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WO2018134597A1 - Capteur d'indication de cycles de chargement d'une structure - Google Patents

Capteur d'indication de cycles de chargement d'une structure Download PDF

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Publication number
WO2018134597A1
WO2018134597A1 PCT/GB2018/050144 GB2018050144W WO2018134597A1 WO 2018134597 A1 WO2018134597 A1 WO 2018134597A1 GB 2018050144 W GB2018050144 W GB 2018050144W WO 2018134597 A1 WO2018134597 A1 WO 2018134597A1
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WIPO (PCT)
Prior art keywords
sensing element
edge
sensor
loading
transparent layer
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Ceased
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PCT/GB2018/050144
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English (en)
Inventor
Meisam JALALVAND
Michael WISNOM
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University of Bristol
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University of Bristol
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L1/00—Measuring force or stress, in general
    • G01L1/06—Measuring force or stress, in general by measuring the permanent deformation of gauges, e.g. of compressed bodies
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/16—Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/16—Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge
    • G01B11/18—Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge using photoelastic elements
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
    • G01B5/30—Measuring arrangements characterised by the use of mechanical techniques for measuring the deformation in a solid, e.g. mechanical strain gauge
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L1/00—Measuring force or stress, in general
    • G01L1/24—Measuring force or stress, in general by measuring variations of optical properties of material when it is stressed, e.g. by photoelastic stress analysis using infrared, visible light, ultraviolet
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L1/00—Measuring force or stress, in general
    • G01L1/24—Measuring force or stress, in general by measuring variations of optical properties of material when it is stressed, e.g. by photoelastic stress analysis using infrared, visible light, ultraviolet
    • G01L1/241—Measuring force or stress, in general by measuring variations of optical properties of material when it is stressed, e.g. by photoelastic stress analysis using infrared, visible light, ultraviolet by photoelastic stress analysis
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
    • G01L5/0047—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes measuring forces due to residual stresses
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
    • G01L5/0052—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes measuring forces due to impact
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
    • G01L5/0061—Force sensors associated with industrial machines or actuators
    • G01L5/0071—Specific indicating arrangements, e.g. of overload
    • 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
    • G01M5/0033—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by determining damage, crack or wear
    • 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

