EP2461296A1 - Überwachungsvorrichtung einer luftfahrttechnischen Ausrüstung - Google Patents

Überwachungsvorrichtung einer luftfahrttechnischen Ausrüstung Download PDF

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Publication number
EP2461296A1
EP2461296A1 EP10193525A EP10193525A EP2461296A1 EP 2461296 A1 EP2461296 A1 EP 2461296A1 EP 10193525 A EP10193525 A EP 10193525A EP 10193525 A EP10193525 A EP 10193525A EP 2461296 A1 EP2461296 A1 EP 2461296A1
Authority
EP
European Patent Office
Prior art keywords
equipment
monitoring device
sensor
parameter
monitoring
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.)
Ceased
Application number
EP10193525A
Other languages
English (en)
French (fr)
Inventor
Albert Cornet
Nicolas Doucet
Philippe Langohr
Matthieu Droeller
Nicolas Raimarckers
Fabrice Haudry
Michel Saint-Mard
Rémy Leblond
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.)
Safran Aero Boosters SA
Original Assignee
Techspace Aero SA
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 Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP10193525A priority Critical patent/EP2461296A1/de
Priority to CA2756599A priority patent/CA2756599A1/fr
Priority to US13/307,177 priority patent/US20120143436A1/en
Publication of EP2461296A1 publication Critical patent/EP2461296A1/de
Ceased legal-status Critical Current

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    • G—PHYSICS
    • G07—CHECKING-DEVICES
    • G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
    • G07C5/00—Registering or indicating the working of vehicles
    • G07C5/08—Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle or waiting time
    • G07C5/0841—Registering performance data
    • G07C5/085—Registering performance data using electronic data carriers

