EP1678474A2 - Dispositif permettant de detecter les sollicitations subies par des parties structurales en composite a base de fibres - Google Patents

Dispositif permettant de detecter les sollicitations subies par des parties structurales en composite a base de fibres

Info

Publication number
EP1678474A2
EP1678474A2 EP04791066A EP04791066A EP1678474A2 EP 1678474 A2 EP1678474 A2 EP 1678474A2 EP 04791066 A EP04791066 A EP 04791066A EP 04791066 A EP04791066 A EP 04791066A EP 1678474 A2 EP1678474 A2 EP 1678474A2
Authority
EP
European Patent Office
Prior art keywords
fiber
fiber composite
strain gauges
evaluation device
designed
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP04791066A
Other languages
German (de)
English (en)
Inventor
Karl-Heinz Haase
Carsten Hecker
Sebastian Klein
Sigmund Glaser
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hottinger Bruel and Kjaer GmbH
Original Assignee
Hottinger Baldwin Messtechnik GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hottinger Baldwin Messtechnik GmbH filed Critical Hottinger Baldwin Messtechnik GmbH
Publication of EP1678474A2 publication Critical patent/EP1678474A2/fr
Withdrawn legal-status Critical Current

Links

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
    • 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
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L1/00—Measuring force or stress, in general
    • G01L1/20—Measuring force or stress, in general by measuring variations in ohmic resistance of solid materials or of electrically-conductive fluids; by making use of electrokinetic cells, i.e. liquid-containing cells wherein an electrical potential is produced or varied upon the application of stress
    • G01L1/22—Measuring force or stress, in general by measuring variations in ohmic resistance of solid materials or of electrically-conductive fluids; by making use of electrokinetic cells, i.e. liquid-containing cells wherein an electrical potential is produced or varied upon the application of stress using resistance strain gauges
    • G01L1/2287—Measuring force or stress, in general by measuring variations in ohmic resistance of solid materials or of electrically-conductive fluids; by making use of electrokinetic cells, i.e. liquid-containing cells wherein an electrical potential is produced or varied upon the application of stress using resistance strain gauges constructional details of the strain gauges
    • 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
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/0014—Type of force applied
    • G01N2203/0016—Tensile or compressive
    • G01N2203/0017—Tensile
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/0058—Kind of property studied
    • G01N2203/006—Crack, flaws, fracture or rupture
    • G01N2203/0062—Crack or flaws
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/0058—Kind of property studied
    • G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
    • G01N2203/0073—Fatigue
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/0058—Kind of property studied
    • G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
    • G01N2203/0075—Strain-stress relations or elastic constants
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
    • G01N2203/02—Details not specific for a particular testing method
    • G01N2203/06—Indicating or recording means; Sensing means
    • G01N2203/0617—Electrical or magnetic indicating, recording or sensing means
    • G01N2203/0623—Electrical or magnetic indicating, recording or sensing means using piezoelectric gauges