Definitions

  • the present invention relates to a sensor for indicating the number of loading cycles that a structure has been subjected to.
  • Structures formed from composite or other materials are often required to be subjected to a number of loading cycles. Cycles of repeated loading and unloading result in material fatigue. Such loading cycles can cause structural damage and even the critical failure of the structure.
  • a sensor for indicating the number of loading cycles that a structure has been subjected to comprising: a transparent layer; a first sensing element comprising a first surface and a second surface connected to the first surface by a first side so as to define a first edge of the first surface where the first surface meets the first side, the first surface being coupled to the transparent layer, the second surface being arranged to be secured to the structure via a coupling interface such that loading of the structure causes corresponding deformation of the first sensing element; and a measurement region including one or more first visual markers, the measurement region being positioned to include, or be in registration with, the first edge, each first visual marker indicating a distance from the first edge along a measurement axis which extends in a generally perpendicular manner with respect to the first edge, wherein loading of the structure causes the first edge to decouple from the transparent layer causing a first decoupled zone resulting in a visible change in the external appearance of the sensor,
  • the first edge of the first sensing element serves as a delamination instigation line between the first sensing element and the transparent layer.
  • the first edge of the sensing element decouples from the transparent layer to form a decoupled zone between the first sensing element and the transparent layer.
  • the decoupled zone is visible through the transparent layer and has a different visual appearance in comparison to regions of the transparent layer that are still bonded to the sensing element(s).
  • the visual markers which can for example be printed on the transparent layer, can be used to measure the extent to which the decoupled zone propagates from the first edge to provide an indication of the number of loading cycles that the structure has been subj ected to.
  • the sensor according to the first aspect of the invention therefore results in a simple, robust loading cycle gauge that can be cheap to manufacture and can be easily read without the need for special training.
  • a sensor is particularly useful since the fatigue of a structure usually has no visible effect on a structure before a final failure occurs.
  • the sensor can provide a visual indication before such final failure, allowing the user to know the number of loading cycles that the structure can be subjected to and the amount of loading cycles remaining before the end of the structure's lifetime.
  • Sensors according to embodiments of the invention can be suitable for measuring variable and non-variable oscillatory loading cycles.
  • the ratio of the thickness of the sensing element to the thickness of the transparent layer can be such that the decoupled zone propagation rate, which is linearly proportional to the number of loading cycles, can cover the lifetime and the number of load cycles a structure is designed for.
  • the first surface and the second surface can be connected by a second side to define a second edge of the first surface where the first surface meets the second side, wherein a first internal angle between the first surface and the first side is closer to 90° than a second internal angle between the first surface and the second side, such that the second edge is relatively chamfered in comparison to the first edge.
  • the chamfer angle of the second edge is chosen in a way to avoid delamination initiation from the transparent layer to form decoupled zones within the designated fatigue life of the structure.
  • the side which is closer to 90° will decouple first, meaning that the measurement region can be positioned appropriately relative to the edge that will decouple first. It is preferred that the first angle is approximately 90° because this causes delamination to begin with the first load cycle.
  • the second angle is approximately 45° to build a delay into the instigation of delamination at the second edge, so as to allow the first decoupled zone to propagate through a desired amount of the measurement zone without interference from delamination propagating from the second edge.
  • the number of loading cycles that the structure is subjected to during the delay of the instigation of delamination depends on the chamfer angle at the second edge and the configuration of the sensing element and the transparent layer.
  • the sensor can comprise a second sensing element having a third surface and a fourth surface connected by a third side to define a third edge of the third surface where the third surface meets the third side, the third surface being bonded to the transparent layer, the fourth surface being arranged to be secured to the structure via a coupling interface such that loading of the structure causes corresponding deformation of the second sensing element, wherein the measurement region includes one or more second visual markers, the measurement region being positioned to include or be in registration with the third edge, each second visual marker indicating a distance from the third edge along the measurement axis, wherein loading of the structure causes the third edge to decouple from the transparent layer causing a second decoupled zone resulting in a visible change in the external appearance of the sensor, and further loading causes the second decoupled zone to propagate along the measurement axis in accordance with the number of the loading cycles to which the structure has been subjected to.
