CA1095607A - Microwave ice detector - Google Patents
Microwave ice detectorInfo
- Publication number
- CA1095607A CA1095607A CA275,245A CA275245A CA1095607A CA 1095607 A CA1095607 A CA 1095607A CA 275245 A CA275245 A CA 275245A CA 1095607 A CA1095607 A CA 1095607A
- Authority
- CA
- Canada
- Prior art keywords
- ice
- waveguide
- energy
- surface waveguide
- microwave
- 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.)
- Expired
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
Abstract
ABSTRACT OF THE DISCLOSURE
The present invention relates generally to surface ice detection systems, and, more particularly, to the detectors for use in aircraft.
Various techniques have been employed in the past for the detection of ice, but have all proved unreliable for one reason or another. One prior art method utilizes forward facing orifices, the formation of ice on the orifices being detected as a decrease in pressure. Other ice detection techniques depend on the detection of a variation in a particular mechanical or electrical parameter. While some of these techniques may operate reason-ably satisfactorily on fixed-wing aircraft, there are additional problems posed by the detection of ice on-helicopters. Many of the prior art techniques are incapable of being adapted for use on rotating surfaces.
Consequently, no satisfactory method has heretofore been available for the detection of ice on helicopter rotor blades. The present invention provides a system for detecting ice on exterior surfaces of aircraft by transmitting a microwave electromagnetic signal into a dielectric layer functioning as a surface waveguide, and monitoring the signals transmitted into and reflected from the waveguide. The waveguide includes a termination element which is mismatched with the waveguide impedance, resulting in partial or total reflection of the microwave energy from the remote end of the wave-guide. As ice builds up on the surface waveguide, the impedence or reflec-tion characteristics of the composite waveguide comprising the ice layer and the permanent surface waveguide give a reliable indication of the presence and location of the ice.
The present invention relates generally to surface ice detection systems, and, more particularly, to the detectors for use in aircraft.
Various techniques have been employed in the past for the detection of ice, but have all proved unreliable for one reason or another. One prior art method utilizes forward facing orifices, the formation of ice on the orifices being detected as a decrease in pressure. Other ice detection techniques depend on the detection of a variation in a particular mechanical or electrical parameter. While some of these techniques may operate reason-ably satisfactorily on fixed-wing aircraft, there are additional problems posed by the detection of ice on-helicopters. Many of the prior art techniques are incapable of being adapted for use on rotating surfaces.
Consequently, no satisfactory method has heretofore been available for the detection of ice on helicopter rotor blades. The present invention provides a system for detecting ice on exterior surfaces of aircraft by transmitting a microwave electromagnetic signal into a dielectric layer functioning as a surface waveguide, and monitoring the signals transmitted into and reflected from the waveguide. The waveguide includes a termination element which is mismatched with the waveguide impedance, resulting in partial or total reflection of the microwave energy from the remote end of the wave-guide. As ice builds up on the surface waveguide, the impedence or reflec-tion characteristics of the composite waveguide comprising the ice layer and the permanent surface waveguide give a reliable indication of the presence and location of the ice.
Description
:1~9~60~7 The present invention relates generally to surface ice detection systems, and, more particularly, to ice detectors for use in aircraft.
The problems relating to the formation of ice on aircraft are well known, and-date from the earl~ days of aviation. In certain climatic conditions, ice has a tendency to form, especially in the vicinity of the leading edges o~ airfoil surfaces, in sheets of sub-stantial thickness. The ice not only increases the e~fective weight of the aircraft, but it can also in-crease drag re~istance and reduce the lift provided by the air~oil.
Various techniques have been employed in the past for the detection of ice, but have all proved un-reliable for one reason or another. One prior art method of ice detection i8 known as the orifice or pressure-probe method, and utilizes forward facing orifices, the formation of ice on the orifices being detected as a decrease in pressure. Other ice detection techniques depend on the detection of a variation`in a partioular mechanical or electrical parameter, such as electrlcal or heat conductivity, or the attenuation of light passed through the ice~ While some of these techniques may operate reasonably satisfactorily on fixed-wing aircraft, there are additional problems posed by the detection of lce on helicopters. Typically helicopters are used at lower altitudes, and are more likely to encounter icing ¢onditions than modern fixed-wing aircraft. Moreover, many of the prior art techniques are incapable of being adapted ~or use on rotating surfaces. Consequently, no completely satisfactory method has heretofore`been avail-able for the detection of ice on heIicopter rotor blades.
It will be apparent from the foregoing that ~ 09S607 there exists a clear need for an ice detection system which can reliably indicate the presence o~ ice on aircra~t, and particularly on rotor blades of helicopters. The present invention ~ulfills this need.
The present invention resides in an aircra~t ice detector, and a related method for its use, in which microwave electromagnetic energy is transmitted into a surface layer o~ ice, and the re~lection or impedance characteristic of the ice layer is monitored to determine the presence and amount of the ice. Basically, and in general terms, the apparatus of the invention includes means for generating microwave electromagnetic energy, coupling means, for coupling the microwave energy for transmission into the surface layèr of ice in such a manner as to propagate the energy through the ice layer acting aa a surface waveguide, and signal monitoring means, such as a re~lectometer, for monitoring the micro-wave energy transmitted to and re~lected from the ice layer, and thereby determining the presence and relative amount of ice ~n the layer.
~ The apparatus of the invention also includes a ;~ permanent surface waveguide o~ such a thickness a~ to allow the propagation of microwave energy even when the ice layer is extremely thin. The permanent surface wave-gulde material is selected to have a dielectric constant approximately equal to that o~ ice and to be a relatively low-los~ material for the transmission of microwave energy.