Definitions

  • the invention relates to a device for determining loads on fiber composite components according to the preamble of claim 1 and its manufacturing method according to the preamble of claim 9 and a sensor element for the device according to the preamble of claim 11.
  • fiber composite materials In vehicle and aircraft construction, more and more components made of fiber composite materials are used. These fiber composite materials preferably consist of glass, carbon or aramid fibers, which are made up of fiber layers and are connected to one another by polymeric materials. The components are generally manufactured by lainating the synthetic resin-impregnated fiber layers under pressure and heat in a press mold. These composite materials are usually lighter than comparable metal structural parts and have a high level of rigidity and strength and are therefore preferably used in aircraft construction.
  • the precise documentation of the operational loads is of great interest in order to be able to demonstrate the remaining lifespan of the structure as realistically as possible.
  • the permissible operating times for each structure can be optimally used economically.
  • the maintenance and service intervals and, on the other hand, the remaining service life can be adapted to the conditions that have actually occurred during operation, so that the structure can be operated in an economically optimal manner.
  • damage to the material can occur in the case of lightweight structures as a result of high loads or excessive manufacturing tolerances, such as cavities or fiber components. This damage can considerably weaken the mechanical rigidity and the strength of the components. In the case of aircraft in particular, such components are also exposed to the risk of impact damage from birds and pieces of ice during operation. These loads can 'lead, which are not visible from the outside and constitute a safety hazard to the aforementioned damage within the composites. In order to be able to determine such damage, it is known to recognize it during the regular maintenance work by means of non-destructive test methods such as X-ray or ultrasound tests.
  • a device for determining impact damage to fiber composite components is known.
  • a large number of distributed piezoelectric film pieces are fastened on a surface side of the body components, which are usually only a few millimeters thick, and are led to an electronic monitoring device via an electrical connection.
  • a capacitive charge change occurs in the nearby piezo pickup elements, which is essentially proportional to the impact pressure.
  • This change in charge is then recorded in a monitoring device and can be displayed in accordance with the impact pressure and location relevant to the damage in order to immediately initiate a targeted damage investigation. With such a monitoring device, however, only excessive impact stresses can be determined, which can lead to delamination.
  • the reflection grating can be illuminated with a laser light beam and its Radiation intensity can be detected in a specific direction of reflection. If the surface of the material changes due to stretching or compression, the diffraction angle and thus the radiation intensity in the detected directions also change. Such a radiation intensity is then measured by optoelectronic position detectors and can be displayed as a value of the surface stretch.
  • Such monitoring of the material surfaces is only possible where this surface can be irradiated with laser light and whose radiation intensity can be detected at a certain distance from the surface. In particular, if the surfaces are also provided with other protective or insulation layers that do not follow the stretch, such monitoring or strain analysis cannot be carried out.
  • strain gauges would have to be renewed after every test attempt or every exposure to surface strains that are susceptible to damage, which requires a considerable cost-intensive effort, particularly in the case of multi-point measurements.
  • Material analysis measurements are then no longer evaluated in the upper damage-prone area, so that even an inadequate analysis result can thus be achieved. It is conceivable to produce special strain gauges from wire measuring grids for such surface tension measurements, which also withstand larger strain ranges on composite fiber surfaces, but which would be uneconomical for multi-point measurements for component analysis or for monitoring large aircraft parts.
  • the invention is therefore based on the object of providing a device for measuring material stresses on fiber composite materials and suitable, inexpensive transducer components which are particularly suitable for multi-point measurements or for large-area monitoring of such components.
  • Strain gauges and methods for their production are known from EP 0 667 514 B1. These basically consist of a commercially available photolithographically produced measuring grid which is vapor-deposited on a carrier film and is additionally covered with a protective layer. For connection, this measuring grid has flat soldering surfaces which represent the beginning and the end of the measuring grid. Connection wires are soldered on for wiring and fed to the intended connection parts for connection. Such a strain gauge can basically only be applied to the surface of a strain gage, since otherwise subsequent wiring is no longer possible. Prior wiring would also be unrealistic, as economical manual Habung a large number of connecting wires in the known manufacturing processes of composite materials is hardly possible.
  • the invention has the advantage that, by integrating the strain gauges near the neutral fiber of the composite materials, very flat, almost commercially available foil measuring grids can be used, which are not destroyed by the material loads even at high surface tensions of the composite materials. This also enables cost-effective multi-point measurements on composite materials, which can be used both for analysis of the material components as well as for load monitoring and for permanent monitoring of large-area components, preferably of aircraft body components.
