EP3612423A1 - Procédé et système de surveillance de l'état d'un frein d'un aéronef - Google Patents

Procédé et système de surveillance de l'état d'un frein d'un aéronef

Info

Publication number
EP3612423A1
EP3612423A1 EP18721270.9A EP18721270A EP3612423A1 EP 3612423 A1 EP3612423 A1 EP 3612423A1 EP 18721270 A EP18721270 A EP 18721270A EP 3612423 A1 EP3612423 A1 EP 3612423A1
Authority
EP
European Patent Office
Prior art keywords
temperature
brake
aircraft
landing
time
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Withdrawn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
EP18721270.9A
Other languages
German (de)
English (en)
Inventor
Stefan SPIESMACHER
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.)
Lufthansa Technik AG
Original Assignee
Lufthansa Technik AG
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 Lufthansa Technik AG filed Critical Lufthansa Technik AG
Publication of EP3612423A1 publication Critical patent/EP3612423A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
    • B60T17/00—Component parts, details, or accessories of power brake systems not covered by groups B60T8/00, B60T13/00 or B60T15/00, or presenting other characteristic features
    • B60T17/18—Safety devices; Monitoring
    • B60T17/22—Devices for monitoring or checking brake systems; Signal devices
    • B60T17/221—Procedure or apparatus for checking or keeping in a correct functioning condition of brake systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/42—Arrangement or adaptation of brakes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D66/00—Arrangements for monitoring working conditions, e.g. wear, temperature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D66/00—Arrangements for monitoring working conditions, e.g. wear, temperature
    • F16D66/02—Apparatus for indicating wear
    • F16D66/021—Apparatus for indicating wear using electrical detection or indication means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
    • B60T2250/00—Monitoring, detecting, estimating vehicle conditions
    • B60T2250/02—Vehicle mass
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
    • B60T2250/00—Monitoring, detecting, estimating vehicle conditions
    • B60T2250/04—Vehicle reference speed; Vehicle body speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D66/00—Arrangements for monitoring working conditions, e.g. wear, temperature
    • F16D2066/001—Temperature