`:
In accordance with another aapect of the inven-tlon, there is included a mismatch element, suc~l as a short-circuit element, at the end of the surface waveguide remote from the end into which the miorowave energy is transmitted. The mismatch element results in a partial or total re~lection o~ the energy back along the surface ~' .
1{~956(~7 waveguide, the reflected energy being detected by the re~lectometer means. Since the ice will typically contain many impurities, including a signi~icant amount of un-frozen water, it will present a lossy dielectric medium ~or the transmission o~ the microwave energy, and much less energy will be reflected out o~ the composite wave-guide, comprising the ice and the permanent sur~ace wave-guide, when a layer o~ ice is present.
Not enough energy is supplied to the ice layer to heat or melt the ice to any significant degree, but the ice detector of the present invention i~ well suited ~or use in conjunction with a microwave signal source o~
a greater strength, which would be actuated on the de-tection o~ a signi~icant or predetermined amount o~ ice, and which would operate to heat the ice and effect its removal. Alternatively, the invention ha~ independent application as an ice detector, without regard to the type o~ deicing apparatus used.
The method o~ the present invention basically comprises the steps of generating a relatively low-power miorowave signal, coupling the microwave signal ~or trans-mlssion through a surface ice layer acting as a sur~ace waveguide, and monitoring the energy transmitted lnto nd~re~lected ~rom the ice layer, to determine the ; presence and relative amount o~ lce.
It w111 be apparent that the present invention represents a signi~icant advance in the ~ield of ice - , deteotion systems. In particular, the use Or microwave energ~ transmitted through the ice acting as a surface waveguide~ and the monitoring o~ the reflection characteris-tic o~ the ice layer, allows the presence and amount o~
ice to be reliably and accurately determined. Other aRpects and advantage~ Or the invention will become ' , ~095G07 apparent ~rom the following more detailed description taken in conjunction with the accompanying drawings.
FIGURE 1 is a diagrammatic view o~ the ice detection system o~ the present invention;
FIGURE 2 is an equivalent circuit diagram ~or the composite surface waveguide ~ormed by an ice layer and a permanent sur~ace waveguide;
FIGURE 3 is a diagrammatic representation o~
the transmission of micrGwave energy through the permanent sur~ace waveguide and an ice layer on an aircraft surface;
FIGURE 4 i9 an elevational view, partly in section, of a coupler used to transmit microwave energy into the surface waveguide; and FIGURE 5 is a plan view, partly in section, correaponding to the elevational view o~ FIGURE 4.
As shown ln the drawings ~or purposes o~ illu-stration, the present inventi~on is principally concerned with a novel technique ~or the detection o~ ice layers ormed on exterior surfaces of aircra~t. It is particu-larly well-suited to the detection o~ ice on air~oil surfaces o~ both ~ixed-wing and rotating-wing aircraft.
In accordance with the inventionJ an lce layer indioated by reference numeral 1OJ i9 detected by trans-mitting~into it miorowave electromagnetic energy supplied from a conventional miorowave signal aource 12, and ooupled to~the ic;e~by means o~ a sur~ace waveguid~ coupler 14 in such~a manner that the ice layer~unctions as a sur~aoe waveguide~'. me ice layer 10 is ~ormed on a per-:
manent dielectric layer 16 which also ~unctions aa a ' 30 sur~ace wavegulde, ~the dlelectriç layer 16 being ~ormed ' ~ on an aircraft aur~ace 18, typlcally of metal, on which ice is expected to accumulate. A microwave short-circuit element 20 is instal~led at the end of the wa~eguide 16 , : ~ :
~956~'7 remote ~rom the surface waveguide coupler 14, to ensure re~lection o~ microwave energy back along the waveguide.
A dual directional coupler 22 is used to couple the micro-wave energy from the signal source 12 to the surface wave-guide coupler 14, and to supply a signal to a reflectometer 24 connected to the dual directional coupler 22. The reflectometer monitors the complex value of the impedance or reflection characteristic o~ the composite waveguide comprising the ice layer 10 and permanent surface waveguide 16.
Waveguides taking the ~orm of closed tubes o~
circular or rectangular cross section are well known.
Less ~amiliar is the concept o~ an "open boundary" struc-ture for transmitting microwave energy along a surface.
The energy is closely bound to the surface, and although electric or magnetic fields persist outside o~ the wave-guide, they decrease exponentially in a direction normal to the surface. Propagation of microwave energy through a surface waveguide occurs in what are commonly known as "trapped" modes o~ transmission, which can be considered equivalent to total internal re~lection ~rom the surface boundaries of the waveguide. As shown in FIGURE 3, the microwave energy can be thought o~ as being launched into , :
the permanent surface waveguide 16 in such a manner that the angle of incidence with the surface boundaries~ i.e, with the ice-alr interface, and the dielectric metal interface, exceeds the crltical angle above which total internal reflection will take place.
The frequency of operation o~ the apparatus of the invention is not critical and can be selected to meet specific design re~uirements, and to con~orm with relevant governmental regulations. Typical ~requencies would fall in the range 2,000-22,000 megahertz. The ~:
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.. . .. . . . . .
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signal source 12 can be operated continuously, i.e., in "continuous-wave" mode, or can be adapted ~or pulsed operation .
FIGURE 2 is an equivalent circuit diagram showing the composite waveguide as being equivalent to a trans- ~ -mission line short circuited at its remote end by the element 20. In FIGURES 1 and 2 the letter A is used to indicate the input end of the composite waveguide, B is used to indicate the location at which the ice layer be-gins~ C i8 used to indicate the location in which the ice layer ends, and D is used to indicate the short-circuited end o~ the waveguide.
