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WO2001011582A1 - Detecteur de glace optique - Google Patents

Detecteur de glace optique Download PDF

Info

Publication number
WO2001011582A1
WO2001011582A1 PCT/US2000/021837 US0021837W WO0111582A1 WO 2001011582 A1 WO2001011582 A1 WO 2001011582A1 US 0021837 W US0021837 W US 0021837W WO 0111582 A1 WO0111582 A1 WO 0111582A1
Authority
WO
WIPO (PCT)
Prior art keywords
ice
optical
light
ice detector
optical element
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
PCT/US2000/021837
Other languages
English (en)
Inventor
Thomas J. Bachinski
Brett A. Muehlhauser
Robert D. Rutkiewicz
Timothy T. Golly
Douglas M. Holm
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.)
Rosemount Aerospace Inc
Original Assignee
Rosemount Aerospace Inc
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 Rosemount Aerospace Inc filed Critical Rosemount Aerospace Inc
Priority to AU66291/00A priority Critical patent/AU6629100A/en
Publication of WO2001011582A1 publication Critical patent/WO2001011582A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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 present invention relates to ice detectors, and more particularly, to optical ice detectors capable of detecting and measuring a liquid water and/or ice accumulation layer, such as can occur on the surface of an air vehicle
  • a major application of the invention lies in aviation where, during cold periods, it is important to know prior to aircraft takeoff whether the surfaces of its lift structures are clean, and to detect ice and icing conditions in flight.
  • the detection of contaminants, and in particular, ice and frost on the ground and ice during flight is critical for safe air vehicle operation.
  • a number of different kinds of contaminant detectors have been utilized for air vehicles.
  • ultrasonic contaminant detectors which utilize ultrasonic energy transmitted through a buffer or plate.
  • Networks of flexible microstrip antennas multiplexed into a microcomputer are also used to detect surface contaminates by measuring the electrical properties of compounds on the surface over the sensor.
  • Other detectors use lasers, fluorescent dyes or vibrating probes.
  • Optical sensors used for measuring liquid level are well known. Thus, sensing circuitry for optical sensors is available. Vickers, Inc. of Maumee, Ohio, USA and Gems Sensor, Inc. of Plainsville,
  • the present invention is a light refractory optical ice detector.
  • the principle of operation makes use of the difference in the optical refraction of light in air, liquids and ice.
  • a light source sends a light beam into a prism or other optically reflective shape. If the outer surface of the prism is free from liquid or ice, the majority of the light beam is reflected through its normal path back to a phototransistor . When the prism is exposed to liquid or ice, some of the light is refracted into the liquid or ice and a less intense light beam is collected by the phototransistor.
  • Sensing circuitry activates warning lights, deicing mechanisms or the like depending on the intensity of the light beam collected by the phototransistor.
  • the optical ice detector would be subject to exposure to light from ambient light sources such as the sun. This ambient light can off set the sensitivity of an optical ice detector by flooding the phototransistor with light thus reducing or eliminating it's capability to detect ice. Because of this, the present invention employ electronic modulation/filtration methods and/or optical filtering methods of reducing or eliminating the effects of the ambient light.
  • optics for ice detection offers several desirable advantages, among which are significantly lower costs, greater simplicity and increased reliability.
  • optical ice detection can be used in combination with decontamination methods for removing ice from the surface.
  • optical ice detectors include carburetor ice detection, ice management systems and ground ice detection in aerospace .
  • Figure 1 is a top view of an airplane where ice detectors are typically mounted on the wing and fuselage;
  • Figure 2 is a cross section taken on line 2--2 in Figure 1, illustrating the placement of optical ice detectors at possible locations on the wing surface;
  • Figure 3 is a side view of an optical ice detector using a prism-shaped reflective surface
  • Figure 4 is a top view of the prism-shaped optical ice detector of Figure 3 ;
  • Figure 5A is a side view of the optical detector of Figure 3 illustrating the internal reflection of light when there is no ice or water build- up on the detector's exterior face;
  • Figure 5B is a side view as in Figure 5A, but with ice or water build-up on the exterior surface of the optical detector;
  • Figure 6 is a side view of an optical ice detector using a flat reflective surface to allow for flush surface mounting
  • Figure 7 is a perspective view of an optical ice detector mounted in a modified housing that has a particle separating inlet shroud
  • Figure 8 is a front view of the modified housing design shown in Figure 7 illustrating the position of the inlet shroud and the optical ice detector in the housing;
  • Figure 9 is a cross section taken on Line 9- -9 in Figure 8 showing the modified housing and particle separating shroud separating particles over the optical ice detector;
  • Figure 10 is a schematic side elevational view of a helicopter having an optical ice detector made according to the present invention installed on the rotor;
  • Figure 11 is a sectional view showing the ice detector mounted in the rotor and taken along line 11-- 11 in Figure 10.
  • FIG. 1 is a top view of an airplane. Ice detectors 12A, 12B and 12C are shown on the top of the wing 10 and on the fuselage 13.
  • Figure 2 is a cross sectional view of wing 10.
  • Optical ice detectors are shown at two possible locations 12A and 12B at the top and leading edge of the wing. Placement or application of the optical ice detector is not restricted by the drawings of the present invention.
  • the ice detectors can be located at any desired location, for example, on fuselage surfaces, turbine inlets and other locations where ice is likely to initially accumulate.
  • FIG 3 is a side view of an optical ice detector 12 shown in Figures 2 and 4 that is mounted on a wing 10.