  • the third surface and the fourth surface can be connected by a fourth side to define a fourth edge of the third surface where the third surface meets the fourth side, wherein a third internal angle between the third surface and the third side is closer to 90° than a fourth internal angle between the third surface and the fourth side, such that the fourth edge is relatively chamfered in comparison to the third edge.
  • the first and second sensing elements can be arranged in a side by side, parallel manner with the first edge adjacent to the third edge. This can be simply implemented by cutting through a single sensing element to form the first and second parallel layers.
  • the first and/or third sides and/or edges can extend across the respective sensing element(s) in a linear manner, preferably orthogonal to the longitudinal or measurement axis of the sensing element.
  • the sensing direction must be parallel in relation to the measurement axis.
  • the second and/or fourth surfaces can be secured directly or indirectly to the structure. If the transparent layer is not capable of being directly coupled to the structure, then the sensing element can be bonded or otherwise directly coupled to the structure.
  • At least one of the visual markers can be positioned closer to the first edge of the first sensing element than the second edge of the first sensing element. At least one of the visual markers can be positioned closer to the third edge of the second sensing element than the fourth edge of the second sensing element.
  • the sensor can comprise a plurality of visual markers arranged in a regular spacing along the measurement axis of the, or each, sensing element and forming a linear scale.
  • the sensing element can have a portion of constant thickness which terminates as a boundary.
  • the visual marker can be aligned with the boundary, such as the linear scale can be aligned with the constant thickness boundary. This is because delamination from the constant thickness boundary can be linear.
  • One or more of the visual markers can each comprise a line arranged generally perpendicular to the measurement axis of the, or each, sensing element.
  • One or more or each sensing element can be made out of any material with a linear elastic response at least up to strains of about 0.3%.
  • One or more or each sensing element can be made out of fibrous composite materials, e.g. carbon/ epoxy composites, or metals, or polymers.
  • the stiffness of one or more or each sensing element should generally be higher than the transparent layer. The higher such stiffness difference, the more sensitive the sensor to the number of loading cycles applied.
  • the stiffness range of one or more or each sensing element can be between 50 GPa to 400 GPa.
  • the transparent layer can have linear elastic stress-strain curve at least up to 1% strains.
  • the transparent layer stiffness can be between 10 GPa to 100 GPa.
  • One or more or each sensing element can comprise fibres, and in some cases unidirectional fibres.
  • One or more or each sensing element can comprise fibre reinforced composite material, such as a carbon fibre reinforced composite material.
  • One or more or each sensing element and/or the transparent layer can be made of fibre reinforced thermosetting polymer composite material.
  • bonding of the first sensing element to the transparent layer can be achieved through co-curing the first sensing element and the transparent layer. Alternatively, bonding can be done through other means, for example using adhesive.
  • the first or each sensing element can comprise a first type of composite material and the transparent layer can comprise a second type of composite material which is distinct or different from the first type. Additionally, the first sensing element can comprise a plurality of different fibre types set within the matrix.
  • the transparent layer can be sized to have a larger footprint than the first or each sensing element so as to define a border region which can be used to secure the sensor to the structure.
  • the transparent layer can comprise glass fibre.
  • the sensor can further comprise a second layer on the opposite side of the first sensing element with respect to the transparent layer so as to encapsulate the first or each sensing element.
  • the first or each sensing element can have a sensing direction defined by the orientation of the first edge.
  • the first edge may have a linear direction.
  • the linear direction of the sensing edge may be perpendicular to the sensing direction.
  • the first or each sensing element can have a sensing direction defined by the intrinsic orientation of the fibres of the sensing element.
  • the sensing direction of each sensing element can be parallel with respect to the measurement axis of each sensing element.
  • each sensing element can have a distinct sensing direction. Two or more of the sensing directions can be perpendicular to each other.
  • the transparent layer can have chamfered edges to minimise the risk of premature de- bonding by reducing the stress concentration at the edges of the sensor.
  • an assembly comprising one or more sensors according to the first aspect.
  • One or more of the sensors can be integrally formed with the structure.