The material of the permanent surface waveguide 16 is selected to have a dielectric constant approximately equal to that of ice, so that little refraction occurs at the ice-diele¢tric inter~ace, and to have a relatively lossless dielectric characteristic.
~ he material should also be selected for it~
ability to withstand severe rain, sand and dust erosion.
This is particularly lmportant if the ice detector iq to be used on helicopter rotor blades. Suitable materials are alumina; an ultra-high molecular weight polyethylene, such as one sold under the trademark LENNITE; high quartz fiber silicone resin laminates; fused quartz; or epoxy glass or silicone glass laminates. In addition, a poly-urethane erosion coat, of approximately 0.012 inch thick-::
ness, may be used as an erosion coat over some of these materials. The dielectric properties of polyurethane render it unsuitable ~or use alone as a waveguide material.
One way o~ expressing the relative impedance charaoteristics Or a transmission line is in terms o~ a dimensionless reflection coe~ficient~ which will be a mathematically complex quantit~ having real and imaginary . ~ .
- ' .
. . .
l~S607 components. Since the permanent sur~ace waveguide 16 is Or relatively lossless material~ and since the rerlecting element 20 can be selected to provide almost total re-flection, the reflection coef~icient detected by means o~
the dual direction coupler 22 and the reflectometer 24 will have a magnitude of practically unity when no ice layer 10 is present. There will, however, be a substantial phase di~erence between the transmitted and reflected signals.
The accretion o~ the ice layer 10 on the di- -electric layer 16 introduces a relatively lossy component into the~dielectric waveguide, as indicated by the im-pedance ZOi between the positions B and C in FI~URE 2.
The energy propagated through the composite waveguide will then be sub~ect to a substantial los~ in magnitude as well as a substantial phase shirt, resulting in a reflection coe~icient havlng a magnitude o~ substantially less than unity, and a phase angle dif~erent ~rom the one observed in the absence of the ice layer. As the accretion o~
ice continues, the reflection coefficient aæ measured by the reflectometer 24 will change in both magnitude and phase until a relatively small rerlection coe~ricient ~; ~obtains. The speci~ic values o~ re~leation coe~icients ; detected by the dual directional ooupler 22 and re~lectometer ~ ~ , 24 will depend, of course, on the æpecific parameters of the;ice detector~
The re~lectometer 24 can b0 coupled, as shown at 26J to generate a control signal output indicative o~
the re~leotion coefficient measured by the reflectometer.
~0 The reflection coe~ricient, or a component thereor, can be di~played directly on indicating means (not shown) calibrated directly in terms Or amount of ice, or relative position o~ ice, since the relative phase shi~t Or the ;
1~9S6~
reflection coefficient will be related to the position of the ice with respect to the entire permanent surface wave-guide 16. Alternatively, or in addition, the value of the reflection coefficient could be compared with a threshold value, preselected during calibration of the instrument, and a control signal generated to actuate deicing equip-ment when the reflection coefficient reaches the threshold value.
FIGURES 4 and 5 show a surface waveguide coupler corresponding to that referred to by reference numeral 14 in FIGURE 1. The coupler 14 includes a conventional rectangular waveguide 30 having a flanged end 32 ~or coupling to the dual directional coupler 22 or other conventional microwave distribution components (not ~hown). At its end opposite the flange 32, the waveguide 30 is closed except for a circular aperture 34 in one sidewall through which a coupling pin 36 projects, the pin being attached to the sidewall opposite the aperture.
The pin 36, as best shown in FIGURE 5, overlies and is partly embedded in the sur~ace waveguide 16. The metal surface 18 includes a portion which encloses the end of the surface waveguide 16, as shown at 38, to act as a reflector and thereby to e~fect radiation o~ the micro-wave energy in the desired direction along the waveguide 16. It will be appreciated that some of the microwave energ~ reflected ~rom the reflecting element 20 and di~
rected back along the waveguide 16 will again be reflected by the portion 38 o~ the metal surface 18, resulting in a series of complex multiple reflections back and forth ~0 along the waveguide. Some resultant component of the energy originally transmitted into the waveguide 16 through the coupler 14 will~ however~ be reflected back out of the coupler 14 ~or detection by the dual direc-~09560~
tional coupler 22 and the re~lectometer 24.
For use of the invention to detect ice on heli-copter rotor blades, the microwave signal source 12 may, because o~ its low power requirements, be mounted for rotation with the rotor blades, together with the dual directional coupler 22, reflectometer 24 and sur~ace waveguide coupler 14. Alternatively, the microwave signal :
source 12 could be mounted in the body o~ the helicopter and also used to supply larger amounts o~ power to deice the rotor blades. This arrangement would require the addition o~ a rotary joint and a number of other conven-tional microwave distribution components, none of which is illustrated, to transmit the microwave energy to the rotor blade sur~aces.
It will be appreciated ~rom the foregoing that the present invention represents a significant adYance in the field of ice detection systems. In particular, the use of microwave energy of relatively low power to detect the reflection or~impedance characteristic o~ a composite waveguide comprising a lossless waveguide and a surface ;ice layer, results in the reliable detection of the presenoe, amount and pos1tlon o~ the ice layer on the ; waveguide, as well as its rate o~ accretion. It will also ; be appreciated that, although a partioular embodiment o~
the invention has been described in detail ~or purposes o~ llustration, various changes and modi~ications may be made~without depar~ting from the spirit and scope o~ the invention. Accordingly, the invention is not to be limited except às by the appended claims.
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The problems relating to the formation of ice on aircraft are well known, and-date from the earl~ days of aviation. In certain climatic conditions, ice has a tendency to form, especially in the vicinity of the leading edges o~ airfoil surfaces, in sheets of sub-stantial thickness. The ice not only increases the e~fective weight of the aircraft, but it can also in-crease drag re~istance and reduce the lift provided by the air~oil.