  • the invention has the advantage that, by integrating the strain gauges, they can be used at the factory in the manufacture of the composite components.
  • the sensor elements are also protected against external damage during component assembly, maintenance and operation.
  • the flat foil measuring grids of the strain gauges allow them to be inserted between the individual composite layers in a space-saving manner, which advantageously means that the matrix structure of the components is basically not weakened and, in addition, a non-positive connection between the transducer elements and the composite materials relevant to expansion can be achieved. Since such a connection also takes place on both sides, only slight hysteresis effects occur in the measuring operation, so that high measuring accuracies can be achieved.
  • the transducer elements according to the invention have the advantage that almost all types of loads on fiber composite materials can be determined inexpensively during operation with commercially available film measuring grids.
  • the connection pins provided at the same time provide an advantageous integration Possibility achieved by which a subsequent wiring via plug connections is made possible.
  • the design according to the invention with the connection pins provided permits a high degree of automation in the integrated composite material production, since no manufacturing technology has to be taken into account in connection wires to be led out and nevertheless a subsequent rapid connection possibility is available.
  • FIG. 2 a strain gauge for integration into a fiber composite part
  • 3 a side view of a strain gauge for integration into a fiber composite part with an enlarged section of a connecting pin
  • Fig. 4 a strain gauge with a fixed connection stamp in two mold halves
  • 5 an integration process of a strain gauge into a fiber composite part within a workpiece shape
  • FIG. 6 another preferred embodiment of the device with several integrated measuring points.
  • the fiber composite component 1 of the drawing shows a detail of a device for determining an elongation or for monitoring and for load monitoring on a fiber composite component 1 with film strain gauges 3 integrated in the fiber layers 2 with a connected evaluation device 4.
  • the fiber composite component 1 is shown only in part from a fiber composite material consisting of only two layers 2, between which the strain gauge 3 is arranged.
  • Such fiber composite materials 1 usually consist of several layers, preferably made of glass, carbon or aramid fiber. These are usually placed on top of each other and soaked in a polymer material and are thus firmly connected to each other. Depending on the desired strength requirements, fiber layers are placed on top of each other and oriented in the direction of force and tension.
  • Such fiber composite material components can usually be formed as thin shaped bodies or sheets in thicknesses from 1 to 50 mm with rib reinforcement or in sandwich construction in complex shapes. These are preferably used in the aviation and automotive industries as light, dimensionally stable structural components that are largely independent of aging and corrosion-resistant and are used as an alternative to common metallic materials.
  • the recording of the operating loads is of great interest in order to be able to demonstrate the life of the structure as realistically as possible. With this procedure, the permissible operating times for each structure can be optimally used economically.
  • the frequency and the level of the structural deformations are primarily recorded and documented by the evaluation device 4.
  • the device can be used to detect damage in such components at an early stage which cannot be recognized from the outside and which represents a potential hazard.
  • Fiber breaks, matrix failure, delamination or debonding damage can all occur inside the composite materials, all of which can be determined by their elongation behavior.
  • life tests and strength analyzes are carried out, in which the components are loaded in such a targeted manner that fatigue fractures and damage-related strains occur in order to be able to determine the permissible purposes.
  • surface strains occur that cannot be carried out with conventional film strain gauges, since the elongation capacity of conventional measuring grids is exceeded at these high strains.
  • the invention is based on the knowledge that the foil measuring grids are largely integrated into the so-called neutral fiber, approximately in the middle of the material thickness, in the composite material 1, at which the bending stresses due to expansion are lowest, particularly in the case of damage-prone loads. Furthermore, with this integration, a double-sided connection of the strain gauges 3 with the composite material 1 is possible, which in particular minimizes the hysteresis effect, so that very precise measurements, operating load determination and monitoring can be carried out. For this purpose, a large number of such strain gauges 3 are already integrated in the factory in the manufacture of the composite materials 1, in particular for monitoring large aircraft components, so that the strain gauges 3 are placed at predetermined intervals so that almost all types of damage can be identified at an early stage. This can significantly reduce the risk of plane crashes. When monitoring or examining such components, the distances between the strain gauges 3 to be used can differ depending on the load relevance of the components and can be optimally distributed according to empirical investigations or load calculations.
  • Such a monitoring device is shown schematically and in sections in FIG. 1 of the drawing, in which all strain gauges 3 arranged on component 1 are attached an electronic evaluation device 4 for monitoring and load monitoring are connected.
  • the same arrangement basically also results in an examination device in which the components 1 are subjected to a damage-prone load in order to analyze the load limits or the damage-prone construction requirements.
