Abstract: The invention relates generally to gas turbine engines used for electrical power generation. More specifically, embodiments of the present invention provide ways for improving gas turbine engine performance by reducing ice build-up on the inlet filter housing through heated air injection.

Abstract: A system for detecting icing includes an optical sensor configured to view at least a portion of an exterior surface or component of an aircraft and to output sensor data indicating at least one optical quality of the exterior surface or component, and an icing detection module. The icing detection module is configured to receive the sensor data from the optical sensor, compare the sensor data to predetermined quality data indicating at least one known optical quality of the exterior surface or component without icing, and determine the presence of icing on the exterior surface or component based on a difference between the sensor data and the predetermined quality data.

Abstract: A system detects ice on a surface. The system comprises an ultraviolet (UV) light source configured to project light primarily in the UV-A spectrum onto the surface. The system further comprises an optical device configured to capture an image of the surface while the light primarily in the UV-A spectrum is projected by the UV light source. The system further comprises a control device communicatively coupled to the optical device. The control device is configured to receive the image from the optical device and determine whether or not ice is present on the surface based respectively on whether or not visible light induced by the light projected by the UV light source is captured in the image.

Abstract: Various embodiments include detection systems adapted to monitor at least one physical property of a component in a turbomachine. In some embodiments a detection system includes at least one sensor configured to be affixed to a component of a turbomachine, the at least one sensor for sensing information regarding at least one physical property of the turbomachine component during operation of the turbomachine, a signal converter communicatively coupled to the at least one sensor and at least one RF communication device configured to be affixed to a stationary component of the turbomachine, the radio frequency communication device configured to communicate with the at least one signal converter via an RF antenna coupled to the signal converter.

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: An ice detection system comprising a first group of sensors and a second group of sensors. The first group of sensors is located in a first group of locations on an aircraft. The first group of sensors in the first group of locations is configured to detect a first type of icing condition for the aircraft. The second group of sensors is located in a second group of locations on the aircraft. The second group of sensors in the second group of locations is configured to detect a second type of icing condition for the aircraft.

Abstract: A flight display for an aircraft includes a virtual ice accretion meter having a liquid water content portion and an ice thickness portion. A method for determining ice accretion includes integrating over a time period a constant K multiplied by a liquid water content (LWC) and true airspeed (TAS).

Abstract: A method and apparatus are present for monitoring a runway. Data is received about the runway from a number of sensors associated with an aircraft while the aircraft performs an operation on the runway. A number of conditions are identified for the runway using the data received from the number of sensors.

Abstract: Methods and systems for detecting icing or incipient icing conditions external to a vehicle (100) are disclosed. An apparatus in accordance with one embodiment of the invention includes a temperature sensor (120) configured to direct a first signal corresponding to a temperature of an airstream, and a water content sensor (130) configured to direct a second signal corresponding to a water content of the airstream. A processing unit (140) can receive the first and second signals and, based on at least the first and second signals, provide an indication (150) when at least the first and second signals taken together correspond to an at least incipient icing condition. Accordingly, the system can be installed on aircraft to provide notice to the crew of incipient or existing icing conditions.

Abstract: An icing detection subsystem for an aircraft turbine engine is presented. The icing detection subsystem includes a plurality of air pressure sampling ports formed within structure that surrounds a rotating component of the aircraft turbine engine. The subsystem also includes a pressure sensor arrangement coupled to the plurality of air pressure sampling ports to obtain air pressure measurements for the plurality of air pressure sampling ports. A processing module is coupled to the pressure sensor arrangement to analyze the air pressure measurements over time during operation of the aircraft turbine engine, and to generate an alert when at least one characteristic of the air pressure measurements over time is indicative of the presence of ice in the aircraft turbine engine.

Abstract: An automatic headlamp control system for a vehicle which has an image sensor having a forward field of view that captures image data of a scene forward of the vehicle. The image processor processes the image data and detects objects of interest. A controller is responsive to the image processing to control a beam illumination state of the headlamps of the equipped vehicle. The controller is operable to detect at least a partial blocking condition at the image sensor and is operable to limit switching to a different beam illumination state in response to a signal indicative of an outside temperature at the equipped vehicle being below a threshold temperature level.

Abstract: There is disclosed a system comprising Raman spectroscopy used to detect key characteristics of ice formation on aircraft wings and engines in real time. This disclosure provides a method and apparatus for early detection of icing. The disclosed apparatus is suitable for use in aircraft, boats, oil rigs, wind turbines, and the like.

