35 results about "Ice accretion" patented technology

The invention discloses an aeronautical ice accretion identification method based on multi-source data, which solves the coverage blind area of a single data source (mode / satellite) through multi-source data fusion processing, improves the integrity of a three-dimensional space, and further establishes a scene classification foundation through cloud layer structure identification and accurate division of a cloud area / a precipitation area. Through membership function construction processing, a nonlinear relation between meteorological elements and icing is quantified, and a traditional threshold value method is replaced; furthermore, through physical scene classification processing, single-layer cloud / multi-layer cloud / freezing water freezing mechanisms are distinguished, and misjudgment is avoided; through initial index calculation, CTTmap is dynamically adjusted according to different scenes, and satellite detection deviation is corrected; finally, through dynamic index correction processing, vertical motion, supercooled water and a real-time report are introduced, and result self-adaptive optimization is achieved.

The invention provides an airplane ice accretion model training method, a prediction method, a product, equipment and a medium. The method comprises the following steps: acquiring airplane ice accretion observation data and historical weather data; based on the space information and the time information of the airplane icing observation data and the horizontal grid, the vertical layering and the time dimension of the grid points, space-time matching is carried out on the airplane icing observation data and the grid points, and the space-time matched grid points are obtained; calculating the feature data of the space-time matched grid points by using an ice accumulation scheme to obtain ice accumulation indexes of the space-time matched grid points; constructing a training data set according to the feature data corresponding to the plurality of spatio-temporal matched grid points, the icing indexes and the observation labels of the matched airplane icing observation data; and performing model training by using the training data set to obtain an airplane icing model. The training data set provides high-order features with more physical significance for machine learning, the interpretability of the model is improved, and the prediction accuracy of the airplane ice accretion is improved.

A three-dimensional ice accretion reconstruction method and apparatus for a fan blade, and a device and a storage medium. The method comprises: using a cross-sectioning method to cut a fan blade, so as to obtain two-dimensional airfoil-section coordinate data of each position; performing airflow field calculation on each two-dimensional airfoil section, so as to obtain an external airflow velocity of each two-dimensional airfoil section; performing force analysis on water droplets, calculating impingement positions of the water droplets on each two-dimensional airfoil section, and then calculating a local water droplet impingement coefficient and a freeze fraction; on the basis of the local water droplet impingement coefficient, the freeze fraction and environmental parameters, acquiring the thickness of an ice accretion on each two-dimensional airfoil section and an ice accretion shape on each two-dimensional airfoil section; on the basis of the thicknesses of the ice accretions, updating the two-dimensional airfoil-section coordinate data; performing ice accretion calculation at the next time step until a preset condition is met; and performing lofting processing on each two-dimensional airfoil section, so as to obtain a three-dimensional ice accretion shape result of the fan blade. The increased thicknesses and shape of ice accretions of a fan blade under different working conditions are quickly obtained with a small amount of calculation.

The invention discloses an airplane icing early warning method, and relates to the technical field of icing early warning. According to the airplane icing early warning method, cloud picture data and cloud product file data of a set airplane are obtained, a cloud field operation state feature set of the set airplane is extracted based on the cloud product data of the set airplane, and a cloud liquid water path value of the set airplane is analyzed; based on a pre-trained cloud picture error mapping model and in combination with cloud picture data of the set airplane, analyzing a cloud type temperature correction factor of the set airplane, and in combination with the cloud field operation state feature set, analyzing an optimized cloud top temperature value of the set airplane; based on the cloud liquid water path value of the set airplane, the cloud top temperature value is optimized, and the ice accretion index of the set airplane is analyzed, ice accretion early warning processing is performed on the set airplane based on the ice accretion index, so that the finally generated ice accretion index result has higher environmental adaptability, dynamic correction and high-precision characterization of the ice accretion risk are realized, and the method is suitable for large-scale popularization and application. And thus, the accuracy of ice accumulation early warning is improved.

