WO2013091902A1 - System and method for detecting adverse atmospheric conditions ahead of an aircraft - Google Patents
System and method for detecting adverse atmospheric conditions ahead of an aircraft Download PDFInfo
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- WO2013091902A1 WO2013091902A1 PCT/EP2012/051798 EP2012051798W WO2013091902A1 WO 2013091902 A1 WO2013091902 A1 WO 2013091902A1 EP 2012051798 W EP2012051798 W EP 2012051798W WO 2013091902 A1 WO2013091902 A1 WO 2013091902A1
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- brightness temperature
- adverse condition
- infrared
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Classifications
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N5/00—Details of television systems
- H04N5/30—Transforming light or analogous information into electric information
- H04N5/33—Transforming infrared radiation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/38—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system
- G01S19/39—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system the satellite radio beacon positioning system transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/53—Determining attitude
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S3/00—Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received
- G01S3/78—Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received using electromagnetic waves other than radio waves
- G01S3/781—Details
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N23/00—Cameras or camera modules comprising electronic image sensors; Control thereof
- H04N23/90—Arrangement of cameras or camera modules, e.g. multiple cameras in TV studios or sports stadiums
Definitions
- the present invention relates to an apparatus and method for detecting adverse atmospheric conditions ahead of an aircraft.
- Such conditions may include volcanic clouds and so the apparatus may, for example, detect sulphur dioxide and particles such as volcanic ash, wind-blown dust and ice particles.
- the invention also extends to a method of producing such an apparatus or essential components thereof.
- Modern civil aircraft typically cruise at between 30,000 and 40,000 feet, which places them above most weather systems, except for towering cumulonimbus clouds and their associated electrical storms. As these can present a hazard, most airliners are equipped with weather radar that can detect them and enable the pilot to take avoiding action. However, there remain a number of adverse atmospheric conditions that are desirable to detect for which suitable avionic systems are not presently available. These include volcanic ash, toxic gases such as sulphur dioxide gas, wind-blown dust and ice particles.
- Volcanic clouds contain silicate ash and gases that are hazardous to aviation.
- Several encounters between jet aircraft and volcanic ash have resulted in significant damage due to ingestion of ash into the hot parts of the engine, subsequent melting and fusing onto the turbine blades. Ash can also block the pitot static tubes and affect sensitive aircraft instruments, as well as abrade the leading edges of parts of the airframe structure.
- Volcanic gases principally sulphur dioxide (S0 ), whilst less dangerous to aircraft than volcanic ash, do pose a hazard in themselves. In addition, their presence can be used as an indicator of volcanic ash as these substances are often co-located and are transported together by atmospheric winds. S0 2 clouds from volcanices will react with water vapour in the atmosphere to produce sulphuric acid which can damage aircraft.
- S0 sulphur dioxide
- Water vapour occurs in copious amounts in volcanic clouds, either through entrainment of ambient air or from water from the volcanic source (e.g. sea water is a common source for volcanoes on islands or in coastal regions). Once in the atmosphere, the water vapour can condense on ash which act as nuclei, rapidly forming ice with a much smaller radius than ice in normal meteorological clouds. These abundant, small-sized ice particles are hazardous to aircraft because the rapid melting of the ice when in contact with the hot engines releases the ash nuclei which then fuse onto the turbine blades, affecting the engine performance and potentially causing the engine to stop.
- Jet aircraft at cruise altitudes i.e. above 15,000 feet
- travel rapidly >500 km hr "1
- a suitable detection method must be able to gather information rapidly and provide an automated alert and be capable of distinguishing volcanic substances from other substances in the atmosphere (e.g. meteorological clouds of water and ice).
- US 5654700 proposes a volcanic cloud detection system which displays the position of a volcanic cloud relative to the aircraft's position and thereby enables the aircraft to route around the cloud.
- the system operates by comparing the absolute and relative values of brightness temperatures detected at a number of specific infrared wavelengths to certain threshold values.
- these threshold values are determined, except that they are calculated using a microprocessor and depend on the altitude and attitude of the aircraft.