  • the assembly can comprise a single sensor that covers the majority of the surface area of the structure. According to a third aspect of the invention, there is provided a method of forming an assembly comprising:
  • Figures la and lb show sensors according to first and second embodiments of the invention.
  • Figure 2 shows the sensor according to Figure lb with fibres of the sensing element aligned in a single direction
  • Figures 3 a to 3 c show a schematic side view and a top view of the sensor according to Figure lb subjected to a number of loading cycles;
  • Figures 4a and 4b schematically illustrate a loading force applied during a loading cycle to a structure and a sensor according to an embodiment of the invention;
  • Figures 5a to 5c show sensors according to embodiments of the invention wherein the sensor comprises a plurality of separate sensing elements, and wherein the fibres in each sensing element are aligned in a distinct direction.
  • Figure la shows a sensor 1 according to an embodiment of the present invention.
  • the sensor 1 is arranged to indicate the number of loading cycles that a structure 18 has been subjected to.
  • the structure 18 can be made from any material such as steel, aluminium, reinforced concrete or fibre reinforced polymer composite.
  • the structure 18 could be made of other materials such as thermoplastic polymers or metals.
  • the sensor 1 comprises a transparent layer 12 and a sensing element 14.
  • the transparent layer 12 can be constructed from glass reinforced composite, or other translucent fibre, typically but not exclusively with an epoxy resin matrix.
  • the transparent layer 12 can be translucent.
  • the sensing element 14 can be partially visible through the transparent layer 12.
  • the sensing element 14 is formed from a material which is relatively opaque compared to the transparent layer.
  • the sensing element 14 can for example be constructed from fibre reinforced polymer composite or any other layered material. Carbon fibre grades are available in a very wide range and are particularly suitable for use in the sensing element due to them having a variety of well-defined material properties.
  • the sensing element 14 has a thickness Tl, which can for example be 0.5 mm or between 0.1mm and 1mm.
  • the transparent layer has a thickness T2, which can for example be 0.2 mm or between 0.1mm and 0.5mm.
  • the thicknesses Tl, T2 can each be uniform throughout non-chamfered portions of the sensing element and the transparent layer.
  • the sensing element 14 and has a first, upper surface 14a and a second, lower surface 14b.
  • the lower surface 14b of the sensing element 14 is connected to the upper surface 14a by the first side 14c so as to define a first edge El.
  • the first edge El is arranged to serve as a delamination instigation line between the sensing element 14 and the transparent layer 12, as described in more detail below.
  • a first internal angle a between the first surface 14a and the first side 14c is between 75° and 105° and preferably approximately 90° because the inventors have found that approximately 90° results a minimal or negligible delay between the application of loading cycles to the structure 18 and the instigation of delamination. It is preferred that the first internal angle a is between 85 0 to 95°.
  • the lower surface 14b of the sensing element 14 is also connected to the upper surface 14a by a second side 14c so as to define a second edge E2.
  • both of the first and second edges El, E2 may, over time, decouple from the transparent layer 12 to form decoupled zones.
  • the second edge E2 is chamfered in a way to delay such decoupling initiation to after the end of structure's fatigue lifetime. Therefore, the sensor is designed in a way that decoupling propagates only from the first edge El. The edge which is closer to 90° will decouple first.
  • a second internal angle ⁇ between the first surface 12a and the second side 14d is relatively remote from 90°, such that the second side 14d is relatively chamfered in comparison to the first side 14c, so as to completely delay instigation of delamination from the second edge E2.
  • This configuration builds a delay into the instigation of delamination at the second edge, so as to allow the first decoupled zone to propagate through a desired amount of a measurement zone (described in relation to Figures 3 a to 3b) without interference from delamination propagating from the second edge.
  • the second angle ⁇ is between 150° and 179° and preferably approximately 170°. Higher angles towards 180° are more preferred. Such shallow angles may be achieved by ply-drops over a long overlap using thin layered materials. This will produce a few steps in thickness change from full sensing layer thickness to the end.
  • the top surface 14a of the sensing element 14 is coupled to the bottom surface 12b of the transparent layer 12; for example, by the resin in composite sensing element 14 and transparent layers 12 or by way of adhesive bonding.
  • the same technique can be applied to attach the sensor 10 to the structure 18 at surface 14b.
  • the top surface 14a of the sensing element 14 is bonded to a lower surface 12b of the transparent layer 12 (gaps are shown for clarity purposes only).
  • the sensor 10 is attached to the structure 18 such that a force applied to the structure 18 is experienced by the sensor 10 similarly and deformation of the structure 18 causes corresponding deformation of the sensing element 14 of the sensor 10.
  • the sensing element 14 is subject to substantially the same strain as the region of the structure 18 to which it is attached.