The invention discloses an ice accumulation forecasting method and system, a readable storage medium and a program product, and the method comprises the steps: S1, selecting a specific region, obtaining meteorological data, and processing the meteorological data into a unified format, S2, constructing an initial ice accumulation potential algorithm of the specific region based on the meteorological data, and S3, constructing an initial ice accumulation potential algorithm of the specific region based on the meteorological data. S4, identifying a specific weather system and a key meteorological factor of the specific area, and establishing a membership function of the key meteorological factor under the specific weather system, and optimizing the initial icing potential algorithm in combination with the membership function to obtain a localized icing potential algorithm. And S5, outputting the icing potential based on the localized icing potential algorithm. Therefore, a localized icing potential algorithm can be established for a specific region, so that the icing risk can be predicted more accurately.

The application discloses an ice slurry detection method and system, electronic equipment and medium, and relates to the technical field of remote sensing semantic segmentation. The method comprises the following steps: inputting a to-be-predicted river remote sensing image into a trained ice slurry detection model to obtain ice slurry in the to-be-predicted river remote sensing image; the trained ice slurry detection model is trained by taking a sample river remote sensing image as input and taking ice slurry in the sample river remote sensing image as output; the ice slurry detection model comprises an encoding layer, a multi-head attention layer and a decoding layer; the output end of the encoding layer is connected with the input end of the multi-head attention layer and the input end of the decoding layer, and the output end of the multi-head attention layer is connected with the input end of the decoding layer; the encoding layer comprises a plurality of feature encoding modules; the feature encoding module is an inverted residual structure and comprises a deep parameterized convolution layer; the multi-head attention layer comprises a spatial attention feature mechanism and a channel attention feature mechanism. The application can improve the accuracy of ice slurry edge detection.

The invention relates to a deicing operation robot based on an unmanned aerial vehicle. The deicing operation robot comprises an unmanned aerial vehicle module and a deicing robot module which are integrated into a whole. The deicing robot module comprises a control module, a wire clamping module and a wire deicing module; the unmanned aerial vehicle module comprises a multi-mode sensor and a rotor wing tilting module, and the multi-mode sensor can identify the icing type of a to-be-deiced wire and can also identify the inclination angle of the wire or the inclination angle of a vehicle body; the wire deicing modules are arranged on the wire clamping module and located on the two sides of the wire to be deiced, and can move along with the wire clamping module. The control module can instruct the wire clamping module and the wire deicing module to act according to the icing type, and the control module can instruct the rotor wing tilting module to tilt according to the wire inclination angle or the fuselage inclination angle. According to the integrated design, the maneuverability of the equipment is greatly improved, the equipment can quickly reach various complex operation areas, and the deicing efficiency and the operation flexibility are improved.

The invention discloses an ultra-flexible low-temperature-resistant ice-resistant cable for a high-speed railway in an extremely cold region, and the cable is characterized in that nylon wires are added in a conductor structure as a supporting skeleton, and cooperate with small-diameter copper wires to reduce the overall rigidity, thereby achieving ultra-flexibility; the conductor wrapping layer adopts a carbon fiber braid layer, so that the electrical stability is improved while the low-temperature bending fatigue life is prolonged; according to the three-layer gradient functional co-extrusion insulating layer system, nano aluminum oxide is added into a polypropylene material in the inner layer to improve the corona initial voltage, the fluoroplastic FEP aerogel in the middle layer reduces the elastic modulus at the ultralow temperature, and the modified polyurethane elastomer in the outer layer reduces the surface energy and the ice adhesion. Therefore, the ultra-flexible low-temperature-resistant ice-resistant cable for the high-speed railway in the extremely-cold region has the advantages of good flexibility in an extremely-cold environment, high oxidation resistance, high electrical stability, ice resistance and mechanical damage resistance.

Embodiments of the present disclosure provide systems and methods for averting, shedding, or otherwise managing ice accretions that may develop during flight of an aircraft. Example systems and methods direct oil from a lubrication and cooling path to targeted sections of ice-prone surfaces to manage ice accretion in a way that does not unduly increase the total volume of oil, require larger pumps, or complicate the system.

