WO2002004290A1 - Systeme pour detecter un depot sur une surface - Google Patents

Systeme pour detecter un depot sur une surface Download PDF

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Publication number
WO2002004290A1
WO2002004290A1 PCT/NL2001/000532 NL0100532W WO0204290A1 WO 2002004290 A1 WO2002004290 A1 WO 2002004290A1 NL 0100532 W NL0100532 W NL 0100532W WO 0204290 A1 WO0204290 A1 WO 0204290A1
Authority
WO
WIPO (PCT)
Prior art keywords
heat source
temperature
characteristic
meander
thermopile
Prior art date
Application number
PCT/NL2001/000532
Other languages
English (en)
Inventor
Huibert Blokland
Original Assignee
Nederlandse Organisatie Voor Toegepast-Natuurwetenschappelijk Onderzoek Tno
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 Nederlandse Organisatie Voor Toegepast-Natuurwetenschappelijk Onderzoek Tno filed Critical Nederlandse Organisatie Voor Toegepast-Natuurwetenschappelijk Onderzoek Tno
Priority to AU2001272855A priority Critical patent/AU2001272855A1/en
Publication of WO2002004290A1 publication Critical patent/WO2002004290A1/fr

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Classifications

    • G—PHYSICS
    • G08—SIGNALLING
    • G08B—SIGNALLING OR CALLING SYSTEMS; ORDER TELEGRAPHS; ALARM SYSTEMS
    • G08B19/00—Alarms responsive to two or more different undesired or abnormal conditions, e.g. burglary and fire, abnormal temperature and abnormal rate of flow
    • G08B19/02—Alarm responsive to formation or anticipated formation of ice
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/20—Means for detecting icing or initiating de-icing

Definitions

  • the invention relates to the detection of a specific deposit or boundary layer on a surface, in particular, but not exclusively, of ice and/or de-icing fluid on a surface of an aircraft.
  • Other examples relate to ice deposits on high voltage cables and on roads, rime formation in refrigerated display cabinets or the interior contamination of pipelines.
  • Ice formation occurs relatively frequently when the aircraft takes off, in the case of sleet, snowfall and the like. However, ice can also deposit on the aircraft when landing. The wings and fuselage then still have a low temperature as a consequence of the low temperatures at cruising height. If the aircraft comes into a humid environment in such a situation, rapid ice growth can take place on the wings.
  • the wings are usually sprayed with a de-icing fluid prior to take-off.
  • a de-icing fluid is effective for only a limited period because this fluid drips off the wings.
  • the aircraft is therefore protected against ice formation for only a limited period. This has to be determined on the basis of a table; if the aircraft has to wait for too long before take-off, a fresh treatment with de-icing fluid is needed, or the pilot has to use his own judgement to decide whether ice deposition has occurred.
  • the tables also often prescribe a treatment with de-icing fluid unnecessarily frequently. The consequence is that unnecessary additional costs are incurred and that the environment is additionally polluted.
  • the engines are also susceptible to ice deposition close to the intake.
  • a system of this type for the detection of a boundary layer on a surface, comprising: at least one heat source for locally heating said surface, at least one sensor for measuring at least one temperature characteristic of said surface that is related to the change in temperature that occurs over said surface as a consequence of the local heating thereof, memory means for readily accessible storage of a set of related data concerning the at least one temperature characteristic and at least one characteristic of the boundary layer, comparison means for comparing the at least one temperature characteristic and the at least one boundary layer characteristic, as well as for determining said boundary layer characteristic on the basis of the measured temperature characteristic.
  • the system for the detection of a deposit or boundary layer is based on the change in temperature that is established over the surface after a certain part thereof has been heated.
  • Said change in temperature is highly dependent on the presence and the nature of the deposit.
  • a measurement can also be used for determination of the nature and the thickness of the deposit.
  • a distinction can be made between, on the one hand, a de-icing agent on the wings and, on the other hand, a layer of ice.
  • the abovementioned temperature characteristic on which the determination of the boundary layer is based can be, for example, the magnitude of the temperature drop over a predetermined distance from the heat source.
  • the heat source can be in the form of a straight line, the temperature difference being measured between at least one pair of measurement points on a line that is transverse with respect to the heat source.
  • a temperature characteristic can be used that is the temperature response measured over time in the case of a change in the power supplied to the heat source.
  • the heat source can be meander shaped, the temperature difference being measured between at least two pairs of measurement points, each pair of which is, in each case, on a line that is transverse with respect to the heat source, which pairs are offset with respect to one another in the longitudinal direction of the heat source.
  • Measurement of the temperature drop over a predetermined distance and measurement of the temperature response in the case of a change in the power supplied take place sequentially.
  • the change in the power supplied can be implemented in various ways and, for example, can be in the shape of a sine wave, block-shaped or the like.
  • a straight line heat source can be provided in combination with a meander-shaped heat source and a thermopile.
  • the meander-shaped heat source extends along the straight line heat source and the one set of measurement points of the thermocouples of the thermopile is located in the troughs of the meander- shaped heat source which are oriented away from the straight line heat source.
  • the heat sources and the thermopile can be accommodated on a foil and an insulation layer and covered by a hard coating. The system is consequently very flat and can be fitted on or in the surface to be monitored without significantly influencing the aerodynamic characteristics thereof. It is also not necessary to make an opening passing through the skin of the wing, which is a major advantage from the standpoint of the integrity of the construction.
  • Fig. 1 shows a plan view of a sensor according to the invention.
  • Fig. 2 shows a cross-section.
  • the sensor shown in Fig. 1 comprises a first heating device 1 in the form of a single line and having connection poles 2, 3.
  • the second, meander-shaped heating device 4 has connection poles 5, 6.
  • thermopile 7 with connection poles 8, 9 is also provided.
  • the thermopile 7 has pairs of measurement points 10, 11, each pair of which is determined by a thermocouple 12. These thermocouples 12 are connected in series to the thermopile 7.
  • the one set of measurement points 10 of the thermocouples 12 of the thermopile 7 is located in the troughs of the meander-shaped heat source 4.
  • the meander-shaped heat source 4 is constructed with two meander-shaped sections 13, 14, but one or more sections are also possible.
  • the straight line heat source 1 is arranged between these two meander-shaped sections 13, 14.
  • the senor is mounted on a substrate 15, for example an aircraft wing.
  • An insulation layer 16 for example 1 mm thick, is applied thereto, with, on top of this, foil 17 on which the sensors and the heat sources are located.
  • the top layer 18 consists of a hard coating layer. The dimensions are so chosen that an ice layer thickness of at most 5 mm can be measured; this is determined, inter alia, by the dimensions of the meander-shaped heat source 4.
  • This substrate 15 acts as a heat sink.
  • thermopile By means of the thermopile the difference in temperature is measured between one of the heat sources 1, 4 (that is to say close to the points 10) and a location that is not affected by the heat source 1, 4 (that is to say close to the points 11).