Definitions

  • the invention relates to a device for monitoring an aeronautical equipment, more particularly to a device for monitoring equipment intended to be placed on the equipment in question.
  • the invention also relates to avionic equipment provided with said monitoring device.
  • Aeronautical equipment includes many equipment likely to fail and therefore requiring specific maintenance.
  • the maintenance frequencies of these different devices vary according to various usage parameters. It is therefore useful to be able to measure these parameters of life and use of equipment in order to ensure optimal maintenance and guaranteeing the safety of people.
  • the patent document US 2003/0083794 A1 discloses an avionic equipment diagnostic system, essentially comprising a series of sensors disposed on or near the avionic equipment and able to measure different operating parameters of the equipment in question, and a common receiver able to communicate with the sensors and to receive the data relating to the operating parameters measured by the sensors, with a view to diagnosis and maintenance of the equipment.
  • the sensors include an electrical power source, a microcontroller type circuit board and a transmitter / receiver.
  • the receiver includes essentially a transmitter / receiver capable of communicating with the sensors, a display, control means and a microcontroller.
  • the sensors can be of the passive type, ie working without a source of clean energy. They are then powered electrically by the energy received from the interrogation signal transmitted by the receiver.
  • the diagnostic system disclosed in this document is particularly suitable for performing spot checks of various equipment such as the state of operation of these equipment before takeoff.
  • the monitoring provided by the sensors is essentially limited to the operating state of the equipment in order to detect malfunctions.
  • the parameters usually monitored include vibrations, pressures, liquid levels, etc. This teaching does not really provide a function of monitoring equipment operating conditions in order to monitor their history throughout their lives.
  • the patent document WO 2005/111949 A 1 discloses a device for monitoring the operation of avionic equipment.
  • the device is disposed near the equipment and comprises a processor, a memory, a connection interface with different sensors arranged at various locations of the equipment and a communication interface with the outside.
  • the device is intended to collect the data of the various sensors during a test procedure and to compare the measurements obtained in real time during the operational operation of the aircraft with these so-called reference test measurements, in order to be able to determine the need for maintenance of said equipment.
  • the example equipment subject to monitoring is an air turbine starter and the operating parameters that are measured include torque, speed, vibration, bending deformation and torsional deformation.
  • the memory of the monitoring device stores the data of the different measuring points or equipment, these data being measured in real time, in its memory.
  • the monitoring device is in principle an accessory external to the equipment but can also be integrated into the equipment in question.
  • the device is equipped with a memory, the fact remains that it is essentially intended to process the measured data in real time and to produce a maintenance report or analysis and also a logistical analysis of the parts needed for the measurement. maintenance in question. This teaching does not address the issue of memory capacity to preserve a history of the equipment.
  • the patent document FR 2 909 792 A1 addresses the issue of maintenance of avionics equipment and discloses the presence of a monitoring device with memory and embedded on a LRU type equipment (Line Replaceable Unit), focusing on the centralization of surveillance, without really detailing more the device itself.
  • LRU type equipment Line Replaceable Unit
  • equipment history (especially LRUs) is manually traced and the level of detail is left to the discretion of the company. It is therefore often difficult to trace the life of equipment that may have been placed on different aircraft / engines. And so during a maintenance, it is difficult for the company to judge the relevance of returning this equipment for inspection and repair. It is even more difficult for the maintenance company to know the history of the equipment requiring the complete disassembly of the equipment before it can decide on the parts to be supplied to repair it and thus preventing any optimization of inventory management. The recording of equipment life parameters will allow a coordinated management of maintenance and a reduction of cost.
  • the recording of equipment life parameters will also optimize the design of future generations of equipment.
  • the incomplete information on the experience of the equipment does not allow its designer to draw all the fruit of feedback from the maintenance.
  • the recording of the parameters of the life of the equipment will make it possible to fill statistical databases and thus to quantify the real reliability rates as well as to identify and quantify the causes of the repairs to be made on the equipment and to to improve the design of future generations.
  • the object of the invention is to propose a device for monitoring an aeronautical equipment that overcomes at least one of the drawbacks mentioned above, more particularly a device for monitoring an aeronautical equipment that makes it possible to trace the history of the equipment over a period of time. given or a given number of cycles and especially during the lifetime (typically 50,000 hours or 50,000 cycles), and particularly suitable to be integrated with said equipment.
