ⁇ load.
- the conducting elements may be electrically coupled to other circuitry or components.
- the coupling may be ohmic, for example by providing terminals 40 that are in direct physical contact with the conducting fibres 42 and which extend out of the composite.
- the coupling may be contactless, by means of a capacitative or inductive coupling elements 44 or 46.
- the coupling elements could take the form of adhesive pads that can be bonded to the composite material permanently or semi-permanently to provide the required electrical coupling with the underlying conducting fibres.
- the circuit so formed may be used to transmit and analogue or digital data signals together, in some instances, with power.
- the data signal may be modulated onto a carrier, and the carrier may be rectified to provide a power source.
- the circuits so formed may be used for numerous purposes other than conventional power supply or data transfer.
- an array of surface sensors 50 may be provided on an exposed surface of a composite element 52 on an aircraft to detect one or more parameters relating to the structure and/or aerodynamic environment and connected to monitoring equipment 56 by the electrically conducting fibres 54 within the composite element.
- the use of inductive or capacitive coupling between the sensors 50 and the electrically conducting fibres 52 allows easy reconfiguration and setup.
- an array of conductors on the composite allows redundancy to be built in so that a circuit can be rerouted if required.
- the conductors could be used to heat the composite material and thus provide de- icing, or to allow the infrared signature of a body to be modified.
- a composite structure 60 could be designed to allow the electrical characteristics along the signal path to be modified.
- These intermediate fibres 66 may be solid or hollow or a mixture of both.
- the impedance or capacitance of the conductor may be modified by introducing or withdrawing a suitable fluid material into or from said hollow fibres via a manifold system (not shown).
- a manifold system not shown.
- the apparatus and methods described herein may be used with other techniques in which a composite fibre structure is configured to perform functions other than purely structural.
- the apparatus and methods herein may be combined with other techniques to make up intelligent structures capable of e.g. shielding and detection of radiation and/or structures capable with a facility the structural health momtorinq and/or self repair.
- the conductors are formed of tows of conducting fibres extending in X and Y co-ordinate directions but without contact at the crossing points as the X and Y paths are insulated from each other.
- This is referred to herein as an open node grid or network.
- co-ordinate systems such as e.g. a polar system, and the paths may be non-linear and designed to concentrate in regions of particular interest e.g. to increase the resolution of the grid in these areas, or to align the paths across lines of stress concentration in the structure.
- the paths may be of zig-zag form.
- the component may be provided with layers of the X-Y open node grid, stacked in the Z direction so that events occurring throughout the thickness of the composite can be detected.
- delamination or cracking may initiate anywhere in the depth, and so sensitivity or detection capability in the Z direction provides further advantages.
- a processor 74 applies a signal to each of the columns 70 in turn and for each column the voltage at each row is detected and stored by the processor. This is repeated for all the columns and so data for the whole network is captured.
- This may conveniently be done by defining a table 76 corresponding to the rows and columns of the network and storing in each cell of the table data representing the voltage drop between a selected row and column. By then examining these values, and looking for a peak, the location of an event such as a crack or spalling 78 interrupting the network may be determined. For example, the values may be colour coded and displayed as a two- or three-dimensional image on a display 80.
- the processor may operate to scan or convert data values represented by the tabular form above to obtain a frame of data and then monitor for differences between successive frames. This technique of monitoring for differences may also be applied to the open node grids described above.
- this technique may be used in conjunction with other suitable structural health monitoring techniques such as acoustic, active/passive acoustic detection, conventional strain gauges, optical (Bragg grating type) strain gauges, and time domain reflectometry.
- suitable structural health monitoring techniques such as acoustic, active/passive acoustic detection, conventional strain gauges, optical (Bragg grating type) strain gauges, and time domain reflectometry.
- the gauge factor has been measured to be approximately 0.2.
- one group 82 of conducting fibres is disposed above the neutral bending axis and one below 84.
- the resistances may be compared using a bridge circuit in known fashion.
- the changes in resistance of the groups above and below the neutral bending axis are monitored and analysed to determine whether the component is under tension, compression or bending.
- both groups indicate tension, this indicates that the component is under tension, and the same applies for compression. If one group indicates compression and the other tension, this indicates that the component is experiencing bending, with the bending sense being determined by which is in tension. In other arrangements, not shown, there may be several groups distributed through the thickness of the components and each individually addressable.
- the component is provided with screening or grounding layers here adjacent the upper and lower surfaces of the components.
- These layers are electrically conducting and may be formed of conducting fibres.
- the layers may be connected to each other and used as a common return path by connecting one end of each group of fibres to the adjacent layer. It is important in this instance to ensure that they do not contribute to or mask the piezoresistive effect of the detecting groups.
- these screening layers may be made up of lay ups of conducting fibres that provide no resistive response when the component is loaded.
- respective groups of fibres may be disposed in co-ordinate groups e.g. X and Y with the output data being correlated to determine the location of an event.
- groups of fibres e.g. X and Y with the output data being correlated to determine the location of an event.
- the sensing path is responsive to strain rather than continuity of the fibres
- the impact of an object in the interstices between the X and Y groups will be picked up as a strain wave travels from the impact point.
- the location of an impact can be determined by interpolating the data.
- the X and Y data may be displayed as a two- dimensional image with the row data and column data suitably thresholded or colour coded so that the impact point can be deduced.
- the data may be obtained at intervals with the data being compared between frames to identify changes.
