WO2003002410A1 - Supercooled large droplet ice detector - Google Patents
Supercooled large droplet ice detector Download PDFInfo
- Publication number
- WO2003002410A1 WO2003002410A1 PCT/US2001/021061 US0121061W WO03002410A1 WO 2003002410 A1 WO2003002410 A1 WO 2003002410A1 US 0121061 W US0121061 W US 0121061W WO 03002410 A1 WO03002410 A1 WO 03002410A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- sensor
- housing
- ice
- leading edge
- tip surface
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
-
- 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
Definitions
- This invention relates to ice detectors, and more particularly, to ice detectors for detecting the presence of supercooled large droplets that freeze and form ice on aircraft surfaces.
- the ice detector of the present invention comprises a sensor and a housing for supporting the sensor, wherein the housing includes a base, a tip having a tip surface, and a leading edge and trailing edge extending from the base to the tip, wherein the sensor extends above the tip surface between the leading and trailing edges, and the housing includes a fluid passageway extending from an inlet end in the leading edge to an outlet end on the tip surface, and wherein the passageway outlet end is downstream of the leading edge and upstream of the sensor, and the housing further includes a pair of spaced apart rails extending above the surface of the tip, and the sensor and outlet end are between the rails.
- Figure 2 is a cross-sectional view of an ice detector of the present invention taken along the lines 2-2 of Figure 1 ;
- Figure 3 is a perspective view of an alternative embodiment of the present invention.
- the housing 12 has a leading edge 20 and a trailing edge 22, and as shown in the figures, the sensor 16 is located between the edges 20,22.
- the tip surface 18 inclines upwardly (i.e., away from the base 14) from the leading edge 20 of the housing 12 to the trailing edge 22 of the housing 12.
- a fluid passageway 24 extends from a passageway inlet 26 in the housing leading edge 20 to a passageway outlet 28 in the tip surface 18.
- the inlet 26 is adjacent the tip surface 18; and the outlet 28 is downstream of the leading edge 20 and upstream of, and slightly spaced away from, the sensor 10.
- the housing 12 includes a pair of axially spaced-apart rails 30 that extend above the housing tip surface 18.
- the passageway inlet and outlet ends 26,28, respectively, each have a cross sectional area defined by a length and width.
- the length of the inlet, Li is about the same as the length of the outlet L 0 ; the inlet and outlet lengths Lj. and L 0 are both slightly less than the length (or distance) L r between facing surfaces 31 of the rails 30.
- the inlet and outlet ends 26, 28, respectively, are also defined by a width (or height) . As seen in Fig. 1, the width Wi of the inlet 26 is greater than the width W 0 of the outlet 28. Accordingly, the cross-sectional area of the inlet 26 at the leading edge 20 of the housing 12 is greater than the cross-sectional area of the outlet 28 at the tip surface 18 of the housing 12.
- the cross- sectional area of the fluid passageway 24 decreases from the inlet end 26 to the outlet end 28 in order to maximize the velocity of the air in the passageway 24 at the outlet end 28.
- the axially extending passageway walls 32 and 33 are configured such that both walls are approximately parallel to the tip surface 18 at the passageway inlet end 26, and approximately parallel to the axis 34 of the sensor element 10 at the passageway outlet end 28.
- a conventional cartridge heater 38 is shown running along the leading edge of the housing 12, adjacent the surface of the leading edge 20 but spaced away from the sensor 10, for keeping the temperature of the leading edge above freezing.
- the heater 28 is controlled by electronics schematically indicated by reference numeral 40.
- a thermocouple (not shown) or similar temperature sensing device that monitors the temperature of the housing, particularly the temperature along the housing leading edge 20. If the temperature of the housing 12 drops below freezing, the heater controller energizes the heater until the temperature of the housing 12 rises above freezing.
- the sensing element 10 is thermally isolated from the housing 12, the heat inputted to the housing has a minimal effect on the operation of the sensing element 10:
- a conventional Peltier junction may be utilized, wherein the cold junction is in thermal communication with the element 10 and the hot junction is in thermal communication with the housing 12.
- the housing 12 includes an integral cap 42 that extends above the sensor 10 and passageway outlet end 28. As is seen in Fig. 3, the cap is integral with and extends between the rails 30 from the housing leading edge 20 to the housing trailing edge 22. Not shown in Fig. 3 is a cartridge heater that extends adjacent to the leading edge 20 and sensor 10, similar to the configuration shown in Fig. 2.