  • the two devices differ only in their evaluation, an electronic evaluation device being provided in the examination device, which takes into account in particular the predetermined loads during the determined elongation, while the load monitoring and monitoring device only from the determined elongation values for the service life or for one Damage or a damage-prone burden closes.
  • the strain gauge 3 shown in FIG. 1 of the drawing essentially consists of a measuring grid 5, which is applied to a carrier layer 6, as is shown in more detail in FIG. 2 of the drawing.
  • the carrier material 6 is electrically insulating and temperature-resistant, a polymeric material such as polyimide being preferably used.
  • the outer surface of the carrier material 6 is blasted and activated to improve the adhesion during the later structural integration.
  • the measuring grid 5 is provided on both sides with the carrier material 6, that is to say also covered on the upper side with a carrier layer 7.
  • the measuring grid 5 is electrically conductively connected to two connecting pins 8, which are arranged perpendicular to the measuring grid 5.
  • the connecting pins 8 are preferably soldered to the measuring grid 5 via a contact foot 9.
  • the pins 8 have at the end a wider foot area and preferably a height of approx. 5 to 20 mm.
  • the connecting pins 8 are connected to the measuring grid 5 via a strain relief 10.
  • the strain relief 10 represents an area in which the conductor track is designed as a loop, so that when the strain gauge 3 is stretched, the cross-sectional area of the conductor track and thus its electrical resistance does not change.
  • the special strain gauge 3 consisting of a measuring grid 5 and two carrier layers 6 is shown in side view, in particular the design of the contact pins 8 is shown enlarged in a side view. From this it can be seen that the contact pins 8 are provided with an insulating protective layer 20 in their manufacture, in order to be able to use electrically conductive composite layer materials 1 such. B. carbon fibers to prevent a current flow that falsifies the measured values.
  • This insulating layer 20 is preferably made of a polymeric temperature-resistant material.
  • the embodiments of the strain gauges 3 as sensor elements can also be produced as rosettes.
  • this embodiment of the strain gauges 3 can also be used for other transducer elements that can be integrated in fiber composite materials 1, such as piezo fiber modules.
  • this insulating layer is removed or scraped off by the provided clamping edges of the connecting stamp 11 when it is plugged in, in order to bring it to the electronic evaluation device 4 ' via a cable connection 12 which is to be subsequently produced.
  • the individual strain gauges 3 are first interconnected to form a Wheatstone bridge in order to be able to evaluate the detected strains.
  • the other strain gauges, not shown, in the other fiber composite areas are also connected to the electronic evaluation 4 or monitoring device performed.
  • fixed contact stamps 21 can also be attached to the contact pins, as is shown in the embodiment according to FIG. 4 of the drawing.
  • a recess 14 is provided in one of the two mold halves 13, into which the contact stamp 21 can be inserted.
  • the fixed connecting plunger 21 is now pressed onto the respective contact pin 8 and thus establishes a fixed electrical connection to the latter.
  • This fixed connecting stamp 21 can subsequently be electrically connected to the evaluation device 4 via plug contacts.
  • FIG. 5 of the drawing Another manufacturing method for integrating the strain gauges 3 as sensor elements is shown in FIG. 5 of the drawing.
  • a known pressure or vacuum method is used to manufacture the composite components 1.
  • the fiber layers 2 are successively in a predetermined shape 15 is placed and the sensor elements 3 are placed in between or previously connected to the respective fiber layer 2. It does not matter whether the fiber material 2 is dry or has already been impregnated with resin.
  • the strain gauge 3 is to be inserted into the fiber material 2 so that the connecting pins 8 protrude from the fiber material 2 on one side.
  • a stamp 22 made of a soft, porous material, such as preferably foam, is pressed over the connecting pins 8 under slight pressure.
  • the stamp 22 protects the connection pins 8 during the production of the fiber composite component 1 and thereby also fixes the strain gauges 3. After the production process, the stamp 22 can be removed.
  • the usual auxiliary materials for the production of fiber composite components 1 can be used, such as the tear-off film 16 provided and the suction fabric 17 with the vacuum film 18.
  • FIG. 6 shows a further preferred embodiment of the invention with a plurality of integrated strain gauges 3.
  • Three strain gauges 3 with measuring grids 5 are integrated in different layers at different points in the structure made of fiber composite material 1.
  • FIG. 6 shows the cross section through the structure, which consists of a cover skin and a stiffening rib arranged inwards.
  • the contact pins 8 are used to attach an electrical unit 28 to the inside of the structure, with the aid of which the evaluation device 4 can identify the measuring points.
  • the evaluation device 4 consists of a shielded housing 24 and a current source 25.
  • the measurement signals are amplified with an electrical module 26 and a data processor 22 which processes the current measurement value and stores it in the memory unit 27.
  • the evaluation device 4 is equipped with an internal timer 23, so that the level and frequency of expansion states can be recorded in the structure.
  • the current measured value can be compared with reference signals and thus the exceeding of limit values can be recognized.
  • the stored data can be read out, for example, by the service and the data can be evaluated to prove the remaining service life of the structure.