- a method of detecting an adverse condition in the atmosphere ahead of an aircraft in flight comprising: - a) creating a model of the atmosphere based on simulation of infrared radiative transfer characteristics of a clear atmosphere combined with infrared radiative transfer characteristics of the adverse condition; b) using an infrared sensor mounted on the aircraft, determining a value corresponding to the brightness temperature at a given frequency as viewed ahead of the aircraft;
- step (b) determine whether the brightness temperature value determined in step (b) is indicative of the atmosphere ahead of the aircraft having the adverse condition
- step (c) where the adverse condition is indicated in step (c), providing an alert to the presence of the adverse condition.
- the brightness temperature value determined in step (b) will typically be at a frequency that is characteristic of the adverse condition.
- brightness temperature values may be determined at a plurality of frequencies corresponding to a single adverse condition or to a plurality of adverse conditions. For example, they may relate to different substances present in the atmosphere. These may relate, as discussed above, to a common underlying cause, such as a volcanic eruption.
- the present invention processes brightness temperature values using data obtained from a radiative transfer model of the atmosphere.
- a radiative transfer model of the atmosphere Such a model can be created that provides accurate data corresponding to views from an aircraft at any altitude and taking into account its attitude (e.g. pitched up or down). This is important because it is known that the background temperature varies significantly depending on whether the aircraft is directed towards space or the earth for example.
- a model can be created to cover a range of infrared frequencies and so the method is readily applicable to the detection and analysis of brightness temperatures at a number of frequencies. Likewise, it is applicable to the detection of a number of adverse conditions, or at a plurality of frequencies which are collectively indicative of a given adverse condition. For example, as is known from US 5654700, a pair of brightness temperatures relating to different frequencies may be compared and an indication of an adverse condition provided if they differ by more than a given amount.
- the radiative transfer model may be highly detailed and therefore large and therefore it will often be impracticable to store the model itself in any practical apparatus. Furthermore, the model itself will contain far more data than is required to perform step (c). Therefore, preferably data derived from the model is stored in memory and said data is used in the determination of step (b).
- the data is preferably stored as a look-up table, which may, for example, be indexed by aircraft altitude and attitude. Where a plurality of frequencies are used, it will also be indexed by frequency.
- the data comprises threshold values indicative of the presence of the adverse condition and in particular an alert is provided if a function of the brightness temperature exceeds the threshold value obtained from the look-up table for the altitude and attitude of the aircraft and for the frequency(ies) at which the brightness
- the threshold values can also be determined to allow for statistical variation and en-or so that a balance is struck between sensitivity and false alarms.
- the function may comprise a difference between the brightness temperature at a first frequency and the brightness temperature at a second frequency.
- the magnitude of the threshold value may then indicate a minimum difference between the measured brightness temperatures that is regarded as indicating, to an appropriate level of confidence, the presence of an adverse condition.
- brightness temperature value is used to indicate a quantity that corresponds, at least substantially, in a known manner, to the actual brightness temperature. Needless to say, units of measurement are arbitrary.
- brightness temperature values need not have a linear relation to brightness temperature.
- the invention also extends to at least one software product comprising instructions which when executed by a computer will configure the computer to carry out the above described method of detecting an adverse condition in the atmosphere ahead of an aircraft in flight.
- the software product may be a physical data carrier or signals transmitted from a remote location.
- the software product may be a single software product that configures the computer to carry out the complete method. Or, it may comprise more than one software product, each software product comprising instructions which when executed by a computer will cause the computer to carry out a part of the above method, such that the complete method is carried out by the execution of the instructions of all the software products.
- the present invention provides an apparatus for detecting an adverse condition in the atmosphere ahead of an aircraft in flight, the apparatus comprising: a model of the atmosphere derived from the simulation of infrared radiative transfer characteristics of a clear atmosphere combined with infrared radiative transfer characteristics of the adverse condition; and an infrared sensor mountable on an aircraft and arranged to determine a value corresponding to the brightness temperature at a given frequency as viewed ahead of the aircraft; the apparatus being arranged to: use the model to determine whether the determined brightness temperature value is indicative of the atmosphere ahead of the aircraft having the adverse condition, based on the aircraft's altitude and attitude; and to provide an alert to the presence of an adverse condition when an adverse condition is indicated.
- the invention also extends to a method of manufacturing an apparatus for the detection of an adverse condition ahead of an aircraft in flight, the method comprising:
- the data derived from the model may be stored in a look-up table, as discussed above.
- the apparatus preferably is arranged to operate according to the preferred features set out above.