  • the energy source is preferentially electric. It is preferably of sufficient capacity for the operation of the device.
  • the automatic activation of the monitoring device, its operation and / or its deactivation take place in the absence of electrical connection with the outside of the device.
  • the parameter or parameters representative of the operation of the equipment comprise the temperature and / or the vibrations. Indeed, these parameters are particularly representative of the operation equipment, and more particularly the level of load of their operation.
  • the device comprises a vibration sensor serving as a setting parameter of the device.
  • the device will be activated when the equipment is subjected to a vibration level corresponding to operation under a load beyond a predetermined level.
  • the vibration triggering threshold may be at the measured amplitude, at the frequency level or at a combination of both.
  • the vibration sensor is configured to detect at least one determined frequency range. This is interesting when this frequency range corresponds for example to a so-called idle or "idle" regime of the equipment, as this makes it possible to determine each operating cycle.
  • the device comprises a temperature sensor serving as a setting parameter of the device.
  • the energy source comprises a thermo-generator.
  • a thermo-generator allows the device to be autonomous. It will then be powered in particular when it is likely to be put into operation.
  • thermo-generator ensures the function of the device based on a temperature parameter. This is a simple and effective configuration of the device. The fact of reaching a given temperature level at the location of the device on the equipment will then provide the necessary power supply and commissioning.
  • the device comprises a vibration sensor ensuring the function of the device on the basis of a vibration parameter.
  • the energy source further comprises a piezoelectric generator.
  • the device comprises connectors intended to allow a transfer of information stored in the memory to an external device.
  • the device is passive from a wave emission point of view. This measurement is particularly interesting insofar as the device is intended to remain on the equipment throughout its life.
  • the passivity of the device will make it possible to avoid possible problems of electromagnetic compatibility with the environment of the equipment, on the aircraft and / or on the ground.
  • the device comprises a support housing the components of said device.
  • the support comprises an apparent metallic part intended to receive an identification plate of the device and / or the equipment.
  • the identification is present directly on the support, for example by etching.
  • the support comprises a mounting face on the equipment, said face being metallic and directly supporting the sensor capable of measuring an operating parameter of said equipment, said sensor being selected from temperature and vibration sensors.
  • the metal support ensures optimal transmission of vibrations and heat.
  • the invention also relates to avionic equipment comprising a device as defined above.
  • the avionic equipment has at least one natural frequency
  • the monitoring device comprises a vibration sensor capable of detecting a frequency range comprising said natural frequency of said equipment.
  • the sensor will thus be configured to detect an operating cycle of the equipment when a sufficient amplitude is reached.
  • the figure 1 is a simplified illustration of a dual axial flow turbomachine and provided with lubrication equipment subject to surveillance according to the invention.
  • the figure 2 is a schematic illustration of the lubrication equipment of the turbomachine of the figure 1 and provided with a monitoring device according to the invention.
  • the figure 3 is an enlarged view of the monitoring device of the figure 2 and according to the invention.
  • the figure 4 is an illustration of the architecture of the monitoring device according to the invention.
  • the figure 1 illustrates a double-flow turbomachine type aircraft engine 2 well known to those skilled in the art.
  • This aircraft engine 2 is provided with a series of equipment including a lubrication equipment 4.
  • the aircraft engine comprises a rotor rotating about the axis XX 'by means of bearings undergoing loads more or less important and requiring lubrication and possibly also cooling.
  • the lubrication equipment 4 typically comprises an oil reservoir 8 and an equipment oil management unit 10 comprising, inter alia, a pump 12, means for filtering and regulating the outlet pressure, a connector oil outlet, an oil return connector and an air / oil separator.
  • an equipment oil management unit 10 comprising, inter alia, a pump 12, means for filtering and regulating the outlet pressure, a connector oil outlet, an oil return connector and an air / oil separator.
  • a monitoring device 6 according to the invention is disposed on an outer wall of the equipment, more particularly a wall of the oil management unit of the equipment.
  • This wall makes it possible to collect a good number of information relating to the operation of the equipment, such as in particular its operating temperature and the vibrations which reign there.
  • the pump and the other components are subject to operating speeds and variable temperature and vibration constraints.