  • the sensing element 14 experiences a corresponding number of loading cycles.
  • the sensor 10 defines an attachment surface via which it is arranged to be coupled to the structure 18.
  • the transparent layer 12 has a larger footprint than the sensing element 14 so as to define a border region B around the sensing element 14.
  • the attachment surface is defined by the lower surface 12c of the border region B and the lower surface 14b of the sensing element 14.
  • the surfaces 12c and 14b can be bonded or otherwise attached to the structure 18.
  • the border region B helps to secure the sensing element 14 to the structure 18.
  • the edge 12a of the transparent layer 12 can be chamfered to reduce the risk of premature de-bonding of the whole sensor due to peeling and shear-stress concentration.
  • the sensor 10 can include a bottom layer (not shown) arranged between sensing element 14 and the structure 18. As such, the sensing element 14 can be encapsulated between the transparent layer 12 and the bottom layer.
  • the bottom layer can be identical to the transparent layer 12.
  • sensing element 14 there is no direct coupling between the sensing element 14 and the structure at surface 14b, so that the sensor is secured to the structure only at surface 12c around the sensing layer.
  • the sensing element in this case is deformed through force applied by the transparent layer.
  • the senor 10 can be incorporated into a structure at the point of manufacture.
  • the sensing element 14 lies between the transparent layer 12 and the structure 18.
  • the sensor 10 can alternatively include first and second sensing elements 14, 15 arranged in a side by side, parallel manner.
  • the second sensing element 15 can be of similar or identical construction to the first sensing element 14.
  • the first and second sensing elements 14, 15 can be orientated with the first edge El of the first sensing element E2 being parallel and adjacent with respect to a third edge E3 of the second sending element, such that their sensing directions are aligned.
  • the first and third edges El, E3 can be non- parallel so that the sensor has a plurality of sensing elements with distinct sensing directions.
  • the third edge E3 is arranged to serve as a delamination instigation line between the second sensing element 15 and the transparent layer 12.
  • the first and second sensing elements 14, 15 can be formed by a cut C made through the thickness Tl of a unitary sensing element to form the two sensing elements 14, 15.
  • the cut C can be made for example using a ply cutter arrangement or by placing two separate sensing elements adjacent one another.
  • the sensing element comprises fibres 24.
  • the fibres 24 of the sensing elements 14, 15 are coUimated in a single direction Dl which defines the sensing direction of the sensor 10 and also defined the measurement axis along with delamination zones will propagate, as described in more detail below.
  • the fibres 24 are coUimated in a direction parallel to the length of the sensing element 14, but the fibres 24 can be coUimated in any direction relative to the length of the sensing element 14.
  • the cut C is schematically represented in a central position of the sensing element 14.
  • the cut C is perpendicular to the intrinsic direction Dl of the fibres 24.
  • a number of visual markers V are provided that indicate the number of loading cycles the structure has been subjected to.
  • the visual markers V are visible from the top surface of the sensor 10.
  • the arrangement of the visual markers V defines a measurement region MR which includes the cut C.
  • Each visual marker indicates a distance from the cut C along the length of the first sensing element 14.
  • the visual markers V define a scale that can be used to relate the propagation length of a decoupled zone to a number of load cycles.
  • the visual markers V are a regularly spaced array of lines extending in a perpendicular manner with respect to the length of the first sensing element 14.
  • the lines of the visual markers V can be printed on the top surface of the transparent layer 12.
  • the visual markers can take any suitable form.
  • FIG. 3a the structure 18 and the sensor 10 have not been subjected to any loading. Therefore, a decoupled zone Z is not present, while any light directed to the sensor 10 is completely absorbed by the sensing element of the sensor 10.
  • a schematic representation of the cut C is illustrated. The cut is positioned at the 0k mark of the visual marker V.
  • FIG 3b the structure 18 and sensor 10 have been subjected to a number of loading cycles.
  • the edges El and E3 have been decoupled from the transparent layer 12 to define a decoupled zone Z.
  • the waved lines W represent the extent of the delamination of the first sensing element 14 from the transparent layer 12. Due to the presence of the decoupled zone Z, light directed to the sensor surface is reflected. Therefore, the decoupled zone Z is visible as a light grey area in the TV of the sensor 10.
  • the decoupled zone Z can appear as a light grey or white strip with a length L.
  • the decoupled zone Z provides a visible indication of the number of loading cycles, since the length L of the decoupled zone Z corresponds to the number of loading cycles that the structure 18 has been subjected to.
  • the length L of the decoupled zone is linearly proportional to the number of loading cycles that the structure 18 has been subjected to.