Various techniques have been employed in the past for the detection of ice, but have all proved un-reliable for one reason or another. One prior art method of ice detection i8 known as the orifice or pressure-probe method, and utilizes forward facing orifices, the formation of ice on the orifices being detected as a decrease in pressure. Other ice detection techniques depend on the detection of a variation`in a partioular mechanical or electrical parameter, such as electrlcal or heat conductivity, or the attenuation of light passed through the ice~ While some of these techniques may operate reasonably satisfactorily on fixed-wing aircraft, there are additional problems posed by the detection of lce on helicopters. Typically helicopters are used at lower altitudes, and are more likely to encounter icing ¢onditions than modern fixed-wing aircraft. Moreover, many of the prior art techniques are incapable of being adapted ~or use on rotating surfaces. Consequently, no completely satisfactory method has heretofore`been avail-able for the detection of ice on heIicopter rotor blades.
It will be apparent from the foregoing that ~ 09S607 there exists a clear need for an ice detection system which can reliably indicate the presence o~ ice on aircra~t, and particularly on rotor blades of helicopters. The present invention ~ulfills this need.
The present invention resides in an aircra~t ice detector, and a related method for its use, in which microwave electromagnetic energy is transmitted into a surface layer o~ ice, and the re~lection or impedance characteristic of the ice layer is monitored to determine the presence and amount of the ice. Basically, and in general terms, the apparatus of the invention includes means for generating microwave electromagnetic energy, coupling means, for coupling the microwave energy for transmission into the surface layèr of ice in such a manner as to propagate the energy through the ice layer acting aa a surface waveguide, and signal monitoring means, such as a re~lectometer, for monitoring the micro-wave energy transmitted to and re~lected from the ice layer, and thereby determining the presence and relative amount of ice ~n the layer.
~ The apparatus of the invention also includes a ;~ permanent surface waveguide o~ such a thickness a~ to allow the propagation of microwave energy even when the ice layer is extremely thin. The permanent surface wave-gulde material is selected to have a dielectric constant approximately equal to that o~ ice and to be a relatively low-los~ material for the transmission of microwave energy.
`:
In accordance with another aapect of the inven-tlon, there is included a mismatch element, suc~l as a short-circuit element, at the end of the surface waveguide remote from the end into which the miorowave energy is transmitted. The mismatch element results in a partial or total re~lection o~ the energy back along the surface ~' .
1{~956(~7 waveguide, the reflected energy being detected by the re~lectometer means. Since the ice will typically contain many impurities, including a signi~icant amount of un-frozen water, it will present a lossy dielectric medium ~or the transmission o~ the microwave energy, and much less energy will be reflected out o~ the composite wave-guide, comprising the ice and the permanent sur~ace wave-guide, when a layer o~ ice is present.
Not enough energy is supplied to the ice layer to heat or melt the ice to any significant degree, but the ice detector of the present invention i~ well suited ~or use in conjunction with a microwave signal source o~
a greater strength, which would be actuated on the de-tection o~ a signi~icant or predetermined amount o~ ice, and which would operate to heat the ice and effect its removal. Alternatively, the invention ha~ independent application as an ice detector, without regard to the type o~ deicing apparatus used.
The method o~ the present invention basically comprises the steps of generating a relatively low-power miorowave signal, coupling the microwave signal ~or trans-mlssion through a surface ice layer acting as a sur~ace waveguide, and monitoring the energy transmitted lnto nd~re~lected ~rom the ice layer, to determine the ; presence and relative amount o~ lce.
It w111 be apparent that the present invention represents a signi~icant advance in the ~ield of ice - , deteotion systems. In particular, the use Or microwave energ~ transmitted through the ice acting as a surface waveguide~ and the monitoring o~ the reflection characteris-tic o~ the ice layer, allows the presence and amount o~
ice to be reliably and accurately determined. Other aRpects and advantage~ Or the invention will become ' , ~095G07 apparent ~rom the following more detailed description taken in conjunction with the accompanying drawings.
FIGURE 1 is a diagrammatic view o~ the ice detection system o~ the present invention;
FIGURE 2 is an equivalent circuit diagram ~or the composite surface waveguide ~ormed by an ice layer and a permanent sur~ace waveguide;
FIGURE 3 is a diagrammatic representation o~
the transmission of micrGwave energy through the permanent sur~ace waveguide and an ice layer on an aircraft surface;
FIGURE 4 i9 an elevational view, partly in section, of a coupler used to transmit microwave energy into the surface waveguide; and FIGURE 5 is a plan view, partly in section, correaponding to the elevational view o~ FIGURE 4.
As shown ln the drawings ~or purposes o~ illu-stration, the present inventi~on is principally concerned with a novel technique ~or the detection o~ ice layers ormed on exterior surfaces of aircra~t. It is particu-larly well-suited to the detection o~ ice on air~oil surfaces o~ both ~ixed-wing and rotating-wing aircraft.
In accordance with the inventionJ an lce layer indioated by reference numeral 1OJ i9 detected by trans-mitting~into it miorowave electromagnetic energy supplied from a conventional miorowave signal aource 12, and ooupled to~the ic;e~by means o~ a sur~ace waveguid~ coupler 14 in such~a manner that the ice layer~unctions as a sur~aoe waveguide~'. me ice layer 10 is ~ormed on a per-:
manent dielectric layer 16 which also ~unctions aa a ' 30 sur~ace wavegulde, ~the dlelectriç layer 16 being ~ormed ' ~ on an aircraft aur~ace 18, typlcally of metal, on which ice is expected to accumulate. A microwave short-circuit element 20 is instal~led at the end of the wa~eguide 16 , : ~ :
~956~'7 remote ~rom the surface waveguide coupler 14, to ensure re~lection o~ microwave energy back along the waveguide.