- the invention also extends to an apparatus provided by this method of manufacture, and in particular to one having the preferred methods of operation.
- the infrared sensors preferably provide spatially resolved data so that an output can be provided in the form of an image.
- the method as set out above may be applied to each pixel in the image. Consequently, the invention may provide not just an indication that an adverse condition exists ahead of the aircraft, but a display indicating its relative position to the aircraft's flight path.
- the sensors of the invention are collocated uncooled
- the data processor is preferably arranged to determine brightness temperatures from the detected infrared radiance.
- Such an apparatus is advantageous in that it detects adverse atmospheric conditions, in particular caused by volcanoes, and visualizes them for the crew of the aircraft.
- the invention is particularly useful for detecting volcanic clouds.
- the present invention can enable the rapid detection of volcanic substances ahead of a jet aircraft at cruise altitudes and the simultaneous detection and discrimination of volcanic ash, S0 2 gas and ice-coated ash particles.
- the invention provides algorithms and processes for converting raw camera data to identify ash, S0 2 gas and ice coated ash.
- the system may also include one or more external blackened shutters against which the infrared sensors are pre-calibrated for providing in-flight calibration values.
- the system provides a statistical alert based on analysis of images determined to show an adverse condition of ash, sulphur dioxide or ice- coated ash.
- the statistical alert uses spatial and temporal information and can be tuned according to in-flight tests to reduce false-alarms and ensure robustness.
- the system being arranged to detect at least the three volcanic substances (ash, S0 2 and ash coated ice particles) in the air ahead of the aircraft by a remote method, and in addition it is capable of discriminating these from other meteorological clouds of water droplets and ice.
- the system being arranged to detect at least the three volcanic substances (ash, S0 2 and ash coated ice particles) in the air ahead of the aircraft by a remote method, and in addition it is capable of discriminating these from other meteorological clouds of water droplets and ice.
- the invention also more generally provides a system for detecting adverse atmospheric conditions ahead of an aircraft, including a plurality of infrared cameras mounted on the aircraft, wherein: the infrared cameras are adjusted to spatially detect infrared radiance in different bands of infrared light; each camera is connected to an image processing computer that processes and combines the images, wherein each of the cameras is provided with a respective filter adjusted to filter infrared light with a bandwidth corresponding to infrared bandwidth characteristics of an adverse atmospheric condition from a set of adverse atmospheric conditions; and the image processing computer is adapted to identify and display adverse atmospheric conditions, said identifying being based on threshold conditions and using the detected infi-ared radiance and measured parameters including information on the position and/or attitude of the aircraft.
- the present invention provides a system for detecting adverse atmospheric conditions ahead of an aircraft, including a plurality of infrared cameras mounted on the aircraft, wherein: the infrared cameras are adjusted to spatially detect infrared radiance in different bands of infrared light, each camera is connected to an image processing computer that processes and combines the images, and generates video display signals for producing a video display which indicates the position of the adverse atmospheric conditions relative to the aircraft; each of the cameras is provided with a respective filter adjusted to filter infrared light with a bandwidth corresponding to infrared bandwidth characteristics of an adverse atmospheric condition from a set of adverse atmospheric conditions; the image processing computer is adapted to identify adverse atmospheric conditions, said identifying being based on threshold conditions and using the detected infrared radiance, data from a look-up table and measured parameters including information on the position and/or attitude of the aircraft; and the image processing computer is further adapted to display the identified adverse atmospheric conditions as a spatial image on a display.
- the present invention provides a method for detecting adverse atmospheric conditions ahead of an aircraft and displaying said adverse atmospheric conditions, comprising spatially detecting infrared radiance in different bands of infrared light using a plurality of infrared cameras; and, for each camera: i) Filtering the infrared radiation with a filter adjusted to filter infrared light with a bandwidth corresponding to infrared bandwidth characteristics of an adverse atmospheric condition in a set of adverse atmospheric conditions; ii) identifying likely occurrences of adverse atmospheric conditions based on threshold conditions and using the detected infrared radiance, data from a look-up table and measured parameters including information on the position and/or attitude of the aircraft; and iii) processing the identified likely occurrences of adverse atmospheric conditions to create a spatial image.
- the method further comprises the step of iv) combining the image with images from other cameras and information on the aircraft flight path.