- the housing includes one or more fluid passageways 44 that extend through the cap in an area above the sensor 10.
- the cap 42 and its integrally attached rails 30 define a second inlet end 46 at the housing leading edge 20 and a second outlet end (not shown) at the housing trailing edge 22.
- the cap 42 is constructed and arranged such that the cross sectional area of the second inlet end 46 is slightly larger than the cross sectional area of the second outlet end; and so that the cross sectional area of the second inlet end 46 is slightly larger than the area of the first inlet end 26.
- the ice detector 5 shown in Fig. 3 also includes an ice protection removal system similar to that discussed above with reference to Figs. 1 and 2.
- the detector 50 shown in Fig. 4 includes a first ice detection sensor (or sensing element) 51 surrounded and supported by a housing 52 that includes a base 54 and an attachment structure 55.
- the housing 52 extends from the base 54 to the tip 56, and the sensor 51 extends slightly above the surface 58 of the tip 56.
- the sensor 51 extends through a channel (not shown) in the housing 52, similar to the manner shown in Figures 1 and 2.
- the sensor 51 is thenllally isolated from the housing 52, which is preferably made from a high thermal conductivity material such as aluminum or any of the other well-known materials having high thenllal conductivity.
- the detector 50 has a leading edge 60 and a trailing edge 62.
- a fluid passageway 64 extends from an inlet 66 in the leading edge 60 to an outlet 68 in the tip surface 58.
- a pair of spaced-apart rails 70 extend above the tip surface 58, on each side of the sensing element 51, to a location downstream of the sensor 51. As seen in Fig. 4, the tip surface 58 inclines upwardly in the direction from the leading edge 60 toward the trailing edge 70.
- the detector 50 Downstream of the first sensor 51 and upstream of the trailing edge 62, the detector 50 also includes a second ice detection sensor 72.
- the second sensor 72 is axially aligned with the first sensor 51, and extends above the tip surface 58 a distance greater than the distance above which the first sensor 51 extends.
- the second sensor 72 extends above the surface 58 of the tip 56 an amount that is in the range of about five to ten times greater than the distance the first sensor 51 extends above the surface 58.
- the second sensor 72 is also downstream of the rails 70 and does not tend to be shielded or shadowed by the rails 70.
- the rails 70 shield the first sensing element 51 from impact by certain sized water droplets.
- the second sensor 72 extends through a channel (not shown) in the housing 52 and is thermally isolated from the housing 52.
- the ice detector 50 additionally includes means for removing ice from the housing leading edge (as described with respect to Figures 1-3 above) , and in particular the aforementioned cartridge heater and its associated controller. Peltier junction technology is optionally used for one or both of the detector elements ,51 and 72, as needed.
- air flowing through the passageway 24 forms a series of vortices 82 (sometimes referred as vacuum or separation bubbles) both upstream and downstream of the passageway outlet 28.
- Vortices 82 also form upstream and downstream of the sensing element 10. These vortices 82 force the air flowing past the sensing element 10 to flow away from and over the sensing element 10, as shown in the figure.
- the presence of the rails 30 on either side of the sensing element 10 causes the air to flow in the generally axial direction; that is, the air flows between the rails 30 from the housing leading edge 20 to the housing trailing edge 22.
- the passageway 24 and the sensing element 10 have the greatest effect on the boundary layer of air flowing along the tip surface 18.
- the boundary layer is generally considered to be in the range of about 0.25 1.25 cm (about 0.1-0.5 in.) thick as it passes over tip surface 18.
- the ability to control the shape and flow path direction of the boundary layer is a key factor of the invention, because these boundary layer characteristics have a significant effect upon water droplets that flow past the sensing element 10, as described in more detail below, and with particular reference to Figures 6 and 7.
- FIG. 6 provides a schematic depiction of the flow direction of water droplets typically found in clouds capable of forming "normal" (or non-SLD) icing.
- normal icing typically occurs when an aircraft flies through a population of supercooled water droplets having a mean diameter of about twenty microns.
- such water droplets are represented by the reference numeral 84, and their flow path indicated by the arrows 86.