A dual directional coupler 22 is used to couple the micro-wave energy from the signal source 12 to the surface wave-guide coupler 14, and to supply a signal to a reflectometer 24 connected to the dual directional coupler 22. The reflectometer monitors the complex value of the impedance or reflection characteristic o~ the composite waveguide comprising the ice layer 10 and permanent surface waveguide 16.
Waveguides taking the ~orm of closed tubes o~
circular or rectangular cross section are well known.
Less ~amiliar is the concept o~ an "open boundary" struc-ture for transmitting microwave energy along a surface.
The energy is closely bound to the surface, and although electric or magnetic fields persist outside o~ the wave-guide, they decrease exponentially in a direction normal to the surface. Propagation of microwave energy through a surface waveguide occurs in what are commonly known as "trapped" modes o~ transmission, which can be considered equivalent to total internal re~lection ~rom the surface boundaries of the waveguide. As shown in FIGURE 3, the microwave energy can be thought o~ as being launched into , :
the permanent surface waveguide 16 in such a manner that the angle of incidence with the surface boundaries~ i.e, with the ice-alr interface, and the dielectric metal interface, exceeds the crltical angle above which total internal reflection will take place.
The frequency of operation o~ the apparatus of the invention is not critical and can be selected to meet specific design re~uirements, and to con~orm with relevant governmental regulations. Typical ~requencies would fall in the range 2,000-22,000 megahertz. The ~:
..
.. . .. . . . . .
l~g5~0~
signal source 12 can be operated continuously, i.e., in "continuous-wave" mode, or can be adapted ~or pulsed operation .
FIGURE 2 is an equivalent circuit diagram showing the composite waveguide as being equivalent to a trans- ~ -mission line short circuited at its remote end by the element 20. In FIGURES 1 and 2 the letter A is used to indicate the input end of the composite waveguide, B is used to indicate the location at which the ice layer be-gins~ C i8 used to indicate the location in which the ice layer ends, and D is used to indicate the short-circuited end o~ the waveguide.
The material of the permanent surface waveguide 16 is selected to have a dielectric constant approximately equal to that of ice, so that little refraction occurs at the ice-diele¢tric inter~ace, and to have a relatively lossless dielectric characteristic.
~ he material should also be selected for it~
ability to withstand severe rain, sand and dust erosion.
This is particularly lmportant if the ice detector iq to be used on helicopter rotor blades. Suitable materials are alumina; an ultra-high molecular weight polyethylene, such as one sold under the trademark LENNITE; high quartz fiber silicone resin laminates; fused quartz; or epoxy glass or silicone glass laminates. In addition, a poly-urethane erosion coat, of approximately 0.012 inch thick-::
ness, may be used as an erosion coat over some of these materials. The dielectric properties of polyurethane render it unsuitable ~or use alone as a waveguide material.
One way o~ expressing the relative impedance charaoteristics Or a transmission line is in terms o~ a dimensionless reflection coe~ficient~ which will be a mathematically complex quantit~ having real and imaginary . ~ .
- ' .
. . .
l~S607 components. Since the permanent sur~ace waveguide 16 is Or relatively lossless material~ and since the rerlecting element 20 can be selected to provide almost total re-flection, the reflection coef~icient detected by means o~
the dual direction coupler 22 and the reflectometer 24 will have a magnitude of practically unity when no ice layer 10 is present. There will, however, be a substantial phase di~erence between the transmitted and reflected signals.
The accretion o~ the ice layer 10 on the di- -electric layer 16 introduces a relatively lossy component into the~dielectric waveguide, as indicated by the im-pedance ZOi between the positions B and C in FI~URE 2.
The energy propagated through the composite waveguide will then be sub~ect to a substantial los~ in magnitude as well as a substantial phase shirt, resulting in a reflection coe~icient havlng a magnitude o~ substantially less than unity, and a phase angle dif~erent ~rom the one observed in the absence of the ice layer. As the accretion o~
ice continues, the reflection coefficient aæ measured by the reflectometer 24 will change in both magnitude and phase until a relatively small rerlection coe~ricient ~; ~obtains. The speci~ic values o~ re~leation coe~icients ; detected by the dual directional ooupler 22 and re~lectometer ~ ~ , 24 will depend, of course, on the æpecific parameters of the;ice detector~
The re~lectometer 24 can b0 coupled, as shown at 26J to generate a control signal output indicative o~
the re~leotion coefficient measured by the reflectometer.
~0 The reflection coe~ricient, or a component thereor, can be di~played directly on indicating means (not shown) calibrated directly in terms Or amount of ice, or relative position o~ ice, since the relative phase shi~t Or the ;
1~9S6~
reflection coefficient will be related to the position of the ice with respect to the entire permanent surface wave-guide 16. Alternatively, or in addition, the value of the reflection coefficient could be compared with a threshold value, preselected during calibration of the instrument, and a control signal generated to actuate deicing equip-ment when the reflection coefficient reaches the threshold value.
FIGURES 4 and 5 show a surface waveguide coupler corresponding to that referred to by reference numeral 14 in FIGURE 1. The coupler 14 includes a conventional rectangular waveguide 30 having a flanged end 32 ~or coupling to the dual directional coupler 22 or other conventional microwave distribution components (not ~hown). At its end opposite the flange 32, the waveguide 30 is closed except for a circular aperture 34 in one sidewall through which a coupling pin 36 projects, the pin being attached to the sidewall opposite the aperture.