Definitions

  • the invention concerns a method and system for monitoring state ⁇ a mechanical brake an aircraft.
  • Mechanical brakes of an aircraft often have brake disks made of carbon or carbon material.
  • Carbon brake discs are not only subject to mechanical wear during operation, but can also be affected by oxidation in their condition and their functionality. Such oxidation is promoted for example by Pistenenteisungsmittel.
  • the invention has for its object to provide a method and system of the type mentioned, which allow an efficient condition monitoring and allow early detection of oxidation damage.
  • the method according to the invention comprises the following steps: a. Measurement of the temperature T of the brake to at least one
  • Time t2 during landing after start a mechanical braking operation b. Comparing the measured temperature T with a determined standard temperature for the brake to the at least a time t2 during a landing operation after loading ⁇ beginning of a mechanical braking process, c. Recognizing a state of wear of the brake by ei ⁇ nes exceeding the measured temperature T on the standard temperature over a predetermined amount addition.
  • the method according to the invention comprises the following steps: a. Measuring the temperature T of the brake at least two times ti, t2, where ti is a time during the landing operation before the start of a mechanical braking operation and t2 a time during the landing operation after the beginning of a mechanical braking operation, b. Determination of a temperature increase ⁇ , c. Recognizing a state of wear of the brake by ei ⁇ nes exceeding the temperature rise ⁇ over a standard temperature rise above a predetermined level addition.
  • a mechanical brake converts kinetic energy into thermal energy through friction. It is in the context of the invention preferably a disc brake, the discs are preferably ⁇ carbon discs.
  • the brakes can be used on aircraft of all kinds, preferably on aircraft with wings that have to land at certain minimum speeds.
  • the temperature T of the brake is measured by a suitable sensor. It is the absolute temperature at one or more times during landing and mechanical braking.
  • a temperature measurement can also take place before the start of the mechanical braking process. The temperature measurement is carried out with egg ⁇ nem or more sensors, the or detect the temperature of the brake discs or the temperature of a component whose temperature sufficiently correlated with the brake discs.
  • the standard temperature or the standard temperature increase is the temperature or temperature difference that usually prevails or prevails at the relevant time or over a corresponding period of time on an intact brake of the aircraft.
  • the determination of these values can be carried out within the scope of the invention in a manner which will be explained in more detail below.
  • the detection of a state of wear is carried out according to the invention either on the basis of the absolute measured temperature value or the temperature rise.
  • the invention has recognized that both a conventional mechanical wear of a brake as also a particular affected by oxidation Integ ⁇ capacity of carbon brake discs is expressed in that there is a higher temperature or a higher temperature increase during braking after landing.
  • the invention relates to the detection or determination ⁇ make the oxidation state, ie, an oxidation caused by impairment of the structural integrity that is difficult to detect by conventional tests, in particular visual inspection, not o-.
  • the invention can also be used to detect mechanical wear, simpler methods will often be available for this purpose, for example known visual inspections, thickness measurements or sensory detection of the position of the actuators of the brake.
  • the invention has also recognized that, surprisingly, the state of wear and, in particular, the oxidation state can be derived with sufficient accuracy from the temperature or the temperature increase as the sole measured variable. According to the invention can thus be provided that only the temperature or the temperature rise (over time) is used to determine the Oxidati ⁇ onsschreib.
  • the invention also allows detection of a critical mechanical condition of a brake that does not expressed in a visible reduction in the thickness of a carbon brake discs, but in an oxidation-related impairment of their structural integrity. Under certain circumstances, such an oxidation can not be detected during a visual inspection, but in a subsequent braking operation it can lead to complete destruction of the pane while losing its braking effect and consequential damage through its fragments.
  • the temperature T is monitored at short time intervals (preferably at intervals of 5 s or less, more preferably at intervals of 1 s or less) or completely continuously over a time interval t, which covers the detection of a representative temperature profile of a brake over a part a braking operation after a landing, the full braking or possibly also allows a cooling phase after braking.
  • This time interval t preferably begins with touchdown of the aircraft on landing and has a duration of 20 to 1,000 s, preferably 50 to 600 s, more preferably 100 to 200 s. For example, a time ⁇ duration of 160 s may be provided.
  • the invention is particularly suitable for detecting changes in state of the oxidation state of a brake over a relatively long period of time.
  • the standard temperature and / or the standard temperature rise can be determined by forming a preferably moving average of n landing operations, where n is preferably Zvi ⁇ 's 10 and 50, more preferably 15 and 30 is, n may be for example 20 ,
  • n is preferably Zvi ⁇ 's 10 and 50, more preferably 15 and 30 is, n may be for example 20 .
  • the formation of such a moving average in particular allows, by changing the operating conditions of the aircraft caused by changes in temperature or the temperature ⁇ turan Stieg (for example, high or low outside temperatures, common landings in short distances or rea ⁇ accordingly long cooling-down in the middle and long distance operation) to equalize and thus increase the validity of the measurements he ⁇ .
  • the temperature ⁇ turan Stieg for example, high or low outside temperatures, common landings in short distances or rea ⁇ accordingly long cooling-down in the middle and long distance operation
  • Standard temperature and / or the standard temperature rise can be determined with the help of a comparison of the values of several mechanical brakes of an aircraft. Such an average over several brakes makes it easier to distinguish a change in state of brake discs, which is damaged for example by oxidation of Temperatur Managere ⁇ ments by changing operating conditions.
  • the temperature T and / or the temperature rise ⁇ are normalized, ie certain operating conditions during a landing are taken into account for the conversion of the measured values to so-called normal values. It is particularly preferred that the normalization he ⁇ follows with the aid of the kinetic energy of the aircraft at the time of touchdown, as this kinetic energy significantly determines the thermal load of the brakes. In order to determine the kinetic energy, the mass and velocity of the aircraft at the time of the aircraft are preferred.
  • the invention further provides a system for carrying out the method according to the invention.
  • This system includes: a. at least one temperature sensor associated with the brake, b. a storage device for measured temperatures
  • a comparison device for the comparison of the measured temperatures and / or temperature curves with corresponding standard values.
  • further relevant data can be stored in the memory device, for example parameters which are required for calculating a normalization of the temperatures.
  • This can be, for example, land mass and / or landing speed.
  • the system components storage device and comparison device can be arranged spatially separated from the aircraft, for example, on the ground within the scope of the invention.
  • ⁇ sem means for data communication is provided with the aircraft.
  • the device for data communication may comprise wireless communication, line-based communication (for example while the aircraft is parked at the gate) or communication via data carrier.
  • a communication by data carrier can for example have a suitable storage means on board the driving ⁇ stuff that is brought manually to a land-based storage means and read there.
  • system components storage device and comparison device can be assigned according to the invention to a plurality of aircraft.
  • a device is provided for determining standard temperature and / or standard temperature rise, which operates with the aid of a comparison of the values of a plurality of brakes of a plurality of aircraft of the same or similar type.
  • Fig. 1 shows schematically a disc brake for an aircraft.
  • the brake has five carbon stator disks 1 and four carbon rotor disks 2.
  • the temperature is detected by a temperature sensor 3 and output as a voltage signal.
  • the method according to the invention was carried out on Deutsche Lucashansa's Airbus A321, which was used in intra-European short-haul traffic.
  • the kinetic energy at the time of Aufset ⁇ zen to such a reference landing is about 204,000 kJ.
  • FIG. 2 shows exemplary normalized temperature data for a landing recorded over a period of 900 seconds from the time of touchdown. The following measured values are included in the graphic:
  • Fig. 3 shows normalized temperature data for a landing recorded over a period of 150 seconds from the time of touchdown.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Braking Arrangements (AREA)

