Classifications

• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
  • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
  • G01N29/44—Processing the detected response signal, e.g. electronic circuits specially adapted therefor
  • G01N29/4445—Classification of defects
• • 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
  • G01M5/0066—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by exciting or detecting vibration or acceleration
• • 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
  • G01M5/0091—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by using electromagnetic excitation or detection
• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
  • G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
  • G01N29/04—Analysing solids
  • G01N29/12—Analysing solids by measuring frequency or resonance of acoustic waves

Definitions

• the present invention relates to a monitoring assembly for detecting structural defects that may appear in an aircraft nacelle in service. Furthermore, the present invention relates to a monitoring method for detecting structural defects that may appear in an aircraft nacelle in service.
• the present invention finds application in particular in the aeronautical field or in the aerospace field, in particular for performing non-destructive testing of a reactor nacelle structure.
• a monitoring assembly performs nondestructive testing of certain components of an aircraft engine.
• a monitoring assembly comprises a plurality of piezoelectric sensors connected to a computing unit. Piezoelectric sensors can only measure the amplitude of vibration at the outer surface of the component to be monitored. The piezoelectric sensors communicate their measurements to the computing unit, which analyzes these measurements, so as to signal the possible appearance of a structural defect.
• each piezoelectric sensor must be connected by electrically conductive cables, on the one hand, to a power source, and on the other hand, to the computing unit.
• the installation of such a power source and such connections are difficult and expensive to achieve.
• such connections present significant risks of rupture because of vibrations and shocks suffered by the component to be monitored.
• Such a monitoring assembly is therefore unreliable because, in the case of a break, a structural defect may not be detected.
• the adjective “driver” and the verbs “drive”, “connect” and “connect” refer to the conduction of electricity, generally performed by means of a solid conductor.
• the present invention aims to solve, in whole or in part, the problems mentioned above.
• the subject of the invention is a monitoring assembly, for detecting structural defects that may appear in an aircraft nacelle in service, the surveillance assembly being characterized in that it comprises:
• At least one sandwich structure of composite material with at least two distinct layers the structure being adapted to form at least a portion of the aircraft nacelle;
• each sensor being adapted to emit said signals by electromagnetic waves , for example by radiofrequency, each sensor being formed by an electromechanical microsystem (MEMS) comprising means for converting into mechanical energy mechanical energy, such as the energy of a shock or vibration; and
• MEMS electromechanical microsystem
• At least one adapted computing unit :
• a monitoring assembly in accordance with the invention comprises energy-autonomous MEMS sensors that can communicate wirelessly with the computing unit (s), which can (e) analyze the measurements transmitted by each sensor.
• An energy-autonomous sensor is a sensor that can self-power electrical energy.
• the MEMS sensors equipping an assembly according to the invention convert the mechanical energy of shocks or vibrations into electrical energy.
• each of these MEMS sensors comprises an electromechanical microsystem that forms a kind of microalternator adapted to generate the electrical energy which the other elements of the MEMS sensor need to operate.
• each MEMS sensor itself produces the electrical energy that is necessary for its operation.
• the power supply of such a MEMS sensor has a zero environmental impact, because this MEMS sensor produces electrical energy from shocks or vibrations.
• MEMS sensors dispense with wiring electrical wires that were previously required for the piezoelectric sensors used in the prior art.
• the MEMS sensors are arranged to generate signals representative of at least one amplitude and / or frequency of vibrations produced inside the sandwich structure, the MEMS sensors make it possible to monitor the sandwich structure in its thickness. , which is not possible in a prior art monitoring assembly where the sensors are glued or attached to the outer surface of the structure of a part.
• this arrangement of the sensors makes it possible to eliminate faulty gluing problems and false information that might result therefrom. Indeed, in a prior art monitoring set where the sensors are stuck on the outer surface of the structure of a part, it is sometimes difficult to discriminate the signals emitted by a sensor detecting a faulty bonding on the structure by report to signals emitted by a sensor detecting a fault appeared in the structure.
• such a monitoring assembly can be quickly installed on the structure or nacelle to monitor and it can detect the possible appearance of a structural defect, inside the structure of a nacelle.
• such a monitoring set has reliable operation and high service life because the sensors are rugged and wireless.
• the verbs "connect”, “transmit” and their derivatives relate to the transmission of signals by electromagnetic waves, without conducting wire and by means of a direct link or indirect, that is to say, via no, one or more component (s).
• a detection threshold is applied to the module of the current transfer function measured at a resonant frequency.
• a detection threshold is applied to the number and / or the value (s) of the resonance frequency (s) of the current transfer function with respect to the transfer function. nominal.
• Such a frequency detection threshold makes it possible to determine the position of a structural defect in the structure, in particular by exploiting the signals generated by several adjacent sensors forming a kind of network.