The pin 36, as best shown in FIGURE 5, overlies and is partly embedded in the sur~ace waveguide 16. The metal surface 18 includes a portion which encloses the end of the surface waveguide 16, as shown at 38, to act as a reflector and thereby to e~fect radiation o~ the micro-wave energy in the desired direction along the waveguide 16. It will be appreciated that some of the microwave energ~ reflected ~rom the reflecting element 20 and di~
rected back along the waveguide 16 will again be reflected by the portion 38 o~ the metal surface 18, resulting in a series of complex multiple reflections back and forth ~0 along the waveguide. Some resultant component of the energy originally transmitted into the waveguide 16 through the coupler 14 will~ however~ be reflected back out of the coupler 14 ~or detection by the dual direc-~09560~
tional coupler 22 and the re~lectometer 24.
For use of the invention to detect ice on heli-copter rotor blades, the microwave signal source 12 may, because o~ its low power requirements, be mounted for rotation with the rotor blades, together with the dual directional coupler 22, reflectometer 24 and sur~ace waveguide coupler 14. Alternatively, the microwave signal :
source 12 could be mounted in the body o~ the helicopter and also used to supply larger amounts o~ power to deice the rotor blades. This arrangement would require the addition o~ a rotary joint and a number of other conven-tional microwave distribution components, none of which is illustrated, to transmit the microwave energy to the rotor blade sur~aces.
It will be appreciated ~rom the foregoing that the present invention represents a significant adYance in the field of ice detection systems. In particular, the use of microwave energy of relatively low power to detect the reflection or~impedance characteristic o~ a composite waveguide comprising a lossless waveguide and a surface ;ice layer, results in the reliable detection of the presenoe, amount and pos1tlon o~ the ice layer on the ; waveguide, as well as its rate o~ accretion. It will also ; be appreciated that, although a partioular embodiment o~
the invention has been described in detail ~or purposes o~ llustration, various changes and modi~ications may be made~without depar~ting from the spirit and scope o~ the invention. Accordingly, the invention is not to be limited except às by the appended claims.
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Claims (5)
PROPERTY OR PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS:
1. A method of detecting ice on exterior surface of aircraft, comprising the steps of: generating a microwave electro-magnetic signal; coupling the microwave signal to a permanent surface waveguide of dielectric material having a dielectric constant approximately the same as that of ice; transmitting the microwave signal along the surface waveguide in a direction substantially parallel with a surface on which ice is to be detected; reflecting at least a portion of the microwave energy back along the waveguide from its remote end; and detecting in a reflectometer a ratio between transmitted and reflective energy with respect to the waveguide;
whereby accretion of ice on the surface waveguide results in a different reflection characteristic of the composite wave-guide comprising the ice layer and the permanent surface waveguide, and the presence and location of ice may be detected by means of the reflectometer.
whereby accretion of ice on the surface waveguide results in a different reflection characteristic of the composite wave-guide comprising the ice layer and the permanent surface waveguide, and the presence and location of ice may be detected by means of the reflectometer.
2. Aircraft ice detection apparatus, comprising: a source of microwave electromagnetic energy; surface waveguide coupling means for coupling the microwave energy to a surface layer of ice in such a manner that the ice functions as a surface waveguide; and signal monitoring means for comparing the microwave signals transmitted into and reflected from said surface waveguide means; whereby variations in the amount of ice result in corresponding variations in the amount of reflected energy.
3. The apparatus as claimed in claim 2, wherein said surface waveguide coupling means includes: a permanent surface waveguide of dielectric material overlying a surface on which the presence of ice is to be detected; and means for coupling the microwave energy to said permanent surface waveguide in such a manner that the energy is transmitted along said permanent surface waveguide and along any ice layer formed thereon, as a composite surface waveguide.
4. The apparatus as claimed in claim 3, further comprising:
a dual directional coupler connected between said microwave energy source and said surface waveguide coupler to monitor the transmission of energy in both directions; and reflectometer means coupled with said dual directional coupler, to monitor the relationship bewteen the microwave energy trnasmitted into said waveguide and the energy reflected from said waveguide.
a dual directional coupler connected between said microwave energy source and said surface waveguide coupler to monitor the transmission of energy in both directions; and reflectometer means coupled with said dual directional coupler, to monitor the relationship bewteen the microwave energy trnasmitted into said waveguide and the energy reflected from said waveguide.