Abstract: Apparatus and a method are described for prospecting for water ice on heavenly bodies with the apparatus consisting of site preparation tools and a water ice detector unit. The apparatus is attached at the end of any robotic arm equipped lander or rover spacecraft; for instance, lander designs such as Mars Phoenix or rover designs such as Mars Spirit and Opportunity. Supported on an internal, moveable carriage, the apparatus is also incorporated into smaller, dedicated water ice detection rover spacecraft. The water ice detection unit inserts electrodes into or against a potential water ice deposit and confirms the presence of water ice by making combination impedance and thermal conductivity measurements.

Abstract: The invention relates to a method and a system for monitoring the temperature of an aircraft, in which at least one camera connected to a first processing unit, for imaging detection of at least one region of the substantially upwardly-pointing outer surface of the aircraft, detects an images once, several times, or at regular intervals and transmits this to the first processing unit, wherein the light spectrum which may be detected by the camera lies substantially in the infrared range and the first processing unit determines the temperatures of substantially all the pictorially detected locations or has these determined by a downstream signal-processing device, in each case compares the temperature for individual locations with a predetermined maximum design temperature for the relevant location, and if the maximum design temperature is exceeded, generates a warning signal.

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: An automatic recycling ice detector includes a sensor for sensing the formation of ice on an aircraft surface and a heater for melting the detected ice. The detector also includes a timing circuit for indicating the time to melt any detected ice and automatically recycling the detector when the ice is melted. A computer including a look up table or the like are provided for measuring and indicating the thickness of the accumulated ice based on a relationship between melting time and thickness.

Abstract: An optical system for detecting ice and water on the surface of an aircraft includes an elongated transparent optical element having first and second end portions. A light source and light detector are disposed in one end of the optical element and a reflective surface is disposed in the opposite end portion. The reflective surface defines a critical angle and reflects light from the light source to the light detector when the critical angle is in contact with air and refracts the light toward the external environment when the reflective surface is in contact with ice or water. The system may also incorporate an optical element wherein the reflective surface includes a continuous array of convex elements extending outwardly from and across one end of the optical element and wherein each of the convex elements defines a critical angle.

Abstract: A method for detecting ambient conditions conducive to ice formation. The method includes the steps of measuring at least one parameter selected from a group of parameters consisting of a static pressure, a total pressure, a total temperature, a dew point temperature, and a liquid water content, and determining whether ambient conditions are conducive to ice formation based on the measured parameter.

Abstract: In one embodiment, a system to detect one or more environmental conditions in proximity to a surface comprises a first metamaterial environmental sensor module proximate the surface. The environmental sensor comprises a metamaterial-based electrically resonant structure having a resonance frequency which varies in response to changes in at least one of a humidity proximate the sensor module, a temperature proximate the sensor module, or the presence of a chemical or biological agent proximate the sensor module. The system further comprises a remote receiver to receive an electromagnetic signal comprising the signal generated by the electrically resonant structure and a signal analysis module to determine an environmental condition such as humidity, temperature, pre-ice conditions, ice, chemicals or biological species from the at least one environmental condition signal. Other embodiments may be described.

Abstract: An automatic recycling ice detector includes a sensor for sensing the formation of ice on an aircraft surface and a heater for melting the detected ice. The detector also includes a timing circuit for indicating the time to melt any detected ice and automatically recycling the detector when the ice is melted. A computer including a look up table or the like are provided for measuring and indicating the thickness of the accumulated ice based on a relationship between melting time and thickness.

Abstract: An icing detector is disclosed for detecting presence of ice in static air. An exemplary detector includes an ice collecting surface; a light emitter for emitting a light beam crossing an ice collecting surface, having a prismatic light manipulating window for internally-reflecting the light beam when no ice is present on the ice collecting surfaces, and externally-refracting the light when clear ice is present on the ice collecting surface, wherein the ice collecting surface is oriented to cause standing water to be directed away from the prismatic light manipulating window by gravity; a light sensor in a path of the reflected light; and an annunciator coupled to the light sensor for annunciating the presence of ice when light is sensed by the light sensor.

