WO2023111793A1 - Système et procédé de surveillance de déplacements de points sur la surface d'une pièce d'aéronef ou d'engin spatial - Google Patents

Système et procédé de surveillance de déplacements de points sur la surface d'une pièce d'aéronef ou d'engin spatial Download PDF

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Publication number
WO2023111793A1
WO2023111793A1 PCT/IB2022/061970 IB2022061970W WO2023111793A1 WO 2023111793 A1 WO2023111793 A1 WO 2023111793A1 IB 2022061970 W IB2022061970 W IB 2022061970W WO 2023111793 A1 WO2023111793 A1 WO 2023111793A1
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WO
WIPO (PCT)
Prior art keywords
reference elements
point
signal representative
points
angular coordinate
Prior art date
Application number
PCT/IB2022/061970
Other languages
English (en)
Inventor
Michele Iannone
Original Assignee
Leonardo S.P.A.
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 Leonardo S.P.A. filed Critical Leonardo S.P.A.
Priority to EP22829604.2A priority Critical patent/EP4367472A1/fr
Publication of WO2023111793A1 publication Critical patent/WO2023111793A1/fr

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Classifications

    • 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
    • G01B11/002—Measuring arrangements characterised by the use of optical techniques for measuring two or more coordinates
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S17/00—Systems using the reflection or reradiation of electromagnetic waves other than radio waves, e.g. lidar systems
    • G01S17/66—Tracking systems using electromagnetic waves other than radio waves