Landscapes

  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Investigating Or Analyzing Materials Using Thermal Means (AREA)
  • Length Measuring Devices With Unspecified Measuring Means (AREA)

Abstract

Cette invention se rapporte à un système de détection servant à détecter une couche limite sur une surface, ce système comprenant: au moins une source de chaleur (1, 4) servant à chauffer localement ladite surface, au moins un capteur (12) servant à mesurer au moins une caractéristique de température de ladite surface qui est relative à la variation de température se produisant sur cette surface à la suite de son échauffement local, une mémoire permettant la mémorisation rapidement accessible d'un ensemble de données relatives concernant la ou les caractéristiques de température et la ou les caractéristiques de la couche limite, un comparateur servant à comparer la ou les caractéristiques de température et la ou les caractéristiques de la couche limite, et à déterminer la caractéristique de la couche limite sur la base de la caractéristique de température ainsi mesurée.
PCT/NL2001/000532 2000-07-12 2001-07-12 Systeme pour detecter un depot sur une surface WO2002004290A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU2001272855A AU2001272855A1 (en) 2000-07-12 2001-07-12 System for detecting a deposit on a surface

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
NL1015691A NL1015691C2 (nl) 2000-07-12 2000-07-12 Systeem voor het detecteren van afzetting op een oppervlak.
NL1015691 2000-07-12

Publications (1)

Publication Number Publication Date
WO2002004290A1 true WO2002004290A1 (fr) 2002-01-17

Family

ID=19771726

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/NL2001/000532 WO2002004290A1 (fr) 2000-07-12 2001-07-12 Systeme pour detecter un depot sur une surface

Country Status (3)