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Health & Medical Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Biochemistry (AREA)
  • General Health & Medical Sciences (AREA)
  • Immunology (AREA)
  • Pathology (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
  • Reinforced Plastic Materials (AREA)

Abstract

Dispositif permettant de détecter les sollicitations subies par des parties structurales (1) à base de fibres, en particulier des parties structurales de voiture ou d'avion, lesdites parties structurales (1) étant pourvues d'un nombre prédéterminé d'éléments capteurs (3) destinés à détecter des extensions. Les éléments capteurs (3) sont reliés à un dispositif d'évaluation (4) conçu en particulier pour le contrôle et la surveillance des charges ainsi que pour la détection de sollicitations tendant à provoquer des dommages. Ledit dispositif est caractérisé en ce que les éléments capteurs sont conçus sous forme de bandes de mesure d'extension (3). Lesdites bandes de mesure d'extension (3) sont de préférence intégrées dans la partie structurale (1) en composite à base de fibres de manière telle que leurs grilles de mesure (5) sont placées entre les couches de fibres (2) individuelles et sont acheminées en vue de leur connexion hors de la partie structurale (1) en composite à base de fibres via des broches de connexion (8) spéciales. Les bandes de mesure d'extension (3) individuelles peuvent être connectées à l'aide de ces broches de connexion (8) au dispositif d'évaluation concerné (4) via des liaisons câblées flottantes (4).
EP04791066A 2003-10-30 2004-10-29 Dispositif permettant de detecter les sollicitations subies par des parties structurales en composite a base de fibres Withdrawn EP1678474A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10350974.7A DE10350974B4 (de) 2003-10-30 2003-10-30 Aufnehmerelement, Vorrichtung zur Feststellung von Belastungen an Faserverbundwerkstoffbauteilen und Herstellungsverfahren für die Vorrichtung
PCT/EP2004/012310 WO2005043107A2 (fr) 2003-10-30 2004-10-29 Dispositif permettant de detecter les sollicitations subies par des parties structurales en composite a base de fibres

Publications (1)

Publication Number Publication Date
EP1678474A2 true EP1678474A2 (fr) 2006-07-12

Family

ID=34529992

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04791066A Withdrawn EP1678474A2 (fr) 2003-10-30 2004-10-29 Dispositif permettant de detecter les sollicitations subies par des parties structurales en composite a base de fibres

Country Status (4)

Country Link
US (1) US7552644B2 (fr)
EP (1) EP1678474A2 (fr)
DE (1) DE10350974B4 (fr)
WO (1) WO2005043107A2 (fr)

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CN111766146A (zh) * 2020-07-03 2020-10-13 浙江大学 一种固化土材料收缩开裂性能的测试评价方法及装置

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WO2005043107A3 (fr) 2005-10-27

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