Definitions

  • the present invention relates to a monitoring system for monitoring the displacements of a plurality of points arranged on a surface, in particular on the surface of a part of an aircraft or spacecraft, as well as a related method for determining these displacements, a related part of an aircraft or spacecraft for use in this method, and finally a manufacturing method for producing this part.
  • sensor means to determine displacements of points on a surface is known, and in particular the use of these displacement data for determining the state of deformation and consequently for diagnostic monitoring of the state of structural integrity of a part.
  • monitoring refers to the measurement of certain parameters, typically dimensional parameters, such as, for example, the displacement, at notable points, of an aerospace part aimed at detecting the presence of damage or defects in the part’s structure during its use.
  • notable points may be arranged on an outer surface at extremal positions, or at the median.
  • this part of an aircraft or spacecraft may be a wing cover panel, or a spar, or a wing box rib, or a structural element of an aircraft fuselage, or an aileron element or other movable surface element, or even a compressor or rotor blade or hub, for example in the case of a helicopter.
  • the aim of the diagnostics applied to an aerospace part, or of an aircraft or spacecraft, is to avoid sudden and unexpected failure, damage, and/or breakage of the part or parts thereof. For this reason, constant diagnostics on the parts of an aircraft or spacecraft enable the degree of safety during their use and over their inservice life to be increased. Moreover, diagnostics on parts of an aircraft or spacecraft enable simplified maintenance thereof.
  • diagnostics related to parts of an aircraft or spacecraft involve the use of localized sensor means, such as, for example, strain gauges, connected to optical fibers and applied to or on the surface of the part, so as to be able to determine a state of deformation of the structure at the point where they are applied.
  • localized sensor means such as, for example, strain gauges
  • this type of solution allows strain to be measured only at the point where the sensor is attached.
  • the strain measurement is limited by the physical measurement limits of localized sensor means.
  • the architecture of a measurement system comprising sensor means such as those described above becomes inevitably complex, however, due to the plurality of cables required for both powering and transferring information on the deformation state. The risk of cable breakage during placement and/or during maintenance and/or part replacement is also increased.
  • sensor means such as displacement transducers, or strain gauges, or optical systems such as optical cameras are used to measure the displacement of points on the surface of a part of an aircraft.
  • displacement transducers disadvantages similar to those discussed earlier with regard to strain sensors may be identified, namely the need to have multiple transducers for measuring a plurality of points on the surface, as well as the presence of data and power transmission cables.
  • optical systems comprising cameras, the measurement of the displacement may be carried out only by interference, thus requiring the use of at least two optical cameras arranged in different positions and requiring, moreover, appropriate preparation of the surface to be monitored.
  • the same disadvantages related to the complexity of the monitoring system due to, among other things, the bulk and cost of the system needed for monitoring and power and signal transmission cables are evident.
  • An object of the present invention is, therefore, to provide a system for monitoring point displacements on a surface, in particular on the surface of a part of an aircraft or spacecraft, which does not suffer from the disadvantages of the prior art.
  • a further object of the invention is to provide a method for determining the displacements of points on a surface, in particular on a surface of a part of an aircraft or spacecraft.
  • a further object of the invention is to provide a part of an aircraft or spacecraft for use in such a method, or arranged for it to be monitored by the method for determining displacements according to the invention.
  • a further object of the invention is to provide a manufacturing method for producing such a part.
  • a first aspect of the invention is based on the idea of providing a monitoring system for monitoring the displacements of a plurality of points arranged on a surface, in particular on the surface of a part of an aircraft or spacecraft, where the monitoring system comprises: a plurality of reference elements, adapted to be arranged on the surface, each at a respective point of said plurality of points; a laser telemeter, adapted for: emitting a beam of coherent light, the direction of said beam being adjustable about a first axis according to a first angular coordinate and about a second axis, perpendicular to the first axis, according to a second angular coordinate so that said beam is adapted to scan said surface; whenever said beam is reflected by one of said reference elements, measuring a respective reflection time of said beam and generating, from the respective reflection time, for each of said reference elements, a respective signal representative of the distance of said reference element relative to the laser telemeter; adjusting means adapted for adjusting the direction of said beam emitted by the
  • the reference elements have a reflectance different from the surface.
  • the reference elements comprise metal material on an outer surface thereof.
  • the reference elements are each made as a layer of paint arranged on the surface, preferably of paint comprising metal powder.
  • the reference elements are glued to the surface.
  • the reference elements are joined, or connected with each other by a mesh, preferably a metal mesh.
  • a second aspect of the invention is based on the idea of providing a part of an aircraft or spacecraft comprising a plurality of layers, arranged stacked on each other, wherein an outer layer of said plurality of layers comprises a plurality of reference elements, each reference element being at least partially exposed from an outer surface of the outer layer.
  • the reference elements have a reflectance different with respect to the rest of the surface, at least in their portion partially exposed from the surface.
  • the reference elements are partially embedded within said outer layer.
  • a third aspect of the invention is based on the idea of providing a manufacturing method for producing a part of an aircraft or spacecraft according to the second aspect of the invention, the method comprising the steps of: a) arranging a plurality of layers of composite material, preferably uncured composite material; b) providing, on the plurality of layers of composite material, an outer layer of uncured composite material comprising a plurality of reference elements at least partially exposed from an outer surface of the outer layer; c) having the plurality of layers and the outer layer undergo a curing process in an autoclave with a vacuum bag, according to a specific temperature and pressure cycle, for curing the uncured parts.
  • the step b) comprises the sub-steps of: bl) arranging a plurality of reference elements, preferably a plurality of reference elements joined together by a mesh, on said plurality of layers; b2) partially embedding the plurality of reference elements by providing resin on the plurality of layers so that the reference elements remain at least partially exposed from an outer surface of the outer layer.