  • the specific number of loading cycles can be measured by relating the decoupled zone propagation to the visual markers. According to the visual marker V on the TV of the sensor 10, the number of loading cycles that the structure in Figure 4b has been subjected to is about 5 OK.
  • the decoupled zone Z is further propagated.
  • the waved lines W indicate the further propagation of the decoupling between the sensing element 14 and the transparent layer 12.
  • the length L in this case corresponds to 150K loading cycles.
  • the loading may comprise loading cycles, which are repeatedly applied to the structure 18.
  • Such loading may be oscillatory with constant maximum loading per loading cycle.
  • oscillatory loading may comprise a non-constant maximum loading per loading cycle.
  • Figure 4a shows the structure 18 with no loading applied.
  • a bending force F is applied during a loading cycle, resulting in tensile stress T being applied to the fibres 24 of the sensing element 14 in a direction which is parallel to the direction Dl of the fibres 24.
  • Loading cycles applied to the sensor 10 cause the two edges El and E3 of the cut C to delaminate from transparent element creating the decoupled zone Z.
  • FIG. 5a shows a sensor 40a with a transparent layer 42, a first sensing element 44 and a second sensing element 46. Both of the sensors comprise fibres collimated in a single direction.
  • the fibres of the first sensing element are aligned in a first direction Dl
  • the fibres of the second sensing element are aligned in a second direction D2, as indicated by the arrows.
  • the first direction Dl is perpendicular to the second direction D2.
  • the two sensing element 44 and 46 can determine in which direction loading cycles have been applied to a structure, as well as the number of loading cycles in each direction, by identifying the extent of the visual change of the sensing element in the sensor 40a of Figure 5a.
  • Figure 5b shows the sensor of Figure 5a after a number of loading cycles has been applied in one direction.
  • the two parallel lines represent the decoupled zone Z between the two edges El and E2 of the sensing element 46, which indicates the visible change of the second sensing element 46. If one knows the sensing direction (i.e. the direction of collimation of fibres) in the second direction, then they can determine the direction of the loading the structure has experienced. Similarly, if one knows the direction of collimation of the fibres in the first sensing element, they can determine that the structure has not been subject to loading in a specific direction.
  • the sensing direction i.e. the direction of collimation of fibres
  • a single sensor could indicate loading in more than two directions through including multiple sensing element, with each sensing element having a single sensing direction (e.g. fibres collimated in a single direction), wherein all directions are distinct.
  • Such a sensor 40b is shown in Figure 5c, with sensing element 44 to 49 each with a different sensing direction. The sensor 40b therefore can indicate whether the structure has been subjected to loading in any of four directions.
  • sensing element could be used to provide a multi-directional sensor. More than four, or fewer than four, sensing elements could be used. For example, if ten sensing element were used, the sensor could indicate whether the structure has been subject to loading in any one of ten directions. Alternatively, more than one sensor each with a single sensing element could be attached to a structure to determine the direction of loading. Each sensing element has a sensing direction, and the sensors can be attached to the structure at different angles such that the sensing direction of each sensing element is at a different angle. This has the advantage that the user can customise the direction of detection of loading. The user may attach sensors to indicate a loading along the principal axes, or along the directions which are most vulnerable for the material to experiencing fatigue.
  • Non-variable oscillatory loading cycles e.g. those in pressure vessels
  • a pre-set length L for the decoupling zone Z for a given sensor at the end of a structure's lifetime is determined.
  • Non- variable oscillatory loading cycles means that the maximum working pressure or loading per cycle is constant.
  • the pre-set length of the decoupled zoned due to delamination is represented as 'a' in the following equations.
  • the number of fatigue cycles 'N' that the structure will be subjected to until the end of its lifetime can be determined from experimental data, the design phase of the product or it may be directly defined by the number of loading cycles the sensor is aimed to be used for.
  • the maximum load for the oscillatory fatigue cycles can be determined according to equation is the maximum mode-II energy release rate for the maximum applied load or strain the driving force of the delamination propagation for the sensor.
  • Equation 2 defines the relationship for remote applied maximum strain, for the
  • the material properties of a material combination set can be the inputs for the equation (2).
  • 'E C ' and 'ED' are the stiffness of the transparent layer and the stiffness of the sensing element respectively, s the modulus ratio and is the thickness ratio of the
  • the last step is to check if the stiffness of the sensing element ' ⁇ ⁇ ' is less than 10% of the stiffness of the structure 'K s '.
  • 'R' is the load ratio
  • 'Pmax' is the maximum working pressure or load in a cycle of loading.
  • the constant 'B' depends on the mechanical properties, moduli and geometry of the sensing element and the transparent layer and critical fracture toughness.