- the adverse atmospheric conditions preferably include volcanic ash, ice coated ash, water vapour and sulphur dioxide.
- the measured parameters can include pitch angle and ambient temperature.
- the invention provides a system for detecting volcanic clouds ahead of an aircraft, including one or more infrared cameras mounted on the aircraft, the infrared cameras are adjusted to spatially detect infrared radiance in different bands of infrared light, each camera is connected to an image processing computer that process and combines the images, combining them with flight path information from the aircraft and generates video display signals for producing a video display which indicates the position of the adverse conditions relative to the aircraft; characterized in that each of the cameras is provided with a respective filter adjusted to filter infrared light with a bandwidth corresponding to infrared bandwidth characteristics of one of the volcanic species in a set of volcanic species, and that the image processing computer is adapted to identify and display species as a spatial image on a display by means of threshold look-up tables for the respective species mapping thresholds for the infrared radiance, above which species are likely to occur, with measured parameters.
- the invention provides a method for detecting a volcanic cloud ahead of an aircraft and displaying said cloud, processing
- the present invention provides a method of detecting an adverse condition in the atmosphere ahead of an aircraft in flight, comprising: a) utilizing a computer model of the atmosphere based on a simulation of infrared radiative transfer characteristics of a clear atmosphere combined with infrared radiative transfer characteristics of the adverse condition;
- step (b) determine by a processor whether the brightness temperature value determined in step (b) is indicative of the atmosphere ahead of the aircraft having the adverse condition
- step (c) where the adverse condition is indicated in step (c), providing by the processor an alert to the presence of the adverse condition.
- the present invention provides a method of manufacturing an apparatus for the detection of an adverse condition ahead of an aircraft in flight, the method comprising:
- the present invention provides an apparatus comprising a detector array including at least one infrared sensor, a processing unit, and a display unit wherein the apparatus is configured to perform a method of detecting an adverse condition in the atmosphere ahead of an aircraft in flight, the method comprising:
- step (b) determine by the processor whether the brightness temperature value determined in step (b) is indicative of the atmosphere ahead of the aircraft having the adverse condition
- step (c) where the adverse condition is indicated in step (c), providing by the processor an alert to the presence of the adverse condition on the display unit.
- the present invention provides a non-transitory computer readable medium storing computer-exectuable instructions, which when executed by a processor cause the apparatus to perform a method of detecting an adverse condition in the atmosphere ahead of an aircraft in flight, comprising:
- step (b) determine by the processor whether the brightness temperature value determined in step (b) is indicative of the atmosphere ahead of the aircraft having the adverse condition
- step (c) where the adverse condition is indicated in step (c), providing by the processor an alert to the presence of the adverse condition.
- Figure 1 is a schematic diagram of a volcanic cloud detector according to an embodiment of the invention.
- Figure 2 is a schematic diagram illustrating the detector array of Figure 1 mounted
- Figure 3 is a schematic diagram of an infrared camera that forms part of the detector array of the embodiment
- Figures 4(a) to (f) shows an ash cloud on the display of the embodiment
- Figure 5 shows a series of plots of infrared radiance against wave number for the horizontal path ahead of a cruising aircraft at three different altitudes in a clear atmosphere
- Figure 6 shows a diagram of line strengths for the two bands of S0 2 at 8.6 ⁇ and 7.3 ⁇ . The response functions for the filters of the system are also shown.
- embodiment comprises a detector array 1 and its associated electronics 2, a data processing unit 3, memory 4 and a display unit 5 that provides output data to an aircraft pilot.
- Computer instructions for implementing any of the methods described herein are capable of being stored on the memory 4. These instructions can be executed by the processing unit 3.
- detector array 1 comprises five infrared detectors 6, which are infrared sensitive cameras and are located adjacent and parallel to each other within a housing 7.
- a mechanically driven protective shutter 8 is provided, which is closed when the apparatus is not in use. This is blackened and is provided with a heater (not shown) for use in calibration of the camera, as will be explained below.
- the shutter also serves the potpose of providing protection against debris and dirt directed toward the camera during take-off and landing, when the system is deactivated.
- a germanium glass window 9 is located behind the shutter to provide protection from debris while in viewing mode.
- the cameras 6 are located behind the germanium window, with their signal 10 and power 1 1 lines extending from the back of the housing 7.