Abstract: An optical system for detecting ice and water on the surface of an aircraft includes an elongated transparent optical element having first and second end portions. A light source and light detector are disposed in one end of the optical element and a reflective surface is disposed in the opposite end portion. The reflective surface defines a critical angle and reflects light from the light source to the light detector when the critical angle is in contact with air and refracts the light toward the external environment when the reflective surface is in contact with ice or water. The system may also incorporate an optical element wherein the reflective surface includes a continuous array of convex elements extending outwardly from and across one end of the optical element and wherein each of the convex elements defines a critical angle.

Abstract: A probe for measuring the thickness of frost accretion on a surface includes a plurality of measuring stages that are stacked substantially orthogonally to the base of the probe. Each measuring stage has an emitter that emits a light beam that is substantially parallel to the base and a receiver that receives the light beam after reflection on the frost.

Abstract: A method for detecting ambient conditions conducive to ice formation. The method includes the steps of measuring at least one parameter selected from a group of parameters consisting of a static pressure, a total pressure, a total temperature, a dew point temperature, and a liquid water content, and determining whether ambient conditions are conducive to ice formation based on the measured parameter.

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 and method for detecting ice formation on the surface of an aircraft includes a small rotatable disc disposed on and flush with a surface of a aircraft wing and/or stabilizer and a DC motor for rotating the disc. The disc is rotated periodically and the peak current which is directly proportional to the torque required to break any ice is monitored. When the torque exceeds a pre-selected amount a warning is sounded in the cockpit. If the torque required to rotate the disc increases a second warning is given and the amount of ice accumulation is calculated. In one embodiment of the invention, a stall warning system is automatically modified to increase the margin to accommodate for the increase due to ice accumulation.

Abstract: An electric field sensor may be used to detect accumulation of frozen material. In one embodiment, an e-field system includes a first electrode, a second electrode located at a distance from the first electrode, the second electrode forming a capacitive element with the first electrode, wherein a gap is present between the first and second electrodes, and an electric field sensor having an electrode terminal coupled to the first electrode and providing an electric field output value representative of an amount of frozen material located in the gap between the first and second electrodes. The system may also include a first insulator adjacent the first electrode and outside the gap, and a conductive layer adjacent the first insulator, where the first insulator is between the first electrode and the conductive layer, and where a shield output of the electric field sensor is coupled to the conductive layer.

Abstract: A method for transmitting environmental conditions information, comprising, receiving at least some environmental conditions data and/or information, scaling the received environmental conditions data and/or information such that a scaled environmental conditions value is determined for a particular vehicle, and transmitting, in response to a request for environmental conditions information, at least one of the data and/or information relating to the environmental conditions and the dynamic vehicle information.

Abstract: An ice detection system that detects the onset of ice accreation on an aircraft's external surfaces, continuously measures its thickness and growth time history and provides the type of ice, glaze or rime, is disclosed along with an independent way to confirm that the contaminant is known to be ice and only ice. Total impedance data, thermal conductivity value and complex dielectric properties are used to discriminate between ice, water, deicing fluid and snow with measurements made by low cost, low power consumption, low profile, miniature electronic chips, components and devices collocated together on the external surface in a thin pliant patch that does not effect the airflow about the aircraft. The ice detection system provides ice accreation data and warning signals to displays and aural signaling devices in the cockpit for the pilot and to the control console of a ground controller flying the aircraft if it is unmanned.

Abstract: An optical system for detecting ice and water on the surface of an aircraft includes an elongated transparent optical element having first and second end portions. A light source and light detector are disposed in one end of the optical element and a reflective surface is disposed in the opposite end portion. The reflective surface defines a critical angle and reflects light from the light source to the light detector when the critical angle is in contact with air and refracts the light toward the external environment when the reflective surface is in contact with ice or water. The system may also incorporate an optical element wherein the reflective surface includes a continuous array of convex elements extending outwardly from and across one end of the optical element and wherein each of the convex elements defines a critical angle.

Abstract: Methods and systems for detecting icing or incipient icing conditions external to a vehicle (100) are disclosed. An apparatus in accordance with one embodiment of the invention includes a temperature sensor (120) configured to direct a first signal corresponding to a temperature of an airstream, and a water content sensor (130) configured to direct a second signal corresponding to a water content of the airstream. A processing unit (140) can receive the first and second signals and, based on at least the first and second signals, provide an indication (150) when at least the first and second signals taken together correspond to an at least incipient icing condition. Accordingly, the system can be installed on aircraft to provide notice to the crew of incipient or existing icing conditions.