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Astronomy & Astrophysics (AREA)
- Laminated Bodies (AREA)
- Investigating Or Analyzing Materials By The Use Of Electric Means (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Insulated Conductors (AREA)
- Moulding By Coating Moulds (AREA)
- Reinforced Plastic Materials (AREA)
- Chemical Or Physical Treatment Of Fibers (AREA)
- Woven Fabrics (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA2730186A CA2730186C (en) | 2008-07-08 | 2009-07-07 | Electrical circuit assemblies and structural components incorporating same |
US13/003,145 US8534133B2 (en) | 2008-07-08 | 2009-07-07 | Electrical circuit assemblies and structural components incorporating same |
KR1020117002796A KR101286252B1 (en) | 2008-07-08 | 2009-07-07 | A structural health monitoring arrangement |
JP2011517240A JP2011527432A (en) | 2008-07-08 | 2009-07-07 | Electrical circuit assembly and structural components incorporating it |
AU2009269753A AU2009269753B2 (en) | 2008-07-08 | 2009-07-07 | Electrical circuit assemblies and structural components incorporating same |
EP09785280A EP2307870A1 (en) | 2008-07-08 | 2009-07-07 | Electrical circuit assemblies and structural components incorporating same |
IL210473A IL210473A (en) | 2008-07-08 | 2011-01-05 | Electrical circuit assemblies and structural components incorporating same |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GBGB0812483.6A GB0812483D0 (en) | 2008-07-08 | 2008-07-08 | Electrical Circuit Assemblies and Structural Components Incorporating same |
GB0812483.6 | 2008-07-08 |
Publications (1)
Publication Number | Publication Date |
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WO2010004324A1 true WO2010004324A1 (en) | 2010-01-14 |
Family
ID=40262328
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/GB2009/050799 WO2010004323A1 (en) | 2008-07-08 | 2009-07-07 | Electrical circuit assemblies and structural components incorporating same |
PCT/GB2009/050800 WO2010004324A1 (en) | 2008-07-08 | 2009-07-07 | Electrical circuit assemblies and structural components incorporating same |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/GB2009/050799 WO2010004323A1 (en) | 2008-07-08 | 2009-07-07 | Electrical circuit assemblies and structural components incorporating same |
Country Status (13)
Country | Link |
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US (2) | US8796553B2 (en) |
EP (2) | EP2307870A1 (en) |
JP (2) | JP2011528841A (en) |
KR (2) | KR101274185B1 (en) |
AU (2) | AU2009269752B2 (en) |
BR (1) | BRPI0915580A2 (en) |
CA (2) | CA2729929C (en) |
ES (1) | ES2686317T3 (en) |
GB (1) | GB0812483D0 (en) |
IL (2) | IL210473A (en) |
PL (1) | PL2310190T3 (en) |
TR (1) | TR201810584T4 (en) |
WO (2) | WO2010004323A1 (en) |
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GB0903642D0 (en) | 2009-02-27 | 2009-09-30 | Bae Systems Plc | Electroless metal deposition for micron scale structures |
CA2767809A1 (en) | 2009-07-16 | 2011-01-20 | 3M Innovative Properties Company | Submersible composite cable and methods |
US9081409B2 (en) * | 2011-01-21 | 2015-07-14 | The United States Of America As Represented By The Secretary Of The Navy | Event detection control system for operating a remote sensor or projectile system |
US9233765B2 (en) | 2011-06-16 | 2016-01-12 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Multi-dimensional damage detection |
US9389138B2 (en) * | 2012-10-26 | 2016-07-12 | General Electric Company | Apparatus and method to detect damage of a component of a system |
EP3241009B1 (en) * | 2014-12-29 | 2019-01-09 | Harting It Software Development GmbH & Co. Kg | Offset detection between joined components |
KR101665086B1 (en) * | 2015-02-24 | 2016-10-13 | 울산과학기술원 | Structural health monitoring system using carbon fiber grid |
US9857248B2 (en) * | 2015-06-16 | 2018-01-02 | The Boeing Company | Sensor system for laminated structures |
DE102016202769B4 (en) | 2016-02-23 | 2022-09-15 | Technische Universität Dresden | Sensor for the integral or spatially resolved measurement of strains based on pre-damaged carbon fibers |
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CA2730186C (en) | 2013-12-03 |
KR101286252B1 (en) | 2013-07-12 |
AU2009269752B2 (en) | 2014-05-29 |
US8534133B2 (en) | 2013-09-17 |
PL2310190T3 (en) | 2018-10-31 |
WO2010004323A1 (en) | 2010-01-14 |
KR20110028382A (en) | 2011-03-17 |
JP2011527432A (en) | 2011-10-27 |
JP2011528841A (en) | 2011-11-24 |
BRPI0915580A2 (en) | 2016-01-26 |
US20110120750A1 (en) | 2011-05-26 |
EP2307870A1 (en) | 2011-04-13 |
CA2730186A1 (en) | 2010-01-14 |
IL210473A (en) | 2015-07-30 |
ES2686317T3 (en) | 2018-10-17 |
US20110107843A1 (en) | 2011-05-12 |
IL210473A0 (en) | 2011-03-31 |
TR201810584T4 (en) | 2018-08-27 |
CA2729929C (en) | 2014-10-21 |
EP2310190A1 (en) | 2011-04-20 |
CA2729929A1 (en) | 2010-01-14 |
AU2009269753B2 (en) | 2014-03-27 |
IL210472A0 (en) | 2011-03-31 |
KR20110028383A (en) | 2011-03-17 |
AU2009269752A1 (en) | 2010-01-14 |
EP2310190B1 (en) | 2018-06-27 |
KR101274185B1 (en) | 2013-06-18 |
GB0812483D0 (en) | 2009-01-07 |
US8796553B2 (en) | 2014-08-05 |
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