  • the figure 3 is an enlarged view of the monitoring device 6. It is generally parallelepiped shape and very small, typically of the order of one or more centimeters of side and a few millimeters thick. It preferably comprises a support 20 serving as housing or housing to its components. The support comprises an outer surface 16 covered mostly or completely by an identification plate 18 of the equipment. In this way, the monitoring device is intimately associated with the equipment and identifiable by the identification of the equipment.
  • FIG 4 An example of an architecture of the monitoring device 6 figures 2 and 3 is illustrated at the figure 4 . It comprises inside the support 20 at least one sensor 28 able to measure an operating parameter of the equipment. This or these sensors 28 can take various forms and be of various origins. Typically, the device comprises a vibration sensor and / or a temperature sensor. Indeed, these two parameters are among the most representative parameters of the operation of many aeronautical equipment.
  • the monitoring device 6 also comprises a microcontroller 22, a memory 24, an electrical energy generator 26 and a connection interface 30.
  • the electrical energy source 26 makes it possible to power the device, in particular the microcontroller 22.
  • memory 24 makes it possible to store the data relating to the parameters measured by the sensor or sensors 28.
  • the source of electrical energy may be of the thermo-generator type.
  • a thermo-generator uses the thermoelectric effect, which is a physical phenomenon present in certain materials that binds the flow of heat through the electric current flowing through them. This effect gives the possibility of converting heat flow into electric current and allows applications of electricity generation from lost heat sources. Conversion systems using the thermoelectric effect have however, low yields, whether in electricity generation or refrigeration. However, this low efficiency makes it possible to power very advantageously a monitoring device which is a very small consumer of electrical energy.
  • thermo-generator module may consist of "couples" electrically connected.
  • Each of the pairs consists of a p-type semiconductor material and an n-type semiconductor material. These two materials are joined by a conductive material whose thermoelectric power is assumed to be zero.
  • the two branches (p and n) of the pair and all the other couples constituting the module are connected in series electrically and in parallel thermally. This arrangement optimizes the heat flow through the module and its electrical resistance. Charge carriers (electrons and holes) move from the cold source to the hot source (in the thermodynamic sense) in the two branches of each pair. The heat flow will then cause a displacement of the charge carriers and therefore the appearance of an electric current.
  • piezoelectric generator is based on piezoelectricity which is the property that some bodies have to be electrically polarized under the action of a mechanical stress and reciprocally to deform when an electric field is applied to them.
  • the vibrations of the equipment will make it possible to compress and decompress one or more elements made of piezoelectric material and, consequently, to generate, for example by means of an integrated smoothing circuit, a current source. electrical capable of supplying or co-powering the thermoelectric generator with the monitoring device.
  • the device is configured to be activated automatically only in the presence of one or more parameters representative of the operation of the equipment, such as a minimum temperature or a predetermined vibration level.
  • This commissioning or on-demand function also makes it possible to determine the length of the cycles and the cumulative hours of service of the equipment.
  • the decommissioning is carried out inversely and automatically: when the parameter or parameters representative of the operation of the equipment exceed or pass under a predetermined value or values, and during a predefined period of time, the device will be automatically switched off. service.
  • the device will be turned on when the equipment is subjected to a vibration level corresponding to operation at a level of load beyond a predetermined level.
  • the vibration trigger threshold may be at the level of the measured amplitude, at the frequency level or a combination of both.
  • the vibration sensor is configured to detect at least one frequency range corresponding for example to a so-called idle speed or "idle" of the equipment, in order to determine each operating cycle.
  • the equipment may have one or more natural frequencies when it is mounted on the aircraft and in operation. These natural frequencies may be intrinsic to the equipment or result from vibrations from other equipment and transmitted to the equipment in question.
  • the electric generator that will ensure the setting in function or service and the decommissioning of the device.
  • Such a device will then be of extremely simple construction since it is the power up which will start the measurement of the operating parameter (s) and the power off which will stop the measurement.
  • the measurements will intrinsically contain, in addition to information relating to the operating costs of the equipment, information relating to the length of the operating cycles and thus the number of cumulative hours of operation of the equipment.
  • the generator whether based on heat, vibration or any other base, can thus be calibrated to deliver a voltage or an output current sufficient for the commissioning of the monitoring device only when the equipment is in operation. .