A turbofan engine is provided. The turbofan engine includes a fan including a plurality of fan blades, a turbine operably coupled to the fan for driving the fan, the turbine including a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath, an nacelle surrounding and at least partially enclosing the fan, an inlet pre-swirl feature upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle, and a device on the inlet pre-swirl feature for reducing ice accumulation or ice formation, the device in communication with the inlet pre-swirl feature.

The present application relates to a kind of ice accretion and freezing rain device and test method suitable for low temperature environment, by the low temperature condition of being set by test equipment in environmental test chamber, according to the surface temperature of being tested equipment, the temperature of environmental test chamber is adjusted, so that the acceleration test of being tested equipment under low temperature can be carried out, and the real low temperature environment is simulated for being tested equipment;By setting mobile platform and spraying rack, being tested equipment can be uniformly sprayed and overall evenly iced in the process of experiment;By setting spraying device, water mist can be sprayed to being tested equipment, and the real freezing rain, ice accretion and rain environment are simulated;By setting axial fan, water mist sprayed by spraying device can be hit on the surface of being tested equipment, and the splashing icing and snow blowing environment are simulated;By setting measuring equipment, the environmental conditions of test area, the surface temperature of being tested equipment and ice accretion thickness can be measured, so whether the required environmental conditions of being tested equipment low temperature test are reached is judged.

The invention relates to test benches for pieces of aviation equipment and can be used for testing an engine and propeller assembly (an engine with a propeller mounted thereto) for small unmanned aerial vehicles under icing conditions. A test bench for testing an engine and propeller assembly for ice accretion comprises a freezing chamber, a system for supplying power to and controlling the revolutions of the engine and propeller assembly undergoing testing, a system for monitoring the state of the engine and propeller assembly undergoing testing, meters for measuring the air temperature and humidity inside the freezing chamber, a two-phase nozzle for spraying water onto the engine and propeller assembly undergoing testing, and systems for supplying water and compressed air to the two-phase nozzle, wherein, in addition to a compressor with a tank, a pipeline, a filter and a compressed air pressure regulator, the system for supplying compressed air comprises an air dryer. The technical result of the invention is that of providing more accurate test results using a compact and energy efficient test bench.

A method for controlling an anti-icing device for protecting at least one outer surface of an aircraft, the device being provided with at least one anti-icing means (5, 6) and means (4) for measuring the rate of ice build-up, the method comprising the following steps: determining, as a function of the rate of ice build-up determined by the measuring means (4), the speed of ice build-up of the at least one anti-icing means (5, 6); 6) in order to prevent ice build-up on the at least one outer surface to be protected or in order to reduce the thickness of ice build-up on the at least one outer surface to be protected.

Embodiments of the present disclosure provide systems and methods for avoiding ice accretions that may occur during flight of an aircraft, shedding the ice accretions, or otherwise managing the ice accretions. Example systems and methods selectively modulate propeller parameters in a manner that does not interfere with a flight trajectory; directing oil from the lubrication and cooling path to a target section of the ice prone surface in a manner that does not excessively increase the total volume of oil, does not require a larger pump, or does not complicate the system to manage ice build-up; or heat is generated at a target area of the propeller assembly by an electrical heating system utilizing propeller motion.

The present invention belongs to the field of ice performance testing, and specifically relates to an ice accretion shear adhesion test device. The device includes an ice accretion specimen, a fixing mechanism, a clamping mechanism, a linear stretching mechanism, and a sensor. The ice accretion specimen includes an ice accretion specimen and an ice accretion mold. At least one surface of the ice accretion specimen is provided with a coating to be tested. The ice accretion mold is provided with an opening at the bottom, which is used to provide a site for ice accretion to adhere to the coating to be tested. The fixing mechanism is used to fix the ice accretion mold; the clamping mechanism is used to clamp the ice accretion specimen; the linear stretching mechanism is connected to the clamping mechanism and provides a tensile force along the direction of the ice accretion specimen to separate the coating to be tested from the ice accretion on the surface of the ice accretion specimen. One end of the sensor is connected to the linear stretching mechanism, and the other end is connected to the clamping mechanism to collect the real-time tensile force applied to the clamping mechanism. The present invention has a relatively simple structure, a small size, and a low cost. It can be directly placed in a general low-temperature environmental chamber for measurement and can accurately measure the ice accretion shear adhesion of the coating to be tested.

