Abstract: A method of detecting that ice has been shed from an external surface of a component is provided, the method comprising applying power to a heating means to provide heat to said external surface. The method further comprises sensing the temperature of the component and calculating the rate of change of temperature increase of the external surface over time. Further, the method comprises detecting a change in said rate of change of temperature increase over time, wherein said detected change in rate of change of temperature increase indicates that said ice has been shed from said external surface of said component.

Abstract: The method of controlling an autonomous anti-icing apparatus includes: a first step of collecting and storing ice formation environment data; a second step of calculating a calculated value of an aerodynamic parameter based on the ice formation environment data and the ice formation prediction data in real time to determine whether ice formation is present on a surface of the structure and calculating a degree of ice formation through the calculated value of the aerodynamic parameter; and a third step of allowing a calculation control unit to send a temperature control signal, which includes a heating period signal, to a power supply so that an electric heating part is heated when the ice formation is determined by comparing the degree of ice formation with a preset value.

Abstract: Accumulation of debris, snow, ice, wildlife, insects, and other contaminants adversely affect antennas that are mounted outdoors. An antenna comprises a housing and a removeable inflatable cover. The housing may include one or more engagement features, such as a perimeter channel into which perimeter of an opening of the covering is retained. The covering may be selectively inflated to produce a motion in the covering that displaces accumulated contaminants and discourages further accumulation. Heaters may warm air inside the covering to facilitate melting of ice. Inflation of the covering may be responsive to environmental conditions. For example, during high wind conditions, the covering may be evacuated and retained in a collapsed configuration to reduce damage.

Abstract: An ultrasonic measurement apparatus (1) estimates a property/state of a test object (100) that allows an injected ultrasonic wave to propagate as plate waves (UW) of propagation modes. The ultrasonic measurement apparatus (1) includes: a receiver (30) configured to receive a detected signal obtained by detecting the plate waves (UW) propagating through the test object (100) to output a received signal indicating a time-domain waveform of the detected signal; an intensity detector (12) configured to detect the signal intensity of a waveform part corresponding to a first propagation mode, and the signal intensity of a waveform part corresponding to a second propagation mode; and an estimator (13) configured to make a comparison between the signal intensities to estimate a property/state of the test object (100) on the basis of a result of the comparison.

Abstract: Disclosed are a method and device for compressing and reconstructing data. The method includes: disposing a transmitting EMAT array and a receiving EMAT array; exciting a Lamb wave, receiving the Lamb wave, subjecting the Lamb wave to narrowband filtering with the narrowband frequency, to form detecting data x(n); analysing the detecting data with a DFT; reconstructing original detecting data and calculating a reconstruction error according to the measurement vector and the recovery matrix by using a TLBO algorithm; optimizing measurement vector and recovery matrix; transmitting the measurement vector to a supervisory device.

Abstract: Embodiments describe a method for predicting the accumulation of ice on a rotor blade (111, 112) of a wind turbine (100) and the use thereof.

Abstract: A method of improving the measurement accuracy of a digital ice rate sensor by providing an enhanced surface finish on a magnetostrictive oscillator detector probe by measuring the surface roughness of the detector probe, comparing the measured value to a critical value, and authorizing the probe for use in the digital ice rate sensor if surface roughness is within the critical value. Surface roughness may be measured optically or with a surface profilometer. Remedial steps taken if surface roughness is not within the critical value include reworking the probe surface finish and investigating the manufacturing process.

Abstract: The present approach relates to the inspection of assets, such as assets having parts that move during operation. As discussed herein, operational data for the asset may be incorporated into planning or adapting the flight plan and/or operational commands may be issued to asset in accordance with the flight plan to facilitate acquisition of the inspection data.

Abstract: A heat sink with shape-optimized fins provides for improved heat transfer. Synthetic jets create vortices which enhance heat transfer and cooling of downstream fins, while the shape of the fins limits pressure drop in the flow over the cooling fins.