Abstract: An optical system for detecting ice and water on the surface of an aircraft includes an elongated transparent optical element having first and second end portions. A light source and light detector are disposed in one end of the optical element and a reflective surface is disposed in the opposite end portion. The reflective surface defines a critical angle and reflects light from the light source to the light detector when the critical angle is in contact with air and refracts the light toward the external environment when the reflective surface is in contact with ice or water. The system may also incorporate an optical element wherein the reflective surface includes a continuous array of convex elements extending outwardly from and across one end of the optical element and wherein each of the convex elements defines a critical angle.

Abstract: A system for detecting and discriminating between water and ice formation on a number of objects, such as aircraft or roadways is described. The system includes an optical element or sensor adapted to receive at least first and second wavelengths of light from a multi-wavelength light source and for outputting attenuated versions of the first and second wavelengths of light. A detector senses and converts the attenuated versions of the first and second wavelengths of light to electrical signals proportional to the light intensities of the first and second wavelengths of light. A processor is coupled to receive and process the electrical signals for determining one or more light intensity values and for actuating one or more indicators corresponding to one of a number of predetermined states of operation of the optical element, including a normal state of operation, a rain state of operation and/or an ice state of operation.

Abstract: Apparatus, methods, system and devices for monitoring road surface temperature to detect hazardous road surface conditions. An indicator provides the sensed road surface temperature and hazardous road condition warning to a driver while a tail light interface automatically produce a tail light signal to warn drivers traveling behind the vehicle when a hazardous condition is detected. In an embodiment, the system includes a vehicle engine retardation system interfaced with the hazardous road condition warning system. When the retardation system is in use and hazardous road surface conditions are detected the controller automatically produces the brake light signal unless a tail light control switch is used to manually deactivating the automatic tail light flashing signal when the vehicle is traveling in a state that does not allow alternative control of the brake lights.

Abstract: An Aviation Weather Awareness and Reporting Enhancements (AWARE) system provides situational awareness by effectively filtering, analyzing and visualizing aviation weather data and specific hazard alerts in preflight, in-cockpit and controller applications. The AWARE system includes a temporal-spatial databases that filters weather data and a Bayesian network that assesses specific hazards in the filtered weather data in the context of pilot preferences, aircraft properties and airport properties. The filtered weather data and hazard alerts are then displayed on a client.

Abstract: A temperature measuring device is provided which measures the total temperature T1 of an airflow based on the measured temperature T of the airflow flowing over the surface of an approximately blade-shaped casing arranged within the airflow flowing into an engine of the aircraft. The shape of the casing is set such that lumps of ice and snow, which may form on a surface of the casing and which may thereafter detach from the casing and strike the engine, detach at a stage of growth at which they do not cause damage to the engine.

Abstract: A method for transmitting environmental conditions information, which includes receiving at least some environmental conditions information, scaling the received information such that a scaled environmental conditions value is determined for a particular vehicle, receiving an environmental conditions threshold value, comparing the scaled value to the received threshold value, determining whether the scaled value is greater than the received threshold value, and transmitting, if the scaled value is greater than the received threshold value, at least some of the information.

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 system (24) for detecting an air disturbance in front of an aircraft (10) has a controller (26) that is coupled to an image detector (40). Image detector (40) generates an image signal corresponding to heated air in front of the aircraft (10). The air in front of the aircraft (10) is heated by direct high energy beams such as microwave beams (16, 18) from a respective microwave antenna (12, 14). By monitoring the image, the presence of an air disturbance may be determined. Position adjusters (30, 32) may be used to adjust the position of the beams (16, 18) by controlling the position of antennas (12, 14). The position of the beam is preferably maintained a predetermined distance (d) in front of the aircraft (10) so that an evasive maneuver may be performed.

Abstract: An ice detection warning system mountable on board an aircraft for inflight monitoring of the airspace ahead of the aircraft comprises: a first plurality of optical elements configured to direct a pulsed laser beam at a first wavelength from a laser source into the airspace ahead of the aircraft; a second plurality of optical elements configured to separate received backscattering of light from the laser beam into a plurality of predetermined wavelengths; a plurality of light detectors for detecting the light of the separated plurality of wavelengths, respectively, and generating respectively corresponding plurality of electrical signals representative of the light detected thereby; and a processor for processing the plurality of electrical signals to determine if airspace conditions ahead of the aircraft are likely to cause ice accretion on the surface of the aircraft, and for generating a warning indicative thereof.