  • Optical ice detector 12 consists of housing 20, for attachment of detector components, and a prism 22 for reflecting light.
  • the prism is exposed to ambient conditions, and can be recessed slightly to minimize air flow disruption over the mounting surface.
  • the prism can be small in size so it does not substantially disrupt air flow.
  • a light source 24, typically a light emitting diode (LED) emits a continuous or pulsed light beam 30A into the prism 22 that reflects from or passes through interior face 26A of the prism 22. If reflected from face 26A, light beam 30B passes to the opposite side of prism 22 to either reflect from or pass through another interior face 26B. If reflected from face 26B, the light beam is collected by a phototransistor 32, thus completing a circuit.
  • LED light emitting diode
  • Figure 5A illustrates light beam 30A undergoing little change as it is reflected from face 26A because face 28A is free of water or ice. Therefore, the light beam 30C collected by the phototransistor 32, completes a circuit and an electronic signal indicating the lack of ice, water or other contamination on the surface of the prism 22 is sent by the sensing circuitry 42 through cable 40 for processing and control.
  • Figures 3 and 5B illustrate when the prism exterior faces 28A and 28B are exposed to ice build-up.
  • Light beams 30A and 3OB are partially refracted through 26A and 26B into the ice. The amount of refraction is directly dependant on the amount of ice and the type of ice.
  • Light beam 30C is reduced in intensity and the sensing circuit 42 senses this difference in optical amplitude and triggers a signal proportional to the icing condition present on the prism surface.
  • the signal indicating icing conditions can be used to activate warning lights, energize deicing heaters or other systems such as ultrasonic vibrations of surfaces on which ice accretes.
  • the sensitivity of the circuit 42 can be set to various thresholds depending on the application.
  • the reflector can be prism shaped, as in Figures 2-5, flat to allow for a flush mount surface, as illustrated in Figure 6, or any other optically reflective surface shape.
  • Figure 4 is a top view of optical ice detector 12.
  • the housing 20 is square in this design with the light source 24 and phototransistor 22 symmetrically positioned in the housing.
  • Figure 6 illustrates a flush mount optical ice detector 121.
  • This design utilizes a prism 51 oriented upside down relative to the prism arrangement of Figure 3.
  • the light beam 50A emitted from light source 54 is reflected only once, from prism interior face 56, before collection of the light beam 50B by phototransistor 55.
  • the design of Figure 6 has the advantage of a flush mounting surface, it has the limitation of only one reflective surface.
  • the housing 20, circuitry 42 and cable 40 can be the same, as previously discussed.
  • Multiple reflective surfaces, as illustrated in Figure 3 provide more opportunities for refraction of the light beams 30A and 30B into the water or ice on exterior faces 28A and 28B of the optical ice detector 12. The results of multiple refraction is a greater range of light beam intensities entering phototransistor 32.
  • a modification to the invention is the use of an inlet shroud 60 shown in Figures 7, 8 and 9.
  • the shroud is designed to accelerate and alter the airflow 74, over the ice detector 12.
  • Large, heavier particles 70, shown in FIG. 9, are not able to overcome gravitational forces and impact optical ice detector 12, while small, lighter particles 72 are carried along with the airflow indicated at 76 and fly over the prism.
  • the optical detector is selectively sensitive to Super Large Droplet (SLD) icing.
  • SLD Super Large Droplet
  • the helicopter has a rotor 82 driven in the normal manner from an engine, and the helicopter rotor 82 has an outer end portion 84 in which an optical sensor 86 made according to the present invention is installed.
  • the rotor outer portion 84 is hollow, and the sensor 86 is mounted into place.
  • An outer prism shown at 88 is made out of a natural diamond to avoid abrasion commons, and is used as the light reflecting element as explained in connection with the previous figures.
  • the sensor 86 would include a light source, such as that shown at 24, and sensing circuitry.
  • the circuitry provided in the readout is indicated at 90 and can be on board the helicopter.
  • Suitable wires 92 can carry the needed information to the circuitry 90.
  • the optical lens piece when it is made out of a natural diamond, gives great wear abrasion properties as is needed out on the outer tip of the rotor.
  • the sensor is small and lightweight, so that it can be mounted near the tip portion and thus sense any buildup of ice where the rotor blade is spinning the fastest.
  • the sensor will send out a digitized signal that is transferred down the mast for the rotor, using inductions and or radio frequency sensing in the circuitry 90.
  • the sensor of the present invention can be mounted in remote places such as the tip of a rotor of a helicopter to provide information relating to buildup of ice in a timely manner.
  • Various types of baffles can be used for separation of the particles.
  • a further modification to the invention is the use of a specific frequency circuit and/or filters to eliminate or reduce sensitivity of the sensing circuitry to sunlight and other extraneous light sources using such filters is well known.
  • Electronic modulator/filtration methods and/or optional filtering methods to reduce or eliminate the effects of ambient light include using a source consisting of a single or narrow frequency or single color component.
  • Electronic modulation of the sensors emitting light source can be used to provide differentiation from ambient light sources.
  • Optical filtering can block external optical light sources and geometric filtering is used in some applications to reflect off external light sources or shield the sensor from external light sources.
  • ambient light becomes noise and can be filtered out.
  • Other known methods of accommodating ambient light can be used.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Investigating Or Analysing Materials By Optical Means (AREA)