  • a fourth aspect of the invention is based on the idea of providing a method for determining the displacements of a plurality of points arranged on a surface, in particular on the surface of a part of an aircraft or spacecraft, comprising the steps of: p) providing a plurality of reference elements on the surface, each one at a respective point of the plurality of points; q) providing a laser telemeter, adapted to emit a beam of coherent light; r) scanning the surface by means of the beam of coherent light emitted by the laser telemeter, by adjusting the direction of the beam about a first axis according to a first angular coordinate and about a second axis according to a second angular coordinate, and, whenever the beam is reflected by one of the reference elements, measuring a respective reflection time of the beam and generating, from the respective reflection time, for each of the reference elements, a respective signal representative of the distance of the reference element from the laser telemeter; s) for each point of the plurality of points,
  • the reflection parameter is the reflection time taken by the beam to travel the distance between the respective reference element and the laser telemeter, or is related to or dependent on that reflection time according to a known function.
  • the reflection parameter is associated with a self-oscillation frequency of the laser telemeter or a system in which it is comprised, or is related to or dependent on said selfoscillation frequency according to a known function.
  • Fig. 1 is a perspective view of a monitoring system according to an embodiment of the first aspect of the invention, in which a part of an aircraft is shown in an initial, or nondeformed, configuration;
  • Fig. 2 is a perspective view of the monitoring system of Fig. 1, in which the part is shown in a final, or deformed configuration, and in which the part of Fig. 1 is also shown in transparency for comparison;
  • Fig. 3 is a partially sectional perspective view of the part according to the second aspect of the invention. Detailed description
  • a monitoring system according to the first aspect of the invention is generally denoted by reference number 10.
  • the monitoring system 10 is adapted to monitor the respective displacements Di, D2, ..., D n of a plurality of points Pi, P2, ..., P n , which are arranged on a surface S, in particular an outer surface S, of a part C of an aircraft or spacecraft, or the i-th displacement Di of each i-th point Pi.
  • displacement D means, as is known to the person skilled in the art, a displacement vector comprising three displacement values in the three directions of space.
  • displacement Di means the i-th vector comprising the three displacement values in the three directions of space relative to the i-th point Pi.
  • the monitoring system 10 essentially comprises a laser telemeter 12, adjusting means 14, a plurality of reference elements 16, and an electronic control unit 18.
  • the reference elements 16 are arranged on the surface S, each at a respective point Pi of said plurality of points Pi, P2, ..., Pn, so that their position substantially corresponds to that of a respective point Pi of said plurality of points Pi, P2, ..., P n . Accordingly, the number of reference elements 16 corresponds to the number n of points Pi, P2, ..., Pn of which the relative displacement vector Di, D2, ..., D n is to be measured. Thus, the reference elements 16 are essentially used to identify the position of the points Pi, P2, ..., P n of which the location is to be determined, and, consequently, to monitor their displacement.
  • the reference elements 16 may be obtained according to a plurality of embodiments.
  • the reference elements 16 have a physical reflection characteristic, preferably reflectance, that is different from the surface S on which they are arranged.
  • the different reflectance may be manifest throughout the spectrum, or it may be present only at particular frequencies or in particular frequency ranges.
  • the frequencies at which the reference elements 16 exhibit a different reflectance relative to the surface S must correspond to the emission frequency or frequencies of a beam 20 (which will be described later).
  • the reference elements 16 may also have additional respective physical characteristics that are different with respect to the surface S.
  • the reference elements 16 may further comprise metal material on one of their outer surfaces 16b, or on a surface intended to receive the beam 20 and reflect it.
  • the reference elements 16 are preferably made of a material different with respect to the part C.
  • the reference elements 16 may be made entirely of metal material while the part C is made of composite material.
  • the reference elements 16 may be made entirely of polymeric material or composite material while the part C is made of metal material.
  • the reference elements 16 may likewise be simply painted on the surface S of the part C.
  • the reference elements 16 are each made in the form of a layer of paint arranged on said surface S, preferably a layer of paint comprising metal powder.
  • the reference elements 16 may be glued or otherwise fixed to the surface S, for example by integrating the reference elements 16 into the manufacturing process of the part C as will be explained later.
  • the reference elements 16 may be joined together by connecting elements, or by a mesh 16a, preferably a metal mesh.
  • the laser telemeter 12 is used to measure the distance to each of the points of the plurality of points Pi, P2, ..., P n .
  • the laser telemeter 12 is adapted to emit a beam 20 of laser light, or of coherent light, directing it toward the surface S on which the points of which the distance is to be measured are arranged, so that said surface S reflects the incident beam 20, measuring its reflection parameter X whenever the beam 20 is reflected by a reference element 16— the position of each reference element 16 corresponding to that of a respective i-th point Pi of said points of the plurality of points Pi, P2, ..., P n and uses this information to derive the measurement of the distance di of each reference element 16, or each point Pi of the plurality of points Pi, P2, P n from the laser telemeter 12.
  • the reflection parameter X may be the reflection time, which is the time it takes for the beam 20 to travel the distance between the point of the plurality of points Pi, P2, ..., P n from which it was reflected and the laser telemeter 12.
  • the laser telemeter 12 emits the beam 20, and an electronic chronometer, preferably built into the laser telemeter 12, measures the time interval between the moment of emission of the beam 20 and the moment of return of the beam 20 reflected from a point of the plurality of points Pi, P2, ..., Pnback to the laser telemeter 12: knowing the speed of light in the air, or in the medium, it is straightforward to calculate the distance traveled by the beam 20 of laser light, by simply multiplying speed by time.
  • the reflection parameter X may relate to the frequency of the beam 20.
  • the principle of operation is not based on the direct measurement of the round-trip time interval of the beam 20 emitted by the laser telemeter 12 and reflected by the surface S, but on the measurement of a self-oscillation frequency of a system in which such a delay is embedded.