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
EP10193525A 2010-12-02 2010-12-02 Überwachungsvorrichtung einer luftfahrttechnischen Ausrüstung Ceased EP2461296A1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP10193525A EP2461296A1 (de) 2010-12-02 2010-12-02 Überwachungsvorrichtung einer luftfahrttechnischen Ausrüstung
CA2756599A CA2756599A1 (fr) 2010-12-02 2011-10-21 Dispositif de surveillance d'un equipement aeronautique
US13/307,177 US20120143436A1 (en) 2010-12-02 2011-11-30 Monitoring Device for Aircraft Equipment

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10193525A EP2461296A1 (de) 2010-12-02 2010-12-02 Überwachungsvorrichtung einer luftfahrttechnischen Ausrüstung

Publications (1)

Publication Number Publication Date
EP2461296A1 true EP2461296A1 (de) 2012-06-06

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EP10193525A Ceased EP2461296A1 (de) 2010-12-02 2010-12-02 Überwachungsvorrichtung einer luftfahrttechnischen Ausrüstung

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US (1) US20120143436A1 (de)
EP (1) EP2461296A1 (de)
CA (1) CA2756599A1 (de)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012047792A2 (en) * 2010-10-04 2012-04-12 Arizona Board Of Regents, A Body Corporate Of The State Of Arizona Acting For And On Behalf Of Arizona State University Device and method for breath analysis using acoustic resonance flow rate
EP2573338B1 (de) * 2011-09-20 2017-07-19 Safran Aero Boosters SA Überfüllungskontrolle eines Schmiersystems für einen Flugzeugmotor
FR3016710B1 (fr) * 2014-01-20 2016-01-08 Jean-Hugues Pettre Procede de prediction d'une anomalie de fonctionnement des equipements d'un aeronef ou d'une flotte d'aeronefs
US9916701B2 (en) * 2014-09-10 2018-03-13 The Boeing Company Vehicle auditing and control of maintenance and diagnosis for vehicle systems
US9507982B2 (en) * 2015-01-06 2016-11-29 Honeywell International Inc. Line replaceable unit health nodes and methods for determining maintenance actions relating to line replaceable units
US9568912B2 (en) 2015-06-15 2017-02-14 Honeywell International Inc. Aircraft prognostic systems and methods for determining adaptive time between overhaul for line replaceable units
DE102016107303A1 (de) * 2016-04-20 2017-10-26 Rolls-Royce Deutschland Ltd & Co Kg Energiewandlungssystem einer Turbomaschine, Getriebe oder Lagergehäuse einer Turbomaschine und Turbomaschine
US10544738B2 (en) 2017-10-30 2020-01-28 Honeywell International Inc. Energy scavenging health monitors for aircraft and other vehicles
US11661862B2 (en) 2020-06-12 2023-05-30 Unison Industries, Llc Oil life of oil in a gearbox of an air turbine starter

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030083794A1 (en) 2001-10-27 2003-05-01 Juergen Halm System and method for diagnosing aircraft components for maintenance purposes
WO2005111949A1 (en) 2003-10-01 2005-11-24 Honeywell International Inc. Aircraft accessory monitor
US20070114422A1 (en) * 2005-11-23 2007-05-24 Lockheed Martin Corporation System to monitor the health of a structure, sensor nodes, program product, and related methods
US20070144396A1 (en) * 2005-10-21 2007-06-28 Hamel Michael J Structural damage detection and analysis system
US20080036617A1 (en) * 2005-09-09 2008-02-14 Arms Steven W Energy harvesting, wireless structural health monitoring system
WO2008045030A2 (en) * 2005-09-20 2008-04-17 The Boeing Company System and methods for tracking aircraft components
FR2909792A1 (fr) 2006-12-08 2008-06-13 Thales Sa Systeme de maintenance centralisee d'equipements electroniques embarques
US20090216398A1 (en) * 2008-02-27 2009-08-27 Simmonds Precision Products, Inc. Vehicle health and usage monitoring system and method

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8596135B2 (en) * 2006-12-07 2013-12-03 Technion Research and Dvelopment Foundation Ltd. System and method for monitoring health of structural joints

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030083794A1 (en) 2001-10-27 2003-05-01 Juergen Halm System and method for diagnosing aircraft components for maintenance purposes
WO2005111949A1 (en) 2003-10-01 2005-11-24 Honeywell International Inc. Aircraft accessory monitor
US20080036617A1 (en) * 2005-09-09 2008-02-14 Arms Steven W Energy harvesting, wireless structural health monitoring system
WO2008045030A2 (en) * 2005-09-20 2008-04-17 The Boeing Company System and methods for tracking aircraft components
US20070144396A1 (en) * 2005-10-21 2007-06-28 Hamel Michael J Structural damage detection and analysis system
US20070114422A1 (en) * 2005-11-23 2007-05-24 Lockheed Martin Corporation System to monitor the health of a structure, sensor nodes, program product, and related methods
FR2909792A1 (fr) 2006-12-08 2008-06-13 Thales Sa Systeme de maintenance centralisee d'equipements electroniques embarques
US20090216398A1 (en) * 2008-02-27 2009-08-27 Simmonds Precision Products, Inc. Vehicle health and usage monitoring system and method

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CA2756599A1 (fr) 2012-06-02
US20120143436A1 (en) 2012-06-07

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