- twenty micron diameter water droplets generally follow the flow direction of the air in which they are entrained. Because of the relatively small mass (and momentum) of the droplets 84, they are unable to penetrate through the separation bubbles 82 formed as a result of the vortices.
- the sensing element (reference numeral 10 in Figs. 1 and 3; reference numerals 51 and 72 in ⁇ Fig. 4) is of the vibrating element type, such that when ice forms on the element surface, its natural frequency is changed due to mass loading.
- the sensing element 10 vibrates in the direction of its longitudinal axis 34.
- the vibrating frequency of the element 10 is continually sensed by its associated electronics (depicted as reference numeral 41 in Fig. 2), and variations in the sensing frequency are indicative of the formation of ice on the element 10.
- Magnetostrictive sensing elements that operate on the aforementioned principles are available from BFGoodrich Aircraft Sensors Division in Burnsville, Minnesota, U.S.A.; Model No. 0871HL1.
- the detector preferably includes a heater and associated controller circuitry for melting ice that forms on the sensing element 10.
- the housing includes one or more drain holes in fluid communication with the channel within which the element resides.
- Figures 5, 6 and 7 show the effects that boundary layer conditions along-the tip surface 18 of the housing 12 have on the flow direction of air and any entrained water droplets in the air. Droplets in the fifty micron diameter range have sufficient momentum to flow through the separation bubbles and strike the sensing element 10, while particles having a diameter less than fifty micron generally do not strike the sensing element 10.
- the frequency monitoring circuitry of the sensor 10 may be adjusted to establish a threshold level above which SLD conditions will be presumed not to be present; below such threshold level, SLD conditions will be presumed to exist.
- the threshold level can be established taking into account the rate at which the frequency changes, as well as simply monitoring the amount of frequency change.
- the rate of frequency change can also be used to indicate droplet size, when compared with the output from a conventional ice detector.
- the threshold level and ice accumulation rate are determined from calibrations of the detector in an icing wind tunnel.
- the ice sensing element is of the vibrating element type, which allows the user to establish threshold levels as appropriate to safely provide an indication of SLD conditions without the need to absolutely determine a droplet diameter that causes SLD icing.
- frequency sensing detection element 10 as is used in the detectors of Figures 1, 2 and 3 may also be used in the combination sensor shown in Figure 4.
- the rails extend above the tip surface an amount sufficient to shield or shadow the sensing element and, in conjunction with the vortices and separation bubbles that form adjacent to the sensing element, to prevent such small droplets from striking the sensing element.
- the ice detector of the present invention When operated in an environment containing a varied population of water droplet diameters, the ice detector of the present invention is capable of providing a signal indicating whether conditions are present for forming SLD icing or whether normal cloud icing will result. If SLD icing conditions are present, the environment will contain water droplets having a variety of diameters, some of which will be in the range of fifty microns and larger and others will be smaller, in the range of about twenty microns. In such an environment, and using an SLD detector such as is shown in Fig. 4, those droplets with sufficient momentum to be undisturbed by the boundary layer (i.e., the fifty micron particles) will contact the sensor 51 in the manner as described above. Those same droplets will also strike the sensor 72.
- the ability of the sensor of the present invention to detect when it is in SLD icing conditions, but also to discriminate between SLD icing conditions and non-SLD icing conditions provides the aerospace industry with a key technology for improving the safety of flight in icing conditions .