Abstract: A flowrate sensor includes first and second portions to be mounted protruding inside and the duct, respectively, includes a probe constrained to the first portion responsive to the flowrate and arranged to move from a rest position to a measuring position under a fluid dynamic thrust, the sensor having a load cell constrained to the second portions and arranged to receive a force from the probe responsive to the measuring position and configured to maintain a corresponding electric measurement signal, wherein first and second portions are fluid-tightly separated by a wall, and the probe and the load cell are configured for transferring a magnetic force between the probe and the cell, through the wall, without contacting each other, first and second portion being preferably housed within an elongated container whose first and second parts house first and second portions and protrude inside and outside the duct, respectively.

Abstract: In a first aspect the invention relates to a sensor system (10) for determining a proximity to icing conditions of an environment. The system includes a sensor having a sensor surface (12) for exposure to the environment, an electrically powered heat pump means (16) for cooling and/or heating the surface (12), and a temperature detector (14) for providing a signal representative of the temperature of the surface (12). An environment temperature is determined, and a processor determines, from the temperature detected by the temperature detector (14) and the environment temperature, a proximity to icing conditions of the environment to which the surface (12) is exposed. In a second aspect of the invention the sensor system includes a power monitor for determining an amount of power required to heat or cool the surface through a temperature indicative of ice formation. The processor determines the proximity to icing conditions from the detected temperatures and the amount of cooling or heating power.

Abstract: An icing detector probe includes three sections arranged sequentially along the direction of air flow, namely, a first section, a second section and a third section. The shape of the outer surface of the first section is suitable for collecting droplets in the air flow. The shape of the outer surface of the second section is suitable for full decelerating and releasing latent heat of large droplets during their movements. The outer surface of the third section is suitable for icing of large droplets. The probe detects icing by distinguishing and identify large droplets icing. The probe effectively detects types of traditional icing, thus being helpful for exact detection of icing thickness. An icing detector including said icing detector probe is also provided.

Abstract: A method and apparatus for detecting icing conditions. An icing condition detection system comprises a number of sensors and an icing condition detector. The number of sensors is located in a number of locations on an aircraft. A sensor in the number of sensors is configured to emit electromagnetic radiation into drops of water in an environment around the aircraft. The sensor in the number of sensors is configured to detect responses to the electromagnetic radiation. The sensor in the number of sensors is configured to generate data from the responses. The icing condition detector is configured to monitor for the data from the number of sensors. The icing condition detector is further configured to detect a presence of a number of types of icing conditions for the aircraft using the data from the number of sensors.

Abstract: Autonomous Underwater Vehicles (AUV) collect and transmit information about ice floe thickness; this is combined with SYNTHETIC APERTURE RADAR images from satellites to identify and track dangerously thick regions of ice. The overlayed data is presented graphically to allow tracking of the thick ice regions over time. This information is used to alert drilling platforms in icy ocean conditions of pending ice floe dangers.

Abstract: A system for preventing icing in a conduit, as can occur in an aircraft's air conditioning system, includes at least one sensor for acquiring mechanical oscillations of the conduits, an electronic evaluation unit and an electronic control unit. The sensor is connected to the electronic evaluation unit, which knows characteristics relating to the oscillation behavior of the conduit and is equipped to compare the measured conduit oscillations with these characteristics, and through correlation to interpret them as conduit icing, and in the case of conduit icing to emit a signal to the control unit. If the operation-associated oscillations are inadequate, oscillations can be generated or amplified through an actuator. With this system an icing state within the conduit can be detected without the use of sensors located in the interior cross section of the conduit, which itself serves as a sensitive element.

Abstract: Device and method for anticipating the deposition of ice on a runway, comprising an object having a non-zero relative velocity with respect to the atmosphere surrounding the runway, this surrounding atmosphere being at a certain temperature, a means for determining the thickness of ice present on said moving object, which further includes a temperature sensor for measuring the temperature of the runway, a means for regulating the temperature of said object in such a way that the temperature of said moving object is substantially equal to or slightly below the temperature of the runway, a computing means, for defining at time t0 a level of icing at time t1 of the runway as a function of the thickness of ice present on the object, and a warning means allowing the results obtained by the computing means to be communicated to a monitoring station.