- the housing 7 also contains the camera electronics and software unit 2 including a frame grabber and related computer hardware.
- the cameras are wide-field-of-view, rapid sampling, imaging, uncooled microbolometer cameras as shown in Fig. 3. Each of these detects a different narrow band (0.5-1.0 ⁇ ) of infrared radiation within the region of 6-13 ⁇ . These enable the detection of ash, water vapour, S0 2 gas and ice coated ash.
- Each camera 6 comprises a housing 12 which contains detector 13, lens 14, and naiTow band filter 15.
- the housing is provided with an infrared transmissive germanium glass window 16 and the window is covered by a camera shutter 17. Infrared radiation from ahead of the aircraft enters the filter 15, is focused through the camera lens 14 and falls on the detector array 13.
- infrared radiation strikes the detector 13, heating it, and thus changing its electrical resistance. This resistance change is measured and processed into temperatures (as described below) which can be used to create an image. Unlike other types of infrared detecting equipment, microbolometers do not require cooling.
- the detector 13 has 640x512 pixels and has a noise equivalent temperature difference of 50 mK (or better) at 300 K in the 10-12 ⁇ region, and provides sampling rates up to 60 Hz. It is sensitive to infrared radiation within the region 6- 13 ⁇ .
- NaiTowband filters 15 are placed over the lens 14 of each camera 6 to restrict spectral content of the radiation that reaches detector 13 to a narrow band.
- Each camera in the array is sensitive to a different band.
- the cameras share the same field of view ahead of the aircraft and therefore, in principle, multiple, simultaneous narrowband infrared images can be acquired by the array 1 in real-time.
- an IR transparent window 16 (e.g. Germanium glass) is attached between the shutter and filter.
- the shutter is temperature controlled and blackened on the side facing the optics.
- a detector electronics module 2 is provided within the housing 7 of the detector array. This contains the components necessary to pre-process the data output from each detector 13.
- the cameras 6 are pre- calibrated prior to installation on the aircraft so that each camera registers the same digital signal when exposed to the same amount of infrared radiation. This can be achieved by pointing each camera, without its filter, at a known source of infrared radiation having a known constant temperature and recording the digital signal from each pixel of each camera.
- a calibration look-up table is then created in non- volatile memory within module 2 by varying the source temperature through the range 210 to 300 K, in steps of 10 K (for example) for each camera, giving a table of 640x512x10x2 values, assuming a linear calibration.
- the calibration look-up table enables a radiance value to be provided for a given digital output from each pixel. (Radiance is assumed to have a linear relationship to the signal counts). This process is repeated for each narrowband filter used. Once on board the aircraft, intermittent re-calibrations are performed using the blackened shutter 8. Optionally, a second shutter could be used to provide a second calibration point in a linear calibration equation. This is heated and placed in front of the filter. The digital counts corresponding to the known (controlled) temperature of the shutter are then recorded.
- the calibrated radiance data for each pixel of all five cameras is transmitted from detector electronics module 2 to processing unit 3.
- processing unit 3 comprises a conventional computer architecture having a microprocessor and memory 4, which includes a look-up table.
- the microprocessor runs software that implements a number of algorithms which, using data from the look-up table, determine whether the outputs from the cameras 6 are indicative of one or more volcanic cloud species, or another hazardous condition.
- the processing unit activates display 5.
- the operation of the algorithms and the resulting output display will now be described in more detail.
- the system is de-activated until the aircraft reaches cruise altitude. In deactivated mode the shutter is closed. Before activation a pre-calibration cycle for the system (all five cameras) is conducted. The shutter is then opened and the system begins to collect images.
- the brightness temperature is determined from:
- Rj j_k is the radiance at pixel i, line j and filter k
- Vk is the central wave number for camera filter k
- Camera images may be averaged in order to reduce noise and improve the signal-to-noise ratio of the system.
- the data for one pixel consists of the measurements: BT1 , BT2, BT3, BT4 and BT5, where these represent brightness temperatures from each of the five cameras (e.g. BT1 is the brightness temperature for that pixel in camera 1 which has filter 1 ).
- the system is linked into the aircraft instrument data stream so that GPS coordinates, altitude (z) , longitude (1), latitude (q), heading (h), direction (d), roll (r), yaw (y), pitch (x), time (t), speed over the ground (v), wind speed (w) and local ambient temperature (Ta) are available at a sampling rate of at least I s "1 and preferably faster.