Country Link
AU (1) AU2001272855A1 (fr)
NL (1) NL1015691C2 (fr)
WO (1) WO2002004290A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010072334A1 (fr) * 2008-12-22 2010-07-01 Ksb Aktiengesellschaft Dispositif et procédé de détection de dépôts
GB2483530A (en) * 2010-09-10 2012-03-14 Ultra Electronics Ltd Aircraft ice detection system
WO2013034083A1 (fr) * 2011-09-06 2013-03-14 中国商用飞机有限责任公司 Détecteur de condition de gel
US9678029B2 (en) 2014-08-22 2017-06-13 Honeywell International Inc. Oxidation catalyst detector for aircraft components
US10295489B2 (en) 2016-09-12 2019-05-21 Ecolab Usa Inc. Deposit monitor
US10816285B2 (en) 2017-02-24 2020-10-27 Ecolab Usa Inc. Thermoelectric deposit monitor
US11953458B2 (en) 2019-03-14 2024-04-09 Ecolab Usa Inc. Systems and methods utilizing sensor surface functionalization

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4928254A (en) * 1988-04-28 1990-05-22 Knudsen Arne K Laser flash thermal conductivity apparatus and method
US4996493A (en) * 1989-08-21 1991-02-26 Monat Seymour M Instantaneous ice detection system
DE4030401A1 (de) * 1990-03-19 1991-09-26 Kromberg & Schubert Vorrichtung zum messen des fluessigkeitsstandes in einem behaelter, insbesondere im kraftstofftank eines fahrzeugs
WO1994008233A1 (fr) * 1992-10-07 1994-04-14 Instrumar Limited Dispositif et procede permettant d'identifier et de quantifier des substances sous forme de couches
US5418522A (en) * 1990-10-15 1995-05-23 Tekmar Angewandte Elektronik Gmbh System for indicating and signaling the presence of snow and ice
US5474261A (en) * 1993-09-20 1995-12-12 Raton Technology Research, Inc. Ice detection apparatus for transportation safety
US5521584A (en) * 1993-10-13 1996-05-28 Eaton Corporation Apparatus and method for detecting ice
US5730026A (en) * 1995-03-31 1998-03-24 Josef Maatuk Microprocessor-based liquid sensor and ice detector

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4928254A (en) * 1988-04-28 1990-05-22 Knudsen Arne K Laser flash thermal conductivity apparatus and method
US4996493A (en) * 1989-08-21 1991-02-26 Monat Seymour M Instantaneous ice detection system
DE4030401A1 (de) * 1990-03-19 1991-09-26 Kromberg & Schubert Vorrichtung zum messen des fluessigkeitsstandes in einem behaelter, insbesondere im kraftstofftank eines fahrzeugs
US5418522A (en) * 1990-10-15 1995-05-23 Tekmar Angewandte Elektronik Gmbh System for indicating and signaling the presence of snow and ice
WO1994008233A1 (fr) * 1992-10-07 1994-04-14 Instrumar Limited Dispositif et procede permettant d'identifier et de quantifier des substances sous forme de couches
US5474261A (en) * 1993-09-20 1995-12-12 Raton Technology Research, Inc. Ice detection apparatus for transportation safety
US5521584A (en) * 1993-10-13 1996-05-28 Eaton Corporation Apparatus and method for detecting ice
US5730026A (en) * 1995-03-31 1998-03-24 Josef Maatuk Microprocessor-based liquid sensor and ice detector

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010072334A1 (fr) * 2008-12-22 2010-07-01 Ksb Aktiengesellschaft Dispositif et procédé de détection de dépôts
AU2009331941B2 (en) * 2008-12-22 2014-01-09 KSB SE & Co. KGaA Device and method for detecting deposits
US9176044B2 (en) 2008-12-22 2015-11-03 Ksb Aktiengesellschaft Device and method for detecting deposits
GB2483530A (en) * 2010-09-10 2012-03-14 Ultra Electronics Ltd Aircraft ice detection system
US8517601B2 (en) 2010-09-10 2013-08-27 Ultra Electronics Limited Ice detection system and method
WO2013034083A1 (fr) * 2011-09-06 2013-03-14 中国商用飞机有限责任公司 Détecteur de condition de gel
US9678029B2 (en) 2014-08-22 2017-06-13 Honeywell International Inc. Oxidation catalyst detector for aircraft components
US10295489B2 (en) 2016-09-12 2019-05-21 Ecolab Usa Inc. Deposit monitor
US10816490B2 (en) 2016-09-12 2020-10-27 Ecolab Usa Inc. Deposit monitor
US10816285B2 (en) 2017-02-24 2020-10-27 Ecolab Usa Inc. Thermoelectric deposit monitor
US11953458B2 (en) 2019-03-14 2024-04-09 Ecolab Usa Inc. Systems and methods utilizing sensor surface functionalization

Also Published As

Publication number Publication date
AU2001272855A1 (en) 2002-01-21
NL1015691C2 (nl) 2002-01-15

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