Abstract: According to the invention, the method comprises exposing a surface (3) sensitive to relative wind and monitoring the thermal flow variations between the surface (3) and the aerodynamic flow, said variations resulting from that of the forced-convection thermal exchange coefficient between the surface (3) and the aerodynamic flow depending on the rime or ice build-up, using the temperature sensor (12) under the surface (3), considering that stripping occurs by the flow of an ice layer formed on the surface (3) if it is detected, preferably after heating by at least one heater (4), that there is a brisk rise of the flow at a temperature close to 0° C., and supplying after the detection of ice stripping, a signal indicating the presence of rime or rime conditions. A cooler (5) may cool the surface (3) for anticipating the formation of ice with a heating process. The invention can be used for detecting rime and/or rime conditions on a flying aircraft.

Abstract: A system and method for detecting ice on a rotor blade of a wind turbine are disclosed. In one embodiment, the method may include pitching the rotor blade across a range of pitch angles, monitoring an ice-related parameter of the wind turbine as the rotor blade is pitched and comparing the monitored ice-related parameter to a predetermined baseline profile for the ice-related parameter.

Abstract: An aerodynamically shaped profile member for aircraft and wind power stations includes, for example, phased-array ultrasonic generator arrangement arranged therein. During operation of the profile member, the ultrasonic generator emits ultrasonic waves in a targeted manner in multiple directions to determine a profile of the thickness of an ice layer on the surface of the aerodynamic profile. The structure may be, for example, a composite fiber material arranged around a foam core, with the ultrasonic generator arrangement being laminated into the composite fiber material. For measurement of the ice thickness, ultrasonic waves are transmitted in a targeted manner to different positions of the surface of the aerodynamic profile, and the ultrasonic waves reflected on the interfaces of the ice layer are detected. At least one region of the surface is scanned by means of the targeted ultrasonic waves, to determine an ice thickness profile.

Abstract: An inexpensive and simple-to-operate ice safety device is provided for deployment in a body of water. Once deployed, the ice safety device can be activated to check whether ice has formed to a predetermined thickness around the ice safety device. If ice has not formed to the predetermined thickness, the ice safety device indicates an unsafe condition. The ice safety device can be moored to a fixed location.

Abstract: The present invention relates to an improved sensor arrangement, a system and method for determining the rate of ice formation and how close conditions are to those at which ice will form on a surface, and to an improved sensor arrangement for use therein. The sensor arrangement comprises a means (11,12,14) for measuring the thermal lag, heating and cooling of a thermally conductive element, which is comprised of a first and second surface (15a, 15b), said first surface exposed to the environment, wherein the surface area of said first surface is smaller than the second surface. The step of ice detection may be performed by either a passive measuring system wherein the latent heat of ice formation is measured via the temperature differential across a Peltier element.

Abstract: The invention relates to a method and a system for detecting the risk of icing on aerodynamic surfaces lapped by a fluid flow (F), in particular on load-bearing surfaces of fluid machines, of the type comprising a temperature sensor (20). The system is characterized in that the temperature sensor (20) is located close to the aerodynamic surface (5S) to be monitored for detecting the temperature of the surface (5S), and that the system comprises a rain sensor (30) located close to the surface (5S) for detecting the presence of water on that surface (5S). The system can thus detect the risk of icing on aerodynamic surfaces.

Abstract: A system for an icing resistant sensor port assembly includes shaped and patterned features for resisting the formation and propagation of ice around a sensor port, such as for a pressure sensor in an aircraft fuel tank. Water may be present in fuel tanks due to condensation and other factors. The water, being heavier than fuel, such as jet fuel, sinks to the bottom of the tank and may be present around the sensor port. If the water completely fills the pressure port, it may damage the sensor. In various embodiments, an inlet assembly having a cone-shaped countersink, sharp edges that reduce surface area, anti-wetting coatings, and slots to allow fluid flow within the inlet assembly, among other features, may be used to help resist ice formation and propagation around a sensor port.