Abstract: An aerial sampler system includes an enclosure, a transfer system, and a measurement system. The enclosure is connected to an external surface of an aerial vehicle and receives atmospheric flow from the external surface of the aerial vehicle. The enclosure also directs at least some of the atmospheric flow into an aperture in the external surface. The transfer system transfers some of the atmospheric flow from the aperture to a measurement system. The measurement system is internal to the external surface of the aerial vehicle and measures atmospheric trace gases in the atmospheric flow.

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: A method and apparatus for measuring the thickness of ice on an aircraft member is disclosed. In the preferred embodiment, the apparatus is mounted beneath an aircraft member surface. The apparatus includes transducers for transmitting ultrasonic signals through the aircraft member and ice at predetermined applied voltages and frequencies. The apparatus measures the current and phase angle relative to voltage associated with each transducer and frequency. The apparatus calculates the impedance of the transducer transmitting through aircraft member and any ice accumulation from the applied voltage and measured current and phase angle relative to voltage at each of the predetermined frequencies. The apparatus then computes the ice thickness by determining the frequencies where the impedance is a peak. The invention also broadly comprises an apparatus and a method for the detection of ice on an aircraft member.

Abstract: An ice detection warning system mountable on board an aircraft for inflight monitoring of the airspace ahead of the aircraft comprises: a first plurality of optical elements configured to direct a pulsed laser beam at a first wavelength from a laser source into the airspace ahead of the aircraft; a second plurality of optical elements configured to separate received backscattering of light from the laser beam into a plurality of predetermined wavelengths; a plurality of light detectors for detecting the light of the separated plurality of wavelengths, respectively, and generating respectively corresponding plurality of electrical signals representative of the light detected thereby; and a processor for processing the plurality of electrical signals to determine if airspace conditions ahead of the aircraft are likely to cause ice accretion on the surface of the aircraft, and for generating a warning indicative thereof.

Abstract: A method and apparatus for measuring the thickness of ice on an aircraft member is disclosed. In the preferred embodiment, the apparatus is mounted beneath an aircraft member surface. The apparatus includes transducers for transmitting ultrasonic signals through the aircraft member and ice at predetermined applied voltages and frequencies. The apparatus measures the current and phase angle relative to voltage associated with each transducer and frequency. The apparatus calculates the impedance of the transducer transmitting through aircraft member and any ice accumulation from the applied voltage and measured current and phase angle relative to voltage at each of the predetermined frequencies. The apparatus then computes the ice thickness by determining the frequencies where the impedance is a peak. The invention also broadly comprises an apparatus and a method for the detection of ice on an aircraft member.

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 road surface monitoring system for monitoring the condition of a road surface wherein at least one sensor unit is interchangeably provided in a sealed container disposed below the road surface and a power source is provided to power the sensor unit, and a communications device is provided to obtain measurement and/or monitoring data from the at least one sensor unit and to provide control signals to the at least one sensor unit, whereby an inexpensive and readily maintainable system is provided.

Abstract: An ice detector for an aircraft comprises a strut and probe assembly, and it is positioned on the aircraft so that the pressure field around the ice detector causes a lower temperature region on the probe assembly compared to the aircraft. Ice will therefore form on the probe assembly before it forms on the aircraft to provide an early warning of icing conditions near freezing temperatures.

Abstract: The present invention comprises a system and method for detecting icing conditions in a multi-mode aircraft by indirectly detecting ice accretion through the measurement of aircraft performance related characteristics. Indirect characteristics are used, sometimes in additional to traditional icing sensor input, because it is difficult to safely and effectively position icing sensors in aircraft that may fly in the hover mode or the fixed wing mode as well as modes in between. Typical indirect characteristics might include thrust and rotor response for a given torque. This information is compared to a model of the expected aircraft performance to determine if icing is likely to take place. For example, decreased thrust or lift for a given torque may indicate the onset of icing. Inputs from the traditional icing sensors may also be employed as additional useful, predictive data.

Abstract: An ice detector for an aircraft comprises a strut and probe assembly, and it is positioned on the aircraft so that the pressure field around the ice detector causes a lower temperature region on the probe assembly compared to the aircraft. Ice will therefore form on the probe assembly before it forms on the aircraft to provide an early warning of icing conditions near freezing temperatures.