  • the practical implementation of such a meter involves the provision of an optical sensor (not shown, known per se) that makes an on-off circuit, and, therefore, interrupts the emission of said beam 20, and turns it on again as soon as it stops receiving the reflected beam 20, and so on in a continuous on-off cycle.
  • the frequency f is easily measured, with high accuracy, by means of known circuits (not shown), and the distance d may then be obtained by a simple calculation according to the formula just described.
  • the reflection parameter X may also not correspond exactly to the frequency f just described but be related to it by a known function. Alternatively, the reflection parameter X may relate to additional physical characteristics of the beam 20. To enable scanning of the entire surface S of the part C, the direction of the beam 20 is orientable, or adjustable by said adjusting means 14.
  • the beam direction 20 is adjustable about a first axis x, according to a first angular coordinate A, thus being able to be oriented in this direction according to a plurality of angular positions defined by first angular coordinates Ai, A2, ..., A n , and is further adjustable about a second axis y, perpendicular to the first axis x, according to a second angular coordinate B, thus being orientable in this direction according to a plurality of angular positions defined by second angular coordinates Bi, B2, ..., B n .
  • the adjusting means 14 may comprise, in an embodiment, a plurality of orientable mirrors (not shown, known per se).
  • these adjusting means 14 may instead comprise a series of hinges or joints adapted to allow rotation of the laser telemeter 12 in its entirety. It is also possible to combine the adjusting means 14 as just described or as obtainable in a manner obvious per se to the person skilled in the art.
  • the laser telemeter 12 may also be arranged in a sliding manner on a track, or on a dedicated sliding means, so that it may translate along a straight direction, for example by translating along a direction perpendicular to the first axis x and the second axis y, or by translating along a curved line such as, for example, a circular arc.
  • Several methods may be used to determine the time at which the beam 20 is reflected by a reference element 16 instead of the surface S. For example, it is possible to check the physical reflection characteristics, such as, for example, the reflectance value, of the reference elements 16 and that of the surface S: if, for example, the reflectance is different, the beam 20, when reflected by a reference element 16, will have different characteristics than when reflected by the surface S, and this difference may be detected by sensor means known per se.
  • the physical reflection characteristics such as, for example, the reflectance value
  • the initial position of the reference elements 16 (known) to be provided in advance to the laser telemeter 12, or to the electronic control unit 18, so that each pair of first angular coordinate Ai and the second angular coordinate Bi in which the beam 20 will be reflected by a reference element 16 and not by the surface S is known.
  • Other embodiments are known to the person skilled in the art.
  • the direction of the beam 20 may be adjusted according to the first angular coordinate A and according to the second angular coordinate B, or the beam 20 may scan the surface S.
  • the beam 20 will be reflected from time to time by a different reference element 16 of the plurality of reference elements 16 — the position of each reference element 16 corresponding to that of a point Pi of the plurality of points Pi, P2, ..., P n .
  • the laser telemeter 12 may measure the respective reflection parameter Xi (as mentioned above, for example an i-th reflection time) of the beam 20 relative to the i-th reference element 16 — and thus to the i-th point Pi of the plurality of points Pi, P2, ..., P n . From this parameter Xi, the laser telemeter 12 is adapted to generate a respective signal representative of the distance di of the i-th reference element 16 relative to the laser telemeter 12 and therefore representative of the distance of the i-th point Pi of the plurality of points Pi, P2, ..., P n . In this way, the monitoring system 10 is adapted to determine the distance of each point Pi of the plurality of points Pi, P2, ..., P n from the laser telemeter 12.
  • Xi an i-th reflection time
  • the monitoring system 10 also comprises an electronic control unit 18.
  • the electronic control unit 18 is configured, or programmed, essentially to determine a respective displacement Di of each point Pi of the plurality of points Pi, P2, ..., P n from a respective initial position Li to a respective end position Li'.
  • the electronic control unit 18 is configured, or programmed, for: receiving, from the laser telemeter, 12 the signals representative of the distance di of each reference element 16 relative to the laser telemeter 12, i.e., indirectly also representative of the distance of each point Pi of the plurality of points Pi, P2, ..., P n relative to the laser telemeter 12, since each i-th reference element 16 is arranged at an i-th point Pi; for each point Pi of the plurality of points Pi, P2, ..., P n , associating with the respective signal representative of the distance di of said reference element 16 relative to the laser telemeter 12 a respective signal representative of the value of the first angular coordinate Ai and a respective signal representative of the value of the second angular coordinate Bi of the direction of said beam 20 at the time of measurement of the respective reflection parameter Xi of said beam 20 by the laser telemeter 12; in this way, it is possible to construct a data set in which, each point Pi of the plurality of points Pi, P2,
  • initial position Li means, as is known to the person skilled in the art, a set of coordinates comprising three position values in the three directions of space.
  • initial position Li means the i-th set of coordinates comprising the three initial position values in the three directions of space relative to the i-th point Pi.
  • end position Li' means, as is known to the person skilled in the art, a set of coordinates comprising three position values in the three directions of space.
  • end position Li' denotes the i-th coordinate set comprising the three values of end position in the three directions of space relative to the i-th point Pi. It is, obviously, not necessary for the coordinates relating to the initial position Li or the end position Li' of each point Pi to be expressed in the form of Cartesian coordinates; rather it is, obviously, also possible to use polar coordinates or other types of reference systems.
  • the initial position Li of each point Pi may have been generated, received, pre-determined in a known manner, or even stored in the electronic control unit 18, for example, as a result of an initial measurement made again by the same laser telemeter 12.
  • the respective displacement Di may then be determined in a manner that is obvious per se to the person skilled in the art. This determination step may be carried out either by the electronic control unit 18 or by an additional dedicated processor. It is considered obvious that for the person skilled in the art, the determination of the displacement Di and the end position Li' may be done hand in hand and one as a consequence of the other.