Abstract: A system and method for detecting ice on a rotor blade of a wind turbine are disclosed. In one embodiment, the method may include pitching the rotor blade across a range of pitch angles, monitoring an ice-related parameter of the wind turbine as the rotor blade is pitched and comparing the monitored ice-related parameter to a predetermined baseline profile for the ice-related parameter.

Abstract: A method and system for detecting asymmetric utilizing longitudinal tower acceleration data may include: providing a rotorspeed acceleration monitoring system; determining from the rotorspeed acceleration monitoring system whether a rotorspeed acceleration is above a rotorspeed acceleration limit; determining whether a rotor-mass imbalance condition exists; and determining whether a longitudinal tower acceleration coincides with icing on a rotor.

Abstract: An aircraft Ice Detection pitot-static tube is described which uses sensors integrated into the pitot-static tube to determine when and where the pitot-static tube is icing up. Temperature, thermal conductivity and impedance sensor measurements are combined with a mathematical transfer of the impedance sensor output into the complex dielectric plane to identify that the material accreating on the exterior and interior of the pitot-static tube is ice and only ice. Identification of ice realized when the trace in complex dielectric space has a distinctive semi-circular form, which only ice exhibits, with measured values in agreement with reference laboratory data stored in the onboard computer system.

Abstract: In an icing condition detection system, a circuit provides an output representing impending icing conditions as a function of power consumption of a single element detector. A thermal isolation pedestal includes a detector support end that supports the single element detector and an opposite strut mounting end. A thermal isolation controller controls a thermal isolation pedestal temperature to thermally isolate the single element detector from a strut mounting end.

Abstract: Systems and methods for detecting ice particle accumulation is disclosed herein. In one exemplary implementation, a method for detecting ice is described in which a parameter within an interior volume of a heated conduit is measured. The method also includes detecting the presence of an accumulation of ice particles based on the parameter measured within the interior volume of the heated conduit.

Abstract: Systems and methods for detecting ice particle accumulation is disclosed herein. In one exemplary implementation, a method for detecting ice is described in which a parameter within an interior volume of a heated conduit is measured. The method also includes detecting the presence of an accumulation of ice particles based on the parameter measured within the interior volume of the heated conduit.

Abstract: An apparatus and method for wind debris detection comprises a spring loaded probe that is deployed on the leading edge of an aircraft wing into an area where debris formation might impact wing aerodynamic performance. The probe travel is sensed by sensors (angular displacement, linear displacement, proximity, torque, load cell on spring, and the like), and if the sensor(s) detect that probe travel is limited then presence of debris is indicated.

Abstract: A sensor for detecting icing conditions in an airstream includes a flow housing mounted on an aircraft and in which one or more probes are mounted. At least one of the probes subjected to impingement of the airstream and liquid moisture droplets in such airstream. The heat removal, or cooling effect on the probe in the airstream carrying liquid droplets is determined. A temperature signal indicating the airstream temperature is combined with signals from the at least one probe for determining whether or not icing conditions are present.

Abstract: Ice detection apparatus for monitoring ice accretion on aircraft surfaces, comprising an array of optical fibres which are mounted flush with an outer surface of an aircraft skin, and an intermediately located electromagnetic radiation emitter which is provided by an optical fibre. In use radiation is emitted by the emitter generally outwardly of the aircraft surface, and the layer of accreted ice diffuses the emitted radiation scattered and reflected. The diffused radiation is detected by the sensors, and the spatial distribution of the detected intensity diffused radiation about the emitter can be used to calculate the thickness of the layer of ice and the type of ice.

Abstract: A system for a virtual frost sensor is disclosed including a method for operating the virtual frost sensor. The method includes determining a first temperature indicative of a fluid upstream of the component and determining a second temperature indicative of a fluid downstream of the component. The method also includes sensing at least one engine parameter and determining a first parameter as a function of the at least one engine parameter. The method further includes determining a third temperature indicative of a temperature associated with the engine component as a function of the first temperature, the second temperature, and the first parameter.

Abstract: Apparatus, methods, and systems for ice detection, e.g., ice detection using a reference probe and a collection probe to detect ice formation on an aircraft.