Abstract

L'invention concerne un détecteur de glace optique (12A, 12B, 12C, 12I, 86) utilisant un élément optique (22) monté dans une position exposée à la glace. La lumière réfléchie par un prisme (22, 51, 88) est captée, et lorsque de la glace s'accumule à l'extérieur de ce prisme (22, 51, 88), la quantité de lumière réfléchie change proportionnellement, donnant ainsi une indication du givrage ou d'autres conditions pouvant affecter une surface.
PCT/US2000/021837 1999-08-10 2000-08-10 Detecteur de glace optique Ceased WO2001011582A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU66291/00A AU6629100A (en) 1999-08-10 2000-08-10 Optical ice detector

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US14806299P 1999-08-10 1999-08-10
US60/148,062 1999-08-10

Publications (1)

Publication Number Publication Date
WO2001011582A1 true WO2001011582A1 (fr) 2001-02-15

Family

ID=22524088

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2000/021837 Ceased WO2001011582A1 (fr) 1999-08-10 2000-08-10 Detecteur de glace optique

Country Status (2)

Country Link
AU (1) AU6629100A (fr)
WO (1) WO2001011582A1 (fr)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1254833A1 (fr) * 2001-04-25 2002-11-06 Rosemount Aerospace Inc. Capteur pour conditions de givrage SLD
WO2003002410A1 (fr) * 2001-06-29 2003-01-09 Rosemount Aerospace Inc. Detecteur de givre permettant de detecter de grosses gouttelettes surfondues
WO2003050778A1 (fr) * 2001-12-05 2003-06-19 Mueller Walter Systeme capteur optique destine a detecter la formation de glace
DE102011102804A1 (de) 2011-05-30 2012-12-06 Airbus Operations Gmbh Bordgestütztes Enteisungssystem für Luftfahrzeuge sowie Enteisungsverfahren
CN103101627A (zh) * 2012-12-04 2013-05-15 中国商用飞机有限责任公司 结冰探测器
WO2013097857A1 (fr) * 2011-12-29 2013-07-04 Vestas Wind Systems A/S Turbine éolienne et procédé de détermination de la présence et/ou de l'épaisseur d'une couche de glace sur un corps de pale d'une turbine éolienne
WO2014132070A1 (fr) * 2013-02-28 2014-09-04 Gkn Aerospace Services Limited Système de protection contre le givre
US10884014B2 (en) 2019-03-25 2021-01-05 Rosemount Aerospace Inc. Air data probe with fully-encapsulated heater
US11002754B2 (en) 2018-11-06 2021-05-11 Rosemount Aerospace Inc. Pitot probe with mandrel and pressure swaged outer shell
US11209330B2 (en) 2015-03-23 2021-12-28 Rosemount Aerospace Inc. Corrosion resistant sleeve for an air data probe
CN114162331A (zh) * 2022-02-14 2022-03-11 中国空气动力研究与发展中心低速空气动力研究所 一种结冰探测装置及结冰探测方法
US11414195B2 (en) 2018-03-23 2022-08-16 Rosemount Aerospace Inc. Surface modified heater assembly
US11428707B2 (en) 2019-06-14 2022-08-30 Rosemount Aerospace Inc. Air data probe with weld sealed insert
US11624637B1 (en) 2021-10-01 2023-04-11 Rosemount Aerospace Inc Air data probe with integrated heater bore and features
US11662235B2 (en) 2021-10-01 2023-05-30 Rosemount Aerospace Inc. Air data probe with enhanced conduction integrated heater bore and features
US11686742B2 (en) 2020-11-20 2023-06-27 Rosemount Aerospace Inc. Laser airspeed measurement sensor incorporating reversion capability
US11851193B2 (en) 2020-11-20 2023-12-26 Rosemount Aerospace Inc. Blended optical and vane synthetic air data architecture