  • the application of the monitoring system 10 according to the first aspect of the invention enables the method for determining displacements according to the fourth aspect of the invention to be carried out.
  • FIG. 1 and 2 By comparing Fig. 1 and 2, in which the same measurement is made on a part C shown in a non-deformed configuration in Fig. 1 and in a deformed configuration in Fig. 2 (and in the same Fig. 2, the part C in a non-deformed configuration is also visible in transparency), the application of the monitoring system 10 may be seen.
  • the same point Pi is associated with the value of the first related angular coordinate Ai and the value of the second related angular coordinate Bi, as well as the distance di between point Pi, or equivalently the reference element 16 associated with point Pi, and the laser telemeter 12.
  • a second point P2 is associated with the value of the first related angular coordinate A2 and the value of the second related angular coordinate B2, as well as the distance d2 between point P2, or equivalently the reference element 16 associated with the point P2, and the laser telemeter 12.
  • These three values in a fixed reference system, for example, on the laser telemeter 12, define an end position L2' of the point P2 and are sufficient — the initial position L2 of point P2 being known — to calculate the displacement D2 and the end position L2', and so on for all the n i-th points Pi of the plurality of points Pi, P2, ..., Pn.
  • part C of an aircraft or spacecraft in particular suitable for use in a method according to the fourth aspect of the invention or contextually with a monitoring system 10 according to the first aspect of the invention.
  • the part C according to the second aspect of the invention may be, for example and non-limitingly, a wing cover panel, or a spar, or a wing box rib, or a structural element of an aircraft fuselage, or an aileron or other moving surface element, or even a compressor or rotor blade or hub, for example in the case of a helicopter.
  • the part C comprises a plurality of layers 22 which are arranged on each other, or stacked on each other, or piled on each other.
  • one of said layers 22, in particular an outer layer 24, or a layer on which no additional layer is stacked comprises the plurality of reference elements 16.
  • the reference elements 16 may be as described above with reference to the first aspect of the invention and may have all or some of the optional features described therein. Moreover, the reference elements 16 are arranged so that they are each partially exposed from the outer surface S of the outer layer 24 of the part C. In particular, as is clearly visible from Fig. 3, the reference elements may, for example, be in the shape of a hemisphere and be partially embedded in the outer layer 24 so that a small portion of each reference element 16 protrudes, or is partially exposed from the outer surface S of the outer layer 24. Preferably, the reference elements 16 are partially embedded within the outer layer 24, or they are made in one piece with the outer layer 24 so that they protrude or are partially exposed from the outer surface S of the outer layer 24 of the part C.
  • the reference elements 16 are partially exposed from the surface S (or they are visible from the outside) but do not protrude from the surface S. Even more preferably, the reference elements 16 are partially exposed from the surface S (or, they are visible from the outside) but do not protrude from the surface S or form a recess with respect to the surface S.
  • the reference elements 16 exhibit special physical reflection characteristics, such as a different reflectance with respect to the surface S, this characteristic is present or must be expressed, or is more present, at least in the portion of reference elements 16 that is partially exposed from the surface S.
  • the layers 22 of the part C may be made jointly by co-curing, or copolymerization, or by co-adhesion or by co-bonding, as better described below.
  • a third aspect of the invention concerns a method for manufacturing for making the part C according to the second aspect of the invention.
  • the method for manufacturing the part C comprises the step of arranging the plurality of layers 22 of composite material, preferably including an epoxy resin matrix stage and a fibrous material reinforcement stage, such as carbon or glass fibers.
  • the layers 22 may be supplied and arranged all together, using a pre-impregnated composite base material, or laminated on each other until a plurality of layers 22 arranged on each other is made.
  • the outer layer 24 is provided, which is made of unpolymerized, or uncured, composite material and comprising the plurality of reference elements 16 as described above, and arranged to be partially exposed from the outer surface S of the outer layer 24.
  • the method comprises two sub-steps.
  • the first step provides for placing the reference elements 16 on said plurality of layers 22, or on the last of said layers 22, preferably supporting them.
  • the reference elements 16 may be linked together by connecting elements or be joined together by a mesh 16a, such as a metal mesh, so in this case this step involves resting the mesh 16a on the last of the layers 22.
  • the second step provides for the provision of resin, or resin injection, on the layers 22 so as to embed, or submerge or cover, the reference elements 16 only partially while still leaving each one partially exposed.
  • a vacuum bag was arranged around the layers 22 beforehand.
  • all layers 22 including the outer layer 24 undergo a curing process in an autoclave with a vacuum bag, according to a specific temperature and pressure cycle, for curing the uncured parts.
  • the polymerization process, or curing is known per se and provides for the application of a specific temperature and pressure cycle and will not be described further.
  • this process makes use of bagging materials necessary for dressing the part C, for example with bagging materials typical of the curing process in an autoclave with a vacuum bag, such as a high-temperature nylon film, a nylon or polyester surface ventilation fabric, a high-temperature separator film.
  • both the layers 22 and the outer layer 24 are of unpolymerized, or uncured composite material, whereby a so-called co-curing or co-polymerization process is implemented.
  • the layers 22 are supplied in already cured material, whereby a so-called co-bonding or co-adhesion procedure is implemented, which may additionally involve placing a layer of adhesive material between the layers 22 and the outer layer 24 prior to the autoclave curing step. It is also possible for additional layers of adhesive material to be placed between the layers 22.
  • a monitoring system and a method for determining displacements according to the present invention provide several advantages.
  • the displacements of a plurality of points on the surface of a part of an aircraft or spacecraft may be determined even from a distance, or there is no need for wiring or other bulky devices.
  • monitoring system it is possible to carry out monitoring and necessary measurements both on the ground or in the laboratory, with the part mounted in a fixed position, and in flight, with the part mounted on the aircraft or spacecraft; in which case, point displacements are determined in relation to a reference system centered on a point of the laser telemeter.
  • the part and the method for manufacturing the part it is possible to provide a part specifically adapted for use with the monitoring system and the method for determining displacements.