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2003508607A JP2004534948A (en) | 2001-06-29 | 2001-06-29 | Large supercooled drop ice detector |
EP01948869A EP1401707A1 (en) | 2001-06-29 | 2001-06-29 | Supercooled large droplet ice detector |
PCT/US2001/021061 WO2003002410A1 (en) | 2001-06-29 | 2001-06-29 | Supercooled large droplet ice detector |
CA002452623A CA2452623A1 (en) | 2001-06-29 | 2001-06-29 | Supercooled large droplet ice detector |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/US2001/021061 WO2003002410A1 (en) | 2001-06-29 | 2001-06-29 | Supercooled large droplet ice detector |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2003002410A1 true WO2003002410A1 (en) | 2003-01-09 |
Family
ID=21742682
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2001/021061 WO2003002410A1 (en) | 2001-06-29 | 2001-06-29 | Supercooled large droplet ice detector |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP1401707A1 (en) |
JP (1) | JP2004534948A (en) |
CA (1) | CA2452623A1 (en) |
WO (1) | WO2003002410A1 (en) |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1396425A1 (en) * | 2003-03-10 | 2004-03-10 | Auxitrol SA | Large spectrum icing conditions detector |
FR2868393A1 (en) * | 2004-03-31 | 2005-10-07 | Rosemount Aerospace Inc | ICE DETECTOR AND ENHANCED ICE DETECTION IN QUASI-GIVING CONDITIONS |
US20130240672A1 (en) * | 2012-01-05 | 2013-09-19 | The Boeing Company | Laser-Based Supercooled Large Drop Icing Condition Detection System |
US9079669B2 (en) | 2010-07-16 | 2015-07-14 | Commercial Aircraft Corporation Of China, Ltd | Icing detector probe and icing detector with the same |
US9527595B2 (en) | 2012-01-06 | 2016-12-27 | Instrumar Limited | Apparatus and method of monitoring for matter accumulation on an aircraft surface |
CN106314800A (en) * | 2016-09-23 | 2017-01-11 | 中国人民解放军国防科学技术大学 | Ice breaking and removing method based on plasma impact jet flow |
EP3264103A1 (en) * | 2016-06-28 | 2018-01-03 | Rosemount Aerospace Inc. | Air data sensing probe with icing condition detector |
US10625869B2 (en) | 2016-06-28 | 2020-04-21 | Rosemount Aerospace Inc. | Automated super-cooled water-droplet size differentiation using aircraft accretion patterns |
US10940952B2 (en) | 2015-05-05 | 2021-03-09 | Instrumar Limited | Apparatus and method of monitoring for in-flight aircraft engine ice crystal accretion |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS6444610A (en) * | 1987-08-12 | 1989-02-17 | Toshiba Corp | Output circuit |
KR101175256B1 (en) | 2010-08-18 | 2012-08-21 | 한국해양연구원 | Method and apparatus for measuring the thickness of ice |
US8907798B2 (en) * | 2012-01-05 | 2014-12-09 | The Boeing Company | Supercooled large drop icing condition detection system |
JP6377315B2 (en) * | 2012-03-08 | 2018-08-22 | ザ・ボーイング・カンパニーThe Boeing Company | Icing condition detection system for supercooled large droplets |
US8650944B2 (en) * | 2012-03-13 | 2014-02-18 | The Boeing Company | Supercooled large drop icing condition simulation system |
US9227733B2 (en) * | 2013-01-02 | 2016-01-05 | The Boeing Company | Automated water drop measurement and ice detection system |
US10336465B2 (en) | 2016-01-08 | 2019-07-02 | The Regents Of The University Of Michigan | Ice crystals and volcanic ash detection system |
US20170283077A1 (en) * | 2016-04-01 | 2017-10-05 | Goodrich Corporation | Pneumatic de-icer with sensor for supercooled large droplet icing detection |
US10621865B2 (en) | 2018-03-29 | 2020-04-14 | The Regents Of The University Of Michigan | Road condition monitoring system |
US10508952B1 (en) | 2018-10-31 | 2019-12-17 | The Regents Of The University Of Michigan | Optimum spectral bands for active vision systems |
Citations (9)
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US3341835A (en) | 1964-11-05 | 1967-09-12 | Rosemount Eng Co Ltd | Ice detector |
US3940622A (en) * | 1972-10-23 | 1976-02-24 | Canadian Patents & Development Limited | Icing detector |
US4210021A (en) * | 1978-07-06 | 1980-07-01 | Bantsekin Viktor I | Method and device for detecting icing of objects found in air flow |