• each respective detection threshold is set absolutely, preferably from the nominal transfer function.
• an absolute detection threshold makes it possible to determine the presence of a structural defect on the basis of the signals transmitted by a single sensor, after having, if necessary, made correlations with the neighboring sensors so as to suppress white noises and / or or false information.
• each respective detection threshold is relatively fixed, the computing unit comparing a current transfer function resulting from the signals of a sensor with at least one current transfer function resulting from the signals of at least a separate sensor.
• the monitoring assembly comprises several calculation units, each calculation unit being incorporated into a respective sensor.
• Such calculating units make it possible to transform into normed signals (displacement, vibration and shocks, etc.) the stresses which are generated essentially in displacement. Filtration can also to be carried out beforehand to extract the signal actually corresponding to a structural defect and to overcome the recurrent constraints related to the nominal vibration profile of the aircraft nacelle.
• a monitoring assembly comprises a calculation unit arranged at a distance from the sensors and adapted to receive said signals from each sensor.
• such a calculation unit makes it possible to recover the normalized signals by radio frequency links, which makes it possible to correlate the various data, to authenticate the structural fault and to deduce its location or position. Condensation of this information can then be performed and then transmitted to a soil diagnosis and maintenance tool or to a maintenance unit on board the aircraft.
• a monitoring assembly further comprises transmission members each adapted to receive said signals from a respective sensor and to transmit them to a respective computing unit, the transmission members being formed by radio frequency identification components embedded on the aircraft.
• transmission members facilitate the transmission to a computing unit of the signals emitted by the sensors; such transmission members are already installed on the aircraft, which limits the costs of installation of a monitoring assembly according to the invention.
• condensed information can be transmitted to a maintenance unit on board the aircraft.
• each sensor emits said signals with an intensity greater than the attenuation achieved by the structure.
• Such sensors provide integral transmission of signals to the computing unit.
• each sensor is of passive type and composed of silicon, each sensor preferably comprising mechanical counting means.
• Such a sensor is particularly compact and inexpensive.
• each sensor is integrated or embedded in the structure.
• each sensor is directly integrated into the sandwich structure.
• each sensor may be embedded or embedded in the matrix (generally a resin) of the composite material composing the sandwich structure.
• the MEMS sensors are arranged to generate signals representative of at least one amplitude and / or frequency of vibrations produced inside the sandwich structure, the MEMS sensors make it possible to monitor the sandwich structure in its thickness. , which is not possible in a prior art monitoring assembly where the sensors are glued or attached to the outer surface of the structure of a part.
• this arrangement of the sensors makes it possible to eliminate faulty gluing problems and false information that might result therefrom. Indeed, in a prior art monitoring set where the sensors are stuck on the outer surface of the structure of a part, it is sometimes difficult to discriminate the signals emitted by a sensor detecting a faulty bonding on the structure by report to signals emitted by a sensor detecting a fault appeared in the structure.
• the sensors are distributed at several points of the structure, so as to monitor the major part of the structure.
• the distribution of the sensors makes it possible to cover the entire structure to be monitored.
• a plurality of sensors are arranged to measure vibrations produced between two distinct layers when the aircraft nacelle is in use.
• sensors positioned at the interface between two layers of the structure can detect a possible separation between these two layers.
• the density of the sensors is greater in the regions of the structure which are intended to undergo the most mechanical stresses. Thus, such areas are monitored more securely.
• each MEMS sensor is equipped with an electric micro-accumulator for storing part of the electrical energy produced by this MEMS sensor.
• the autonomy of such MEMS sensors is increased.
• the subject of the present invention is a monitoring method, for detecting structural defects that may appear in an aircraft nacelle in service, at least a portion of the aircraft nacelle being formed by a sandwich structure made of composite material with at least two distinct layers, the monitoring method being characterized in that it comprises the steps of:
• each sensor transmits, by means of each sensor, said signals by electromagnetic waves, for example by radiofrequency, each sensor being formed by an electromechanical microsystem (MEMS) comprising means for converting into mechanical energy a mechanical energy, such as the energy of a shock or vibration; and
• MEMS electromechanical microsystem
• a calculation unit predetermines a nominal transfer function. For this purpose, this calculation unit selects input parameters, including physical parameters, and then develops a standardized mathematical representation or model, the transfer function, which is adapted to the nacelle to be monitored. The computing unit then compares this mathematical representation with thresholds defined according to this same standard, which makes it possible to detect the appearance of structural defects.
• a monitoring method further comprises a step of predetermined, at each sensor, a nominal transfer function in the initial state of the structure before commissioning the aircraft nacelle.
• the monitoring method records a "signature" of the healthy structure, that is to say before the appearance of a structural defect.