Abstract

L'objet de l'invention est un procédé de surveillance de l'état d'un frein mécanique d'un aéronef, caractérisé par les étapes suivantes : a. la mesure de la température T du frein à au moins un instant t2 pendant une procédure d'atterrissage une fois un processus de freinage mécanique entamé, b. la comparaison de la température T mesurée à une température standard déterminée pour le frein à l'instant ou aux instants t2 pendant un processus d'atterrissage une fois un processus de freinage mécanique entamé, c. le repérage d'un état d'usure du frein sur la base d'un dépassement de la température T mesurée au-delà de la température standard d'une mesure prédéfinie. La présente invention porte également sur un système permettant la mise en œuvre du procédé.
EP18721270.9A 2017-04-19 2018-04-18 Procédé et système de surveillance de l'état d'un frein d'un aéronef Withdrawn EP3612423A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017206593.1A DE102017206593A1 (de) 2017-04-19 2017-04-19 Verfahren und System zur Zustandsüberwachung einer Bremse eines Luftfahrzeugs
PCT/DE2018/100367 WO2018192629A1 (fr) 2017-04-19 2018-04-18 Procédé et système de surveillance de l'état d'un frein d'un aéronef

Publications (1)

Publication Number Publication Date
EP3612423A1 true EP3612423A1 (fr) 2020-02-26

Family

ID=62091627

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18721270.9A Withdrawn EP3612423A1 (fr) 2017-04-19 2018-04-18 Procédé et système de surveillance de l'état d'un frein d'un aéronef

Country Status (5)

Country Link
US (1) US20200189553A1 (fr)
EP (1) EP3612423A1 (fr)
CN (1) CN110678370A (fr)
DE (1) DE102017206593A1 (fr)
WO (1) WO2018192629A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3597496B1 (fr) * 2018-07-16 2020-09-02 Safran Landing Systems UK Limited Ensemble de train d'atterrissage d'aeronef
IT202100005636A1 (it) * 2021-03-10 2022-09-10 Itt Italia Srl Metodo di stima dell'usura di un elemento del freno di un veicolo
CN115163708B (zh) * 2022-06-21 2023-07-25 东风柳州汽车有限公司 一种制动盘温度的实时检测方法和装置

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5651431A (en) * 1996-01-26 1997-07-29 Eaton Corporation Method of brake lining wear detection using temperature sensing
US5668529A (en) * 1996-06-05 1997-09-16 Eaton Corporation Method of statistically determining brake lining wear using temperature sensing
CN1199682A (zh) * 1997-05-16 1998-11-25 日野自动车工业株式会社 制动器警报装置
US5939978A (en) * 1997-07-17 1999-08-17 Meritor Heavy Vehicle Systems, Llc Temperature sensing brake lining wear indicator
CN100372715C (zh) * 2000-08-04 2008-03-05 都恩罗普空间技术有限公司 制动器状态监测***和方法
US6659233B2 (en) * 2001-12-04 2003-12-09 Hydro-Aire, Inc. System and method for aircraft braking system usage monitoring
DE10259529B4 (de) * 2002-12-19 2005-02-17 Daimlerchrysler Ag Verfahren zur Ermittlung eines Bremsenzustands
GB0500305D0 (en) * 2005-01-08 2005-02-16 Dunlop Aerospace Ltd Electrically actuated aircraft brakes
US8548652B2 (en) * 2006-01-31 2013-10-01 Hydro-Aire, Inc., Subsidiary Of Crane Co. System for reducing carbon brake wear
CN103244585B (zh) * 2012-02-09 2016-01-13 阿文美驰技术有限责任公司 对车辆的制动***进行控制的方法
DE102012210149A1 (de) * 2012-06-15 2013-12-19 Lufthansa Technik Ag Verfahren und Passagierinformationssystem zur Bereitstellung von Fluginformationsdaten
US9096204B2 (en) * 2012-12-12 2015-08-04 Goodrich Corporation System and method for determining an adaptive turnaround threshold
US9242739B2 (en) * 2013-11-22 2016-01-26 The Boeing Company Methods to monitor components of an aircraft landing system

Also Published As

Publication number Publication date
CN110678370A (zh) 2020-01-10
US20200189553A1 (en) 2020-06-18
WO2018192629A1 (fr) 2018-10-25
DE102017206593A1 (de) 2018-10-25

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