- the five values of brightness temperature are compared to each other and/or to the ambient temperature using a series of algorithms. Each algorithm uses one or more predetermined threshold values stored in a look-up table in memory 4. These values are determined from a model atmosphere that is based on radiative transfer calculations, as will be described further below. Note that all temperatures are in kelvins.
- the system uses filters at the following central wavenumbers (in cm "1 ):
- a pixel is declared to be ash if both of the following conditions are met at each instance:
- DTl Ash (BT4-BT5)/BT4 > Tl Ash (Ta, r, y, x)/Ta (1)
- DT2 Ash (BT3-BT5)/BT3 > T2 As h(Ta, r, y, x)/Ta (2)
- Tl Ash and T2 As h are threshold values of temperature difference that are both a function of a set of parameters, including ambient temperature (Ta) and realistic aircraft roll, pitch and yaw values.
- DTI Ash and DT2 As h are non- dimensional quantities and are strictly indices. Ta may vary across the image - i.e. it need not be the same for all pixels.
- An alert is sounded if a sequence of 8 consecutive occurrences of conditions (1) and (2) happen for a pre-defined fraction of the total image.
- a value of 5% of the total number of pixels in the difference image is used, but this can be tuned as necessary - a lower value set if the aircraft is operating in airspace declared, or likely to be influenced by volcanic ash; a higher value in unaffected areas.
- a pixel is declared to be water vapour affected if the following conditions are met at each instance:
- T wv is a threshold value of temperature difference that is a function of a set of parameters, including ambient temperature (Ta), and realistic aircraft roll, pitch and yaw values.
- T wv is used with the ice algorithm if that alert is sounded.
- TICA is a threshold value of temperature difference that is a function of a set of parameters, including ambient temperature (Ta), and realistic aircraft roll, pitch and yaw values.
- An alert is sounded if a sequence of 8 consecutive occurrences of condition (4) happen for a pre-defined fraction of the total image. A value of 5% of the total number of pixels in the difference image is used, but this can be tuned as necessary - a lower value set if the aircraft is operating in airspace declared or likely to be influenced by volcanic ash; a higher value in unaffected areas.
- the alert is sounded condition (3) is checked and if this condition is met, the pixel is confirmed to be ICA.
- the use of the water vapour condition is entirely novel and reduces the false alarm rate for detecting hazardous small-sized ice-coated ash particles. SO? Detection Algorithm
- Tl so2 and T2 S o 2 are threshold values of temperature that are a function of a set of parameters including ambient temperature (Ta), and realistic aircraft roll, pitch and yaw values.
- An alert is sounded if a sequence of 8 consecutive occurrences of conditions (5) and (6) happen for a pre-defined fraction of the total image.
- a value of 5% of the total number of pixels in the difference image is used, but this can be tuned as necessary - a lower value set if the aircraft is operating in airspace declared to be or likely to be influenced by volcanic ash; a higher value is used in unaffected areas.
- An example of the display shown to the crew for the detection of an ash cloud is shown in Figure 4. (The actual display uses multiple colours). This is based on an ash cloud composed of silicate material and shows the DTI Ash signal for 6 frames separated by a constant short time difference from two cameras imaging ahead of the aircraft. Highest concentrations of ash are indicated in red (dark in Figure 4); the background sky is shown in light purple (or light grey in Figure 3). As the aircraft approaches the hazard, the pilot can alter the heading of the aircraft to avoid it.
- the threshold values used in the algorithm are pre- computed values stored in a look-up table in memory 4. They are obtained from a detailed radiative transfer model of the atmosphere utilizing geometrical
- the model uses a three dimensional 'monte carlo' approach that allows arbitrary viewing geometry and for the medium (i.e. the substances present in the atmosphere) to be specified flexibly.
- the medium i.e. the substances present in the atmosphere
- the presence of ash, ice-covered ash, mixtures, water clouds, water vapour, etc may all be specified.
- the model also calculates an "environmental" temperature of each of the image pixels based on the ambient temperature sensed by the aircraft instruments. Versions of the model are created with and without a volcanic cloud. A comparison of the clear atmosphere model with one in which a volcanic cloud is simulated identifies the "signature" characteristics which occur only when a volcanic cloud is present. Suitable threshold values can then be determined.