• Figure 1 is a schematic perspective view of a portion of an aircraft nacelle associated with a monitoring assembly according to the invention
• Figure 2 is a schematic perspective view of components of the monitoring assembly of Figure 1;
• Figure 3 is a sectional view of a structure according to the mediating plane III in Figure 1;
• FIG. 4 is a view similar to FIG. 3 and illustrating a structural defect in the aircraft nacelle of FIG. 1;
• FIG. 5 is a diagram illustrating an initial step of a monitoring method according to the invention and realizing a signal emitted by the surveillance assembly before the aircraft nacelle of FIG. 1 is put into service;
• FIG. 6 is a diagram similar to FIG. 5 illustrating a subsequent step of the monitoring method according to the invention and realizing a signal emitted by the surveillance assembly after the aircraft nacelle is put into service and the appearance the structural defect illustrated in Figure 4;
• FIG. 7 is a diagram similar to FIG. 6 illustrating another subsequent step of the monitoring method according to the invention and realizing another signal emitted by the monitoring unit after commissioning of the aircraft nacelle and the appearance of the structural defect illustrated in Figure 4.
• FIG. 1 illustrates an aircraft nacelle 1 which forms a tubular housing for a turbojet engine, not shown.
• the aircraft nacelle 1 has the particular function of channeling the air flows generated by the turbojet engine.
• the nacelle 1 is generally located under a wing 2 of the aircraft.
• a mast 3 links the pod 1 to the wing 2.
• the nacelle 1 comprises an upstream section forming an air inlet 4, a median section 5 surrounding a blower not shown, and a downstream section 6 surrounding the turbojet and housing a thrust reversal system not shown.
• the air inlet 4 has the particular function of directing to the turbojet air to supply the blower and internal compressors of the turbojet engine.
• At least a part of the nacelle 1 is formed by a structure 10 made by a composite material sandwich with several distinct layers, two of which bear the references 10.1 and 10.2 in FIG. 3.
• the entry of 4, the middle section 5 and the downstream section 6 each comprise a part of the structure 10.
• the term "structure” generally designates one or more component (s) arranged (s) to confer mechanical strength to the aircraft nacelle.
• the structure 10 is equipped with a part of a monitoring assembly January 1 which operates by non-destructive testing and comprises in particular two sensor belts 12.
• each sensor belt 1 2 is shown in dashed lines in FIG. 1, since it is integrated into the structure 10 without appearing on the external surface of the nacelle 1.
• Each sensor belt 12 comprises a ribbon 13 and several sensors 14. The sensors 14 are distributed at several points of the structure 10, so as to monitor the major part of the structure 1 0.
• Each sensor 14 is formed by an electromechanical microsystem (usually designated by the acronym MEMS) comprising means for converting into mechanical energy mechanical energy, such as the energy of a shock or vibration experienced by the pod 1 in use. .
• MEMS electromechanical microsystem
• Each sensor 14 is of the passive type and comprises preferably mechanical counting means.
• each sensor 14 may be formed by a ChronoMEMS® sensor produced by SilMach.
• the sensors 14 are glued on an outer face of the stratum 10.1 of the structure 1 0, then covered by another layer.
• the sensors 14 are thus integrated inside the structure 10.
• these sensors can be directly integrated or embedded in a layer, for example in the matrix (resin) of a composite material constituting all or part of the structure 10
• the sensors 14 are arranged to generate signals representative of at least one amplitude and / or vibration frequency produced in the structure 10 when the nacelle 1 is in use.
• the distribution and the density of the sensors 14 depend on the type of structural defect to be detected in priority, because each structural defect generates an energy that is specific to it. For example, sensors 14 may be placed near the most mechanically stressed regions, or the sensor density may be increased around these regions.
• Each sensor 14 is adapted to emit these representative signals by electromagnetic waves, for example by radio frequency.
• a sensor 14 comprises, on the one hand, a MEMS-type measuring device, not shown, for generating these representative signals and, on the other hand, a MEMS-type transmitter element, not shown, for transmitting these signals. representative generated by the transmitting organ.
• FIG. 5 illustrates signals representative of the vibrations produced at a given point of the structure 10 which is located near the interface between the layers 10.1 and 10.2. These signals are generated by a sensor 14 said proximal because located near this point.
• FIG. 5 is a diagram showing the variation of a module H (f) or amplitude of a transfer function as a function of the frequency f of the vibrations.
• the curve illustrated in FIG. 5 represents a nominal transfer function, that is to say a predetermined function before putting the nacelle 1 into service, when the structure 10 is free of defects.
• the transfer function or frequency spectrum of these signals has a resonance frequency f0 with an amplitude H0.