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  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Force Measurement Appropriate To Specific Purposes (AREA)

Abstract

L'invention concerne un capteur (1) permettant d'indiquer le nombre de cycles de chargement auxquels une structure (18) a été soumise, le capteur comprenant : une couche transparente (12) ; un premier élément de détection (14) comprenant une première surface et une seconde surface reliée à la première surface par un premier côté de façon à définir un premier bord de la première surface, la première surface coïncidant avec le premier côté, la première surface étant couplée à la couche transparente, la seconde surface étant conçue pour être fixée à la structure par le biais d'une interface de couplage de telle sorte que le chargement de la structure provoque une déformation correspondante du premier élément de détection ; et une zone de mesure comprenant un ou plusieurs premiers marqueurs visuels, la zone de mesure étant positionnée de manière à comprendre ou à être en alignement avec le premier bord, chaque premier marqueur visuel indiquant une distance à partir du premier bord le long d'un axe de mesure s'étendant d'une manière généralement perpendiculaire par rapport au premier bord, le chargement de la structure provoquant le découplage du premier bord de la couche transparente provoquant une première zone découplée conduisant à un changement visible de l'aspect extérieur du capteur, et une charge supplémentaire provoquant la propagation par la première zone découplée le long de l'axe de mesure en fonction du nombre des cycles de chargement auxquels la structure a été soumise.
PCT/GB2018/050144 2017-01-18 2018-01-18 Capteur d'indication de cycles de chargement d'une structure Ceased WO2018134597A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1700841.8A GB2558899B (en) 2017-01-18 2017-01-18 Sensor
GB1700841.8 2017-01-18

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WO2018134597A1 true WO2018134597A1 (fr) 2018-07-26

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GB (1) GB2558899B (fr)
WO (1) WO2018134597A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10729067B2 (en) * 2018-10-20 2020-08-04 Deere & Company Biomass impact sensor having a conformal encasement enveloping a pressure sensitive film

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050039669A1 (en) * 2003-08-21 2005-02-24 Elsasser Dan William Shock force indicating device
JP2011163784A (ja) * 2010-02-04 2011-08-25 Tokyo Metropolitan Univ ひずみ測定用シート及びひずみ測定装置

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050039669A1 (en) * 2003-08-21 2005-02-24 Elsasser Dan William Shock force indicating device
JP2011163784A (ja) * 2010-02-04 2011-08-25 Tokyo Metropolitan Univ ひずみ測定用シート及びひずみ測定装置

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
M WISNOM ET AL: "Pseudo-Ductile Hybrid Composites with Overload Sensing Capability", PROCEEDINGS OF THE AMERICAN SOCIETY FOR COMPOSITES 2016: THIRTY-FIRST TECHNICAL CONFERENCE ON COMPOSITE MATERIALS, 26 September 2016 (2016-09-26), XP055459425, ISBN: 978-1-60595-316-8, Retrieved from the Internet <URL:https://research-information.bristol.ac.uk/files/118891009/Wisnom_ASC_2016_Sensor.pdf> [retrieved on 20180314] *

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GB2558899A (en) 2018-07-25
GB201700841D0 (en) 2017-03-01
GB2558899B (en) 2022-05-25

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