5. The apparatus as claimed in claim 4, further including waveguide terminating means operative to reflect at least partially the energy transmitted along said surface waveguide.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US672,616 | 1976-04-01 | ||
| US05/672,616 US4054255A (en) | 1976-04-01 | 1976-04-01 | Microwave ice detector |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1095607A true CA1095607A (en) | 1981-02-10 |
Family
ID=24699311
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA275,245A Expired CA1095607A (en) | 1976-04-01 | 1977-03-31 | Microwave ice detector |
Country Status (12)
| Country | Link |
|---|---|
| US (1) | US4054255A (en) |
| JP (1) | JPS52131749A (en) |
| CA (1) | CA1095607A (en) |
| DD (1) | DD130015A5 (en) |
| DE (1) | DE2713081A1 (en) |
| DK (1) | DK147277A (en) |
| FI (1) | FI59062C (en) |
| FR (1) | FR2346218A1 (en) |
| GB (1) | GB1531674A (en) |
| NL (1) | NL7703555A (en) |
| NO (1) | NO143267C (en) |
| SE (1) | SE7703664L (en) |
Families Citing this family (56)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DK149870C (en) * | 1976-12-30 | 1987-03-23 | Danske Sukkerfab | PROCEDURE FOR CONCENTRATION MEASUREMENT IN A MEDIUM |
| FI61249C (en) * | 1979-10-10 | 1982-06-10 | Vaisala Oy | ANORDING FOER INDIKERING AV NEDISNING AV ASFALTSVAEG ELLER MOTSVARANDE |
| JPS5712329A (en) * | 1980-06-25 | 1982-01-22 | Hitachi Ltd | Frost sensor |
| IT1211006B (en) * | 1981-03-09 | 1989-09-29 | Cise Spa | MICROWAVE SENSOR FOR CHECKING THE LEVEL OF THE MELTED METAL IN CONTINUOUS CASTINGS. |
| DE3135263C2 (en) * | 1981-09-05 | 1986-11-06 | ELEKTRO-PHYSIK Hans Nix & Dr.-Ing. E. Steingroever GmbH & Co KG, 5000 Köln | Method and device for the non-destructive measurement of material accumulations or layer thicknesses on film-like dielectric materials, in particular plastic |
| US4688185A (en) * | 1982-01-05 | 1987-08-18 | University Research Foundation | Microwave ice accretion measuring instrument |
| US4470123A (en) * | 1982-01-05 | 1984-09-04 | Miami R & D Limited Partnership | Microwave ice accretion meter |
| GB2124764B (en) * | 1982-08-03 | 1986-01-08 | Atomic Energy Authority Uk | Ice detector |
| US4649713A (en) * | 1984-05-21 | 1987-03-17 | Bezek Donald J | Microwave ice detector |
| US4590803A (en) * | 1984-06-28 | 1986-05-27 | Westinghouse Electric Corp. | Acoustic waveguide monitoring |
| US4913519A (en) * | 1988-03-04 | 1990-04-03 | Fiberchem Inc. | Optical sensor for the detection of ice formation and other chemical species |
| US4873510A (en) * | 1988-04-21 | 1989-10-10 | Boris Khurgin | Ice detector with movable feeler |
| US5061836A (en) * | 1990-01-18 | 1991-10-29 | United Technologies Corporation | Microwave deicing for aircraft engine propulsor blades |
| US5187980A (en) * | 1990-05-31 | 1993-02-23 | The United States Of America As Represented By The United States Department Of Energy | Method and apparatus for acoustic plate mode liquid-solid phase transition detection |
| US5313202A (en) * | 1991-01-04 | 1994-05-17 | Massachusetts Institute Of Technology | Method of and apparatus for detection of ice accretion |
| US5182944A (en) * | 1991-01-18 | 1993-02-02 | Brunnenkant Siegfried W | Helicopter icing spray system |
| FI90957C (en) * | 1992-09-08 | 1994-04-25 | Soundek Oy | Aircraft wing freeze indicator |
| US5381694A (en) * | 1992-09-29 | 1995-01-17 | Dedicated Electronics | Ice thickness measurement reflectometer |
| FI95751C (en) * | 1993-12-09 | 1996-03-11 | Labko Ab Oy | Method for identifying different phases of water and sensor arrangement used in the method |
| US5557261A (en) * | 1994-05-06 | 1996-09-17 | Nichols Research Corporation | Ice monitoring and detection system |
| US5821862A (en) * | 1994-08-30 | 1998-10-13 | University Of Guelph | Method and apparatus for measuring ice thickness on substrates using backscattering of gamma rays |
| US6049282A (en) * | 1994-08-30 | 2000-04-11 | University Of Guelph | Method and apparatus for measuring ice thickness on substrates using backscattering of gamma rays |
| US5497100A (en) * | 1994-10-17 | 1996-03-05 | Hughes Aircraft Company | Surface condition sensing system |
| US5781115A (en) * | 1995-04-03 | 1998-07-14 | Target Microwave | Apparatus and method for detection and thickness measurement of coatings over a surface |
| US6192752B1 (en) | 1995-08-04 | 2001-02-27 | Zevex, Inc. | Noninvasive electromagnetic fluid level sensor |
| US5695155A (en) * | 1995-09-21 | 1997-12-09 | Hughes Aircraft Company | Resonator-based, surface-condition sensor |
| US5772153A (en) * | 1995-10-17 | 1998-06-30 | Abaunza; John T. | Aircraft icing sensors |
| US6052056A (en) * | 1996-04-26 | 2000-04-18 | Icg Technologies, Llc | Substance detection system and method |
| US5841289A (en) * | 1997-01-28 | 1998-11-24 | The United States Of America As Represented By The Secretary Of The Army | System and method for detecting accretion of frazil ice on underwater gratings |
| US5900820A (en) * | 1997-06-09 | 1999-05-04 | The United States Of America As Represented By The Secretary Of The Army | System and method for detection of frazil ice on underwater grating |
| US6166661A (en) * | 1999-01-22 | 2000-12-26 | Rockwell Collins, Inc. | System for detecting ice on an aircraft |