• the monitoring unit 11 furthermore comprises a computing unit 15 whose particular function is to analyze these representative signals, in particular their spectra, in order to detect the appearance of a structural defect in the nacelle 1.
• the calculation unit 15 is arranged at a distance from the sensors 14 and is adapted to receive these signals from each sensor 14. For this arrangement, each sensor 14 emits its signals with an intensity greater than the attenuation achieved by the structure 10.
• Figure 4 illustrates a structural defect 10.3 appeared between strata 10.1 and 10.2.
• the structural defect 1 0.3 corresponds here to a local detachment of strata 10.1 and 10.2.
• Several sensors 14 are arranged to measure vibrations produced between strata 10.1 and 10.2 when platform 1 is in use.
• FIG. 6 illustrates signals representative of the vibrations produced at the given point mentioned above. These signals are generated by the proximal sensor 14. The current transfer function resulting from these signals still has the resonance frequency f0 but with an amplitude H 1 which is greater than the amplitude H0.
• the calculation unit 15 is adapted to evaluate the differences existing between the current transfer function (FIG. 6) resulting from the current signals and a predetermined nominal transfer function (FIG. In the example of FIGS. 5 and 6, such a difference corresponds to the difference between the amplitudes H1 and H0.
• the computing unit 15 is adapted to make a comparison between each of said differences and a respective detection threshold.
• a detection threshold HD is applied, in this case on the module of the current transfer function (FIG. 6) measured at a resonance frequency f0.
• the detection threshold HD is set beforehand at a value greater than the amplitude HO, for example at 120% of HO. In other words, the detection threshold HD is fixed absolutely from the nominal transfer function (FIG. 5). The comparison made by the calculation unit 15 establishes that the amplitude H1 is greater than the detection threshold HD.
• the computing unit 15 can signal the presence of the structural defect 10.3 near the aforementioned point.
• the computing unit 15 is adapted to estimate or evaluate the position of the structural defect in the structure 10.
• the scanning frequency by each sensor is set so that the physical phenomenon to be observed is at least greater than twice the physical frequency, to make it possible to easily exploit the sampling.
• the scanning speed is adapted to the scanning frequency.
• FIG. 7 illustrates another comparison made by the calculation unit 15, from the signals generated by another sensor 14: a detection threshold is applied to the number and / or the value of the resonance frequencies f0 and f1 of the current transfer function (fig.7) with respect to the nominal transfer function (fig.5).
• the algorithm and the detection thresholds are determined according to the type of structural defects to be monitored in priority.
• a monitoring method for detecting a structural defect 10.3 that may appear in the nacelle 1 in service comprises the steps:
• the monitoring method may further comprise a step of predetermining, at each sensor 14, a nominal transfer function (FIG. 5) in the initial state of the structure 10 before placing the nacelle 1 into service.
• a nominal transfer function FOG. 5
• the monitoring set comprises a plurality of calculation units, each calculation unit being incorporated into or associated with a respective sensor.
• the monitoring assembly further comprises transmission members each adapted to receive said signals from a respective sensor and to transmit them to a respective computing unit, the transmission members being formed by radio frequency identification components, for example according to the so-called RFID technology, which are already existing and embedded on the aircraft.
• transmission members may be separate components of the sensors, while in the example of the figures, a transmission member is integrated with each respective sensor.
• Each respective detection threshold is set relative rather than absolute.
• the computation unit compares a current transfer function resulting from the signals of a sensor with at least one current transfer function resulting from the signals of at least one separate sensor.

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• Physics & Mathematics (AREA)
• General Physics & Mathematics (AREA)
• Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Immunology (AREA)
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• Life Sciences & Earth Sciences (AREA)
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• Analytical Chemistry (AREA)
• Biochemistry (AREA)
• General Health & Medical Sciences (AREA)
• Pathology (AREA)
• Electromagnetism (AREA)
• Acoustics & Sound (AREA)
• Signal Processing (AREA)
• Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
• Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)

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• 2011
  • 2011-05-02 FR FR1153717A patent/FR2974900B1/fr active Active
• 2012
  • 2012-04-12 WO PCT/FR2012/050799 patent/WO2012150394A1/fr active Application Filing
  • 2012-04-12 EP EP12722407.9A patent/EP2705343A1/de not_active Withdrawn
  • 2012-04-12 CA CA2834757A patent/CA2834757A1/fr not_active Abandoned
  • 2012-04-12 BR BR112013027295A patent/BR112013027295A2/pt not_active IP Right Cessation
  • 2012-04-12 CN CN201280021800.0A patent/CN103534569A/zh active Pending
  • 2012-04-12 RU RU2013152414/28A patent/RU2013152414A/ru not_active Application Discontinuation
• 2013
  • 2013-10-31 US US14/068,722 patent/US20140053649A1/en not_active Abandoned

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