Abstract: The invention relates to a method and an apparatus for determining the risk of ice deposition due to precipitation. According to the invention the measurements of precipitation known so far are combined with measurements of the actual amount of ice deposited from the precipitation. Said measurements are combined in a combination unit that is able to receive further parameter information, eg the amount and type of anti-icing liquid. Compared to previously a considerably more reliable determination of the risk of ice deposition is accomplished, eg on the wing of an aeroplane applied with anti-icing liquid, and so is reliable determination of the holdover time, HOT, during which one can be sure that the aeroplane is free from ice in the current weather conditions.

Abstract: A dual channel inflight ice detection system to detect ice accretion on an aircraft surface by illuminating an ice collecting surface mounted on an aircraft with linear polarized light. The backscattered light is acquired in two light conductors one with polarization sensitivity aligned to the transmitted light and the second with polarization sensitivity orthogonal to the first. The presence of ice is determined by the change in the ratio of light intensities in the two light conductors.

Abstract: A dual channel inflight ice detection system to detect ice accretion on an aircraft surface by illuminating an ice collecting surface mounted on an aircraft with linear polarized light. The backscattered light is acquired in two light conductors one with polarization sensitivity aligned to the transmitted light and the second with polarization sensitivity orthogonal to the first. The presence of ice is determined by the change in the ratio of light intensities in the two light conductors.

Abstract: A road-ice detecting sensor includes: a temperature sensing member of T shape made of a highly heat conductive metal, having a temperature sensor to be grounded onto a road and a fin part erected from this temperature sensor; an optical fiber having an FBG bonded onto the fin part of the temperature sensing member; and a case having a heat insulating member surrounding the fin part of the temperature sensing member and the optical fiber. A plurality of number of the read-ice detecting sensors are installed on a road, connected to one another via an optical cable. Pulsed light is launched into one of the ends of the optical cable, and beams of reflected light from the respective road-ice detecting sensors are received to measure the road temperature.

Abstract: A sensor system comprises a first sensor, a second sensor, and circuitry. The first sensor collects non-frozen liquid with a first collection efficiency, but does not collect frozen liquid. The second sensor collects non-frozen liquid with a second collection efficiency and also collects frozen liquid. The first collection efficiency and the second collection efficiency are substantially equivalent. The circuitry maintains the first sensor and the second sensor at a substantially constant temperature. The circuitry determines a measurement of the frozen liquid based on maintaining the first sensor and the second sensor at the substantially constant temperature. In some examples, multiple sensor systems can be used in combination to improve the accuracy of the measurement.

Abstract: The accretion of ice on an aerodynamic surface is predicted by identifying predetermined atmospheric parameters relevant to ice formation in a particular fluid environment. Then the behaviour of individual fluid elements is simulated based on the identified parameters to create a model of the ice accretion.

Abstract: Ice accretion on a probe is detected by determining the change of frequency of a vibrating type ice detector or sensor as ice starts to build up. The rate of change of frequency is determined and is combined with parameters including air velocity and air temperature for providing a signal that indicates liquid water content in the airflow as well as ice accretion on the ice detector.

Abstract: The invention proposes an ice detector for detecting ice accretion on the surface of a structure subject to icing, said ice detector comprising a sensing element protruding into the airflow and supported relatively to a surface of said object by a strut upon which it is mounted, characterized in that said sensing element has an evolutionary profile along the longitudinal axis adapted to the spectral distribution of the icing conditions. Said sensing element is adapted to the profile of ice distribution on the aircraft and allows detection on a large spectrum of droplet sizes.

Abstract: An ice detector has a pair of probes, each of which is used for determining the accretion of ice thereon. One of the probes in the assembly is configured so the smaller droplets of supercoooled water are inertially separated and flow away from the one probe. The ice accretion on the one probe is primarily from large (50 microns or greater) supercooled droplets. The ice accreting on the one probe is therefore biased to supercooled large droplets. The probes are connected to detection circuitry that will determine the ratio of the rates of icing between the probes so the presence of supercooled large droplets can be determined. In one form, a flow guide is arranged to create an airflow that carries smaller droplets past one of the probes without impinging on the probe, but the higher inertia, supercooled large droplets will impinge on that one probe.