| US6320511B1 (en) * | 2000-11-28 | 2001-11-20 | Rosemount Aerospace Inc. | Ice detector configuration for improved ice detection at near freezing conditions |
| US6995572B2 (en) * | 2001-03-05 | 2006-02-07 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Sensor and method for detecting a superstrate |
| US7017415B2 (en) * | 2001-09-27 | 2006-03-28 | Siemens Westinghouse Power Corporation | Apparatus for sensing pressure fluctuations in a hostile environment |
| US7104502B2 (en) * | 2004-03-31 | 2006-09-12 | Rosemount Aerospace Inc. | Ice detector for improved ice detection at near freezing condition |
| US20050230553A1 (en) * | 2004-03-31 | 2005-10-20 | Rosemount Aerospace Inc. | Ice detector for improved ice detection at near freezing condition |
| US7805978B2 (en) | 2006-10-24 | 2010-10-05 | Zevex, Inc. | Method for making and using an air bubble detector |
| US7439877B1 (en) | 2007-05-18 | 2008-10-21 | Philip Onni Jarvinen | Total impedance and complex dielectric property ice detection system |
| US7987722B2 (en) | 2007-08-24 | 2011-08-02 | Zevex, Inc. | Ultrasonic air and fluid detector |
| US7775482B2 (en) * | 2008-04-18 | 2010-08-17 | Honeywell International Inc. | Aircraft icing sensor |
| GB0823121D0 (en) * | 2008-12-18 | 2009-01-28 | Penny & Giles Controls Ltd | Ice detection system |
| WO2010091314A2 (en) | 2009-02-06 | 2010-08-12 | Zevex, Inc. | Air bubble detector |
| US8779945B2 (en) * | 2010-03-17 | 2014-07-15 | Sikorsky Aircraft Corporation | Virtual ice accretion meter display |
| US9056684B2 (en) * | 2011-04-08 | 2015-06-16 | Textron Innovations Inc. | Rotor blade de-icing system |
| GB2494435B (en) * | 2011-09-08 | 2018-10-03 | Roke Manor Res Limited | Apparatus for the transmission of electromagnetic waves |
| DE102012210150A1 (en) * | 2012-06-15 | 2013-12-19 | Wobben Properties Gmbh | Wind turbine and method for controlling a wind turbine or a wind farm |
| WO2015014545A1 (en) * | 2013-07-31 | 2015-02-05 | Siemens Aktiengesellschaft | Object detector and method for detecting an object |
| WO2015061557A1 (en) * | 2013-10-24 | 2015-04-30 | The Regents Of The University Of Michigan | Aircraft icing detector |
| US10498393B2 (en) * | 2014-09-11 | 2019-12-03 | Cpg Technologies, Llc | Guided surface wave powered sensing devices |
| US10336465B2 (en) | 2016-01-08 | 2019-07-02 | The Regents Of The University Of Michigan | Ice crystals and volcanic ash detection system |
| 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 |
| WO2021012050A1 (en) * | 2019-07-23 | 2021-01-28 | The University Of British Columbia | Method and apparatus for detecting ice formation on a surface using resonant sensors |
| US20210129997A1 (en) * | 2019-11-05 | 2021-05-06 | Rohr, Inc. | Thermal anti-icing system with microwave system |
| US11802756B2 (en) | 2020-08-18 | 2023-10-31 | Steven R. Weeres | Ice thickness transducer |
| US11021259B1 (en) | 2021-01-07 | 2021-06-01 | Philip Onni Jarvinen | Aircraft exhaust mitigation system and process |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3116395A (en) * | 1960-04-26 | 1963-12-31 | United Control Corp | Ice detector system |
| FR1482385A (en) * | 1966-06-06 | 1967-05-26 | Glass Developments Ltd | Frost detector |
| US3540025A (en) * | 1967-01-20 | 1970-11-10 | Sierracin Corp | Ice detector |
| GB1321596A (en) * | 1969-07-18 | 1973-06-27 | English Electric Co Ltd | Ice detectors |
| GB1322479A (en) * | 1969-07-18 | 1973-07-04 | English Electric Co Ltd | Ice detectors |
| US3836846A (en) * | 1971-09-09 | 1974-09-17 | Monsanto Co | Ice detection apparatus employing microwave reflectance |
| DE2163703A1 (en) * | 1971-12-22 | 1973-06-28 | Vdo Schindling | DEVICE FOR DETERMINING ICING ON A SURFACE OF AN OBJECTIVE |
-
1976
- 1976-04-01 US US05/672,616 patent/US4054255A/en not_active Expired - Lifetime
-
1977
- 1977-03-01 GB GB8493/77A patent/GB1531674A/en not_active Expired
- 1977-03-24 DE DE19772713081 patent/DE2713081A1/en not_active Withdrawn
- 1977-03-30 JP JP3479577A patent/JPS52131749A/en active Pending
- 1977-03-30 SE SE7703664A patent/SE7703664L/en not_active Application Discontinuation
- 1977-03-31 FR FR7709752A patent/FR2346218A1/en active Granted
- 1977-03-31 NO NO771146A patent/NO143267C/en unknown
- 1977-03-31 CA CA275,245A patent/CA1095607A/en not_active Expired
- 1977-03-31 FI FI771007A patent/FI59062C/en not_active IP Right Cessation
- 1977-04-01 DD DD7700198213A patent/DD130015A5/en unknown
- 1977-04-01 DK DK147277A patent/DK147277A/en not_active IP Right Cessation
- 1977-04-01 NL NL7703555A patent/NL7703555A/en not_active Application Discontinuation
Also Published As
| Publication number | Publication date |
|---|---|
| NO771146L (en) | 1977-10-04 |
| NL7703555A (en) | 1977-10-04 |
| NO143267B (en) | 1980-09-29 |
| GB1531674A (en) | 1978-11-08 |
| FI771007A (en) | 1977-10-02 |
| DE2713081A1 (en) | 1977-10-13 |
| US4054255A (en) | 1977-10-18 |
| FR2346218B1 (en) | 1982-11-12 |
| FR2346218A1 (en) | 1977-10-28 |
| DK147277A (en) | 1977-10-02 |
| JPS52131749A (en) | 1977-11-04 |
| NO143267C (en) | 1981-01-07 |
| SE7703664L (en) | 1977-10-02 |
| FI59062C (en) | 1981-06-10 |
| FI59062B (en) | 1981-02-27 |
| DD130015A5 (en) | 1978-03-01 |
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