US4553137A (en) | 1983-06-01 | 1985-11-12 | Rosemount Inc. | Non-intrusive ice detector |
US4611492A (en) | 1984-05-03 | 1986-09-16 | Rosemount Inc. | Membrane type non-intrusive ice detector |
US5562265A (en) | 1994-10-13 | 1996-10-08 | The B. F. Goodrich Company | Vibrating pneumatic deicing system |
US5657951A (en) | 1995-06-23 | 1997-08-19 | The B.F. Goodrich Company | Electrothermal de-icing system |
US5743494A (en) | 1995-03-07 | 1998-04-28 | The Bfgoodrich Company | Polyurethane deicer |
WO2001011582A1 (en) * | 1999-08-10 | 2001-02-15 | Rosemount Aerospace Inc. | Optical ice detector |
-
2001
- 2001-06-29 EP EP01948869A patent/EP1401707A1/en not_active Withdrawn
- 2001-06-29 JP JP2003508607A patent/JP2004534948A/en active Pending
- 2001-06-29 CA CA002452623A patent/CA2452623A1/en not_active Abandoned
- 2001-06-29 WO PCT/US2001/021061 patent/WO2003002410A1/en not_active Application Discontinuation
Patent Citations (9)
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US3341835A (en) | 1964-11-05 | 1967-09-12 | Rosemount Eng Co Ltd | Ice detector |
US3940622A (en) * | 1972-10-23 | 1976-02-24 | Canadian Patents & Development Limited | Icing detector |
US4210021A (en) * | 1978-07-06 | 1980-07-01 | Bantsekin Viktor I | Method and device for detecting icing of objects found in air flow |
US4553137A (en) | 1983-06-01 | 1985-11-12 | Rosemount Inc. | Non-intrusive ice detector |
US4611492A (en) | 1984-05-03 | 1986-09-16 | Rosemount Inc. | Membrane type non-intrusive ice detector |
US5562265A (en) | 1994-10-13 | 1996-10-08 | The B. F. Goodrich Company | Vibrating pneumatic deicing system |
US5743494A (en) | 1995-03-07 | 1998-04-28 | The Bfgoodrich Company | Polyurethane deicer |
US5657951A (en) | 1995-06-23 | 1997-08-19 | The B.F. Goodrich Company | Electrothermal de-icing system |
WO2001011582A1 (en) * | 1999-08-10 | 2001-02-15 | Rosemount Aerospace Inc. | Optical ice detector |
Non-Patent Citations (2)
Title |
---|
"Droplet Size Distribution and Ice Shapes" by Shah et al., AIAA 98-0487 |
NASA/FAA/NCAR Supercooled Large Droplet Icing Flight Research; "Summary of Winter 96-97 FlightOperations" by Miller et al., AIAA 98-0577 |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1396425A1 (en) * | 2003-03-10 | 2004-03-10 | Auxitrol SA | Large spectrum icing conditions detector |
FR2868393A1 (en) * | 2004-03-31 | 2005-10-07 | Rosemount Aerospace Inc | ICE DETECTOR AND ENHANCED ICE DETECTION IN QUASI-GIVING CONDITIONS |
US9079669B2 (en) | 2010-07-16 | 2015-07-14 | Commercial Aircraft Corporation Of China, Ltd | Icing detector probe and icing detector with the same |
US20130240672A1 (en) * | 2012-01-05 | 2013-09-19 | The Boeing Company | Laser-Based Supercooled Large Drop Icing Condition Detection System |
US9013332B2 (en) * | 2012-01-05 | 2015-04-21 | The Boeing Company | Laser-based supercooled large drop icing condition detection system |
US9527595B2 (en) | 2012-01-06 | 2016-12-27 | Instrumar Limited | Apparatus and method of monitoring for matter accumulation on an aircraft surface |
US10940952B2 (en) | 2015-05-05 | 2021-03-09 | Instrumar Limited | Apparatus and method of monitoring for in-flight aircraft engine ice crystal accretion |
US11772801B2 (en) | 2015-05-05 | 2023-10-03 | Instrumar Limited | Electric field sensor with sensitivity-attenuating ground ring |
EP3264103A1 (en) * | 2016-06-28 | 2018-01-03 | Rosemount Aerospace Inc. | Air data sensing probe with icing condition detector |
US10132824B2 (en) | 2016-06-28 | 2018-11-20 | Rosemount Aerospace Inc. | Air data sensing probe with icing condition detector |
US10625869B2 (en) | 2016-06-28 | 2020-04-21 | Rosemount Aerospace Inc. | Automated super-cooled water-droplet size differentiation using aircraft accretion patterns |
CN106314800A (en) * | 2016-09-23 | 2017-01-11 | 中国人民解放军国防科学技术大学 | Ice breaking and removing method based on plasma impact jet flow |
Also Published As
Publication number | Publication date |
---|---|
CA2452623A1 (en) | 2003-01-09 |
JP2004534948A (en) | 2004-11-18 |
EP1401707A1 (en) | 2004-03-31 |
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