Abstract: An apparatus and a method for local measurement of an icing factor for atmospheric air containing supercooled water, and wherein the apparatus comprises at least one surface element made of a material suitable for ice in atmospheric air to freeze on, and said surface element having a predetermined surface area, and wherein the apparats further comprises means that are configured for moving the surface element through the atmospheric air at a predetermined rate and for a predetermined period of time, and wherein means am also provided that are configured for measuring the thickness or mass of the ice frozen fast onto the surface element after the predetermined time interval during which the element is moved through the atmospheric air.

Abstract: A contaminant sensor is provided which has an ultrasonic guided wave transducer that is bonded to a wall in which the ultrasonic energy is transmitted. A detector reflector is provided at a selected distance from the transducer, which will reflect signals that are affected or changed by contaminants collecting on an exposed surface of the wall. A self test reflector is positioned closely adjacent to the transducer and provides a reflected signal that is substantially unaffected by contaminants on the exposed surface of the wall, but which reflects signals only when the transducer assembly is functioning properly, and is properly bonded to the wall. The signal that is reflected by the self test reflector changes when the bond loosens. The receiver is activated right after transmission ceases to determine if the transmitter is operating.

Abstract: Ice accretion on a probe is detected by determining the change of frequency of a vibrating type ice detector or sensor as ice starts to build up. The rate of change of frequency is determined and is combined with parameters including air velocity and air temperature for providing a signal that indicates liquid water content in the airflow as well as ice accretion on the ice detector.

Abstract: A method of generating, for an aircraft, a total air temperature compensated for recovery or deicing heater error includes measuring a total air temperature with a total air temperature probe. A local angle of attack for the total air temperature probe is determined. Then, a corrected total air temperature, compensated for recovery or deicing heater error, is generated as a function of the measured total air temperature and the determined local angle of attack for the total air temperature probe.

Abstract: A contaminant sensor is provided which has an ultrasonic guided wave transducer that is bonded to a wall in which the ultrasonic energy is transmitted. A detector reflector is provided at a selected distance from the transducer, which will reflect signals that are affected or changed by contaminants collecting on an exposed surface of the wall. A self test reflector is positioned closely adjacent to the transducer and provides a reflected signal that is substantially unaffected by contaminants on the exposed surface of the wall, but which reflects signals only when the transducer assembly is functioning properly, and is properly bonded to the wall. The signal that is reflected by the self test reflector changes when the bond loosens. The receiver is activated right after transmission ceases to determine if the transmitter is operating.

Abstract: An integrated air data probe capable of measuring pressure, temperature, relative humidity, turbulence, heading, air speed, the presence of ice, and other relevant measurements for use in building a real time map of the aircraft flying conditions. The probe is attached to the external surface of an airplane such as the wing, fuselage or empannage and is adapted to collect and relay these measurements to a receiving station. By utilizing these probes on numerous airplanes, real time data from numerous data points can be mapped to provide pilots and airlines complete information regarding flying conditions. Additionally, the probe includes a recessed surface for detecting the presence, thickness, and continued buildup of ice by mounting the recessed surface directly into the airflow. One or more light beams are passed over and parallel to the recessed surface, and if ice is present the beams are interrupted.

Abstract: The present invention is an optical ice detection probe capable of detecting the presence, thickness and continued buildup of ice. The invention works by attaching the probe to the external surface of an airplane such as the wing, fuselage or empannage. The probe has a recessed surface, which is mounted to face directly into the airflow. One or more beams are passed over and parallel to the recessed surface. These beams can be of any useful wavelength, however for best results visible, infrared or ultraviolet beams should be used. Ice on the recessed surface interrupts the beams thereby indicating the presence of ice. If two or more beams are used, then each beam emitter is paired with a beam detector and the corresponding beam detector only detects the beam from that emitter. This can be accomplished by numerous methods.