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0249296A2 (fr) * 1986-06-10 1987-12-16 Philips Patentverwaltung GmbH Dispositif pour la détermination du givrage
GB2212913A (en) * 1987-11-28 1989-08-02 Robin Edward Carmic Washington Ice warning detector

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0249296A2 (fr) * 1986-06-10 1987-12-16 Philips Patentverwaltung GmbH Dispositif pour la détermination du givrage
GB2212913A (en) * 1987-11-28 1989-08-02 Robin Edward Carmic Washington Ice warning detector

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6759962B2 (en) 2001-04-25 2004-07-06 Rosemount Aerospace Inc. Inflight ice detector to distinguish supercooled large droplet (SLD) icing
EP1254833A1 (fr) * 2001-04-25 2002-11-06 Rosemount Aerospace Inc. Capteur pour conditions de givrage SLD
WO2003002410A1 (fr) * 2001-06-29 2003-01-09 Rosemount Aerospace Inc. Detecteur de givre permettant de detecter de grosses gouttelettes surfondues
WO2003050778A1 (fr) * 2001-12-05 2003-06-19 Mueller Walter Systeme capteur optique destine a detecter la formation de glace
DE102011102804A1 (de) 2011-05-30 2012-12-06 Airbus Operations Gmbh Bordgestütztes Enteisungssystem für Luftfahrzeuge sowie Enteisungsverfahren
CN104136771B (zh) * 2011-12-29 2017-06-23 维斯塔斯风力系统集团公司 风力涡轮机和确定在叶片本体上冰层存在和/或厚度的方法
WO2013097857A1 (fr) * 2011-12-29 2013-07-04 Vestas Wind Systems A/S Turbine éolienne et procédé de détermination de la présence et/ou de l'épaisseur d'une couche de glace sur un corps de pale d'une turbine éolienne
CN103101627A (zh) * 2012-12-04 2013-05-15 中国商用飞机有限责任公司 结冰探测器
CN103101627B (zh) * 2012-12-04 2015-05-13 中国商用飞机有限责任公司 结冰探测器
CN105121284A (zh) * 2013-02-28 2015-12-02 吉凯恩航空服务有限公司 防冰系统
WO2014132070A1 (fr) * 2013-02-28 2014-09-04 Gkn Aerospace Services Limited Système de protection contre le givre
US10232949B2 (en) 2013-02-28 2019-03-19 Gkn Aerospace Services Limited Ice protection system
US11209330B2 (en) 2015-03-23 2021-12-28 Rosemount Aerospace Inc. Corrosion resistant sleeve for an air data probe
US11414195B2 (en) 2018-03-23 2022-08-16 Rosemount Aerospace Inc. Surface modified heater assembly
US11866179B2 (en) 2018-03-23 2024-01-09 Rosemount Aerospace Inc. Surface modified heater assembly
US11002754B2 (en) 2018-11-06 2021-05-11 Rosemount Aerospace Inc. Pitot probe with mandrel and pressure swaged outer shell
US10884014B2 (en) 2019-03-25 2021-01-05 Rosemount Aerospace Inc. Air data probe with fully-encapsulated heater
US11428707B2 (en) 2019-06-14 2022-08-30 Rosemount Aerospace Inc. Air data probe with weld sealed insert
US11686742B2 (en) 2020-11-20 2023-06-27 Rosemount Aerospace Inc. Laser airspeed measurement sensor incorporating reversion capability
US11851193B2 (en) 2020-11-20 2023-12-26 Rosemount Aerospace Inc. Blended optical and vane synthetic air data architecture
US11624637B1 (en) 2021-10-01 2023-04-11 Rosemount Aerospace Inc Air data probe with integrated heater bore and features
US11662235B2 (en) 2021-10-01 2023-05-30 Rosemount Aerospace Inc. Air data probe with enhanced conduction integrated heater bore and features
CN114162331A (zh) * 2022-02-14 2022-03-11 中国空气动力研究与发展中心低速空气动力研究所 一种结冰探测装置及结冰探测方法

Also Published As

Publication number Publication date
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