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Length Measuring Devices By Optical Means (AREA)
  • Length Measuring Devices With Unspecified Measuring Means (AREA)

Abstract

L'invention concerne un système (10) de surveillance de déplacements (di) de points (Pi) sur une surface (S) d'une pièce (C) d'aéronef ou d'engin spatial, comprenant : des éléments de référence (16) disposés en un point respectif (Pi) ; un télémètre laser (12) destiné à émettre un faisceau (20) pour balayer la surface (S) ; et lorsque le faisceau (20) est réfléchi par un élément de référence (16), pour mesurer un paramètre de réflexion respectif (Xi) et pour générer un signal représentant la distance (di) entre l'élément de référence (16) et le télémètre laser (12) ; une unité de commande électronique (18) configurée pour déterminer, pour chaque point (Pi), une position finale (Li') par traitement d'un signal représentant la position initiale (Li), du signal représentant la distance (di) de l'élément de référence (16) et de signaux représentant la valeur d'une première coordonnée angulaire (A0) et d'une deuxième coordonnée angulaire (Bi) indiquant la direction du faisceau (20).
PCT/IB2022/061970 2021-12-16 2022-12-09 Système et procédé de surveillance de déplacements de points sur la surface d'une pièce d'aéronef ou d'engin spatial WO2023111793A1 (fr)

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EP22829604.2A EP4367472A1 (fr) 2021-12-16 2022-12-09 Système et procédé de surveillance de déplacements de points sur la surface d'une pièce d'aéronef ou d'engin spatial

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IT102021000031499 2021-12-16
IT102021000031499A IT202100031499A1 (it) 2021-12-16 2021-12-16 Sistema e metodo per il monitoraggio degli spostamenti di punti su una superficie di componente di velivolo o di veicolo spaziale

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Citations (5)

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EP3351897A1 (fr) * 2017-01-24 2018-07-25 General Electric Company Procédés de fabrication d'un composant avec un indicateur de contrainte intégral

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