- the look-up table is a multi-dimensional array which is indexed using ambient temperature and aircraft altitude and attitude data so that a given, predetermined threshold value is provided for sets of the other parameters.
- Figure 5 shows a horizontal path simulation of the radiance of the clear atmosphere from 700-1600 cm "1 at three different flight altitudes (the lowermost radiance curve is an altitude of 9.5km, the middle is 4.5km, and the uppermost is 1.5km). At 9.5 km the atmosphere appears very cold-the equivalent blackbody temperature of the horizontal path is about 227 K. Notice that the radiance curves change with altitude and hence with ambient temperature as determined by the on board aircraft instmmentation and used by the detection algorithm. (It could equally use altitude instead of the temperature, but the temperature is a more robust measure). Any volcanic cloud placed between the aircraft and the cold background will alter the radiance received by the system in a known way. Thus the spectral content of the radiation then contains signatures of ash, S0 2 , H 2 0 and ice-coated ash particles. The threshold values obtained from the radiative transfer model are stored in the look-up table.
- the ash signal in these spectra is characterised by a higher brightness temperature in filter 4 (BT4) than in filter 5 (BT5), when viewing a cold
- the threshold values are determined by using refractive index data for silicates and scattering calculations are based on measured particle size distribution for particles with radii in the range 1 -20 ⁇ , according to the art.
- the camera array 6 will look in the horizontal or slightly upwards (aircraft usually have a 3° pitch angle upwards). However, the aircraft may pitch downwards, in which case the background temperature might change from a cold background to a warm background. It is for this reason that the aircraft altitude must be considered when determining threshold values.
- the ash signature is identified by BT4 ⁇ BT5.
- the threshold will have the opposite sign to the pitch-up equivalent.
- the look-up table is therefore constructed in such a way that the pitch angle and ambient temperature are accounted for. Additionally, the roll and yaw angles are compensated for, although these have only a minor influence on the detection algorithm. Extra fail-safe thresholds are also incorporated into the detection algorithm by utilizing a filter near 8.6 ⁇ that has sensitivity to volcanic ash.
- the operation of the ice-coated ash algorithm is similar to the ash algorithm, except the threshold look-up table is now determined using data for ice (refractive indices and scattering data for small particles, radii ⁇ 30 ⁇ ).
- BT4 ⁇ BT5 for viewing into a cold background (the opposite to ash without an ice coating). Background conditions are accounted for in a similar way to that used for the ash detection.
- S0 2 and H 2 0 threshold look-up tables are also used.
- S0 2 has very strong absoiptions near to 8.6 ⁇ and 7.3 ⁇ as Figure 6 illustrates.
- the principle of detecting S0 2 has been described earlier and is based on radiative transfer calculations assuming the line strengths and transmissions applicable to the case of an atmosphere loaded with S0 2 .
- S0 2 has an extremely low abundance ( ⁇ 10 -3 ppm), and so detection of S0 2 using these absorptions features is very effective in the case of volcanic clouds ahead of an aircraft.
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AU2012359085A AU2012359085B2 (en) | 2011-12-22 | 2012-02-02 | System and method for detecting adverse atmospheric conditions ahead of an aircraft |
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US13/334,908 US10063794B2 (en) | 2010-04-29 | 2011-12-22 | System and method for detecting adverse atmospheric conditions ahead of an aircraft |
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US5654700A (en) | 1990-04-09 | 1997-08-05 | Commonwealth Scientific And Industrial Research Organization | Detection system for use in an aircraft |
AU2011100797A4 (en) * | 2010-04-29 | 2011-08-04 | Nicarnica Aviation As | System and method for detecting adverse atmospheric conditions ahead of an aircraft |
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2012
- 2012-02-02 AU AU2012359085A patent/AU2012359085B2/en active Active
- 2012-02-02 WO PCT/EP2012/051798 patent/WO2013091902A1/en active Application Filing
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5654700A (en) | 1990-04-09 | 1997-08-05 | Commonwealth Scientific And Industrial Research Organization | Detection system for use in an aircraft |
AU2011100797A4 (en) * | 2010-04-29 | 2011-08-04 | Nicarnica Aviation As | System and method for detecting adverse atmospheric conditions ahead of an aircraft |
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AU2012359085B2 (en) | 2016-11-24 |
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