The application relates to the technical field of offshore wind power equipment protection, and discloses a system and a method for inhibiting ice accretion resonance of an offshore wind turbine support structure, which comprises an ice accretion resonance identification module and an ice accretion resonance inhibition module; the ice accretion resonance identification module comprises a double-shaft acceleration sensor arranged at the top of a wind turbine tower and at least two high-definition waterproof cameras; the two high-definition waterproof cameras are arranged at the bottom of a tower drum and face the sea surface at an angle of 180 DEG; the ice accretion resonance inhibition module comprises a control module, an execution module and a unit control system; the unit control system is used for collecting a reference frequency of the wind turbine support structure in cooperation with the control module; and the execution module comprises a variable pitch mechanism and a yaw mechanism. The ice accretion resonance identification and inhibition function modules are modularized and divided to form a closed-loop linkage control, the problem that a traditional scheme is prone to false triggering or missed triggering is solved, and the accuracy and reliability of the inhibition action are significantly improved.

The invention relates to aircraft icing detection based on measured density. Examples are disclosed relating to a method (700) for detecting ice accretions present on an aircraft (100). In one example, a depth signal is received from a depth sensor (408A) that is indicative of a depth of water and / or ice collected on a substrate (406) in a collection chamber (402) of an aircraft ice detector (400). A quality signal indicative of a quality of water and / or ice collected on the substrate (406) is received from a quality sensor (410). A volume of water and / or ice collected on the substrate (406) is calculated based on the depth signal and the dimensions of the substrate (406). A density of water and / or ice collected on the substrate (406) is calculated based on the mass signal (410) and the calculated volume of water and / or ice collected on the substrate (406). An ice accretion signal is output based on the calculated density of water and / or ice collected on the substrate (406) being less than a threshold density.

The invention relates to the technical field of aeronautical data identification and analysis, in particular to an ice accumulation prediction method and system based on observation data correction, a medium and a product. The method comprises the following steps: observing and acquiring indirect indexes in a flight area of the aircraft through stationary satellite equipment; calculating an initial membership degree according to the cloud top temperature and a first membership degree function; correcting the initial membership degree according to the cloud top phase state to obtain a corrected membership degree; obtaining a direct index in a flight region of the flight interval; calculating a direct membership degree according to the direct index and a corresponding second membership degree function; selecting a recommended prediction area according to flight information, wherein the flight information comprises meteorological information; and according to the corrected membership degree and the direct membership degree, calculating the icing potentials of the plurality of point locations in the recommended prediction area. According to the method, the calculation efficiency can be greatly improved in a complex flight scene of multiple aircrafts, and the calculation cost is reduced.

The present invention relates to a system (1) for detecting icing conditions. The system (1) comprises a plurality of piezoelectric crystals (2, 2', 2''), a vector network analyser (3), and a processing means (4). A pair of electrodes (5) is connected to each piezoelectric crystal (2, 2', 2''). The piezoelectric crystals (2, 2', 2''), by means of the electrode (5) pairs thereof, are connected in parallel to each other and to the vector network analyser (3). The vector network analyser (3) is configured to scan the response of the piezoelectric crystals in the frequency domain by generating electric signals suitable for producing acoustic waves in each piezoelectric crystal (2, 2', 2''), and by periodically measuring a set of resonance data for each piezoelectric crystal and to send the sets of resonance data to the processor (4). The processor (4) is configured to receive, from the vector network analyser (3), the sets of resonance data and to calculate, using the sets of resonance data, an indicator of ice accretion, a value of ice accretion rate, an indicator of the severity of the ice event and an indicator of the droplet size.

Embodiments of the present disclosure provide systems and methods for averting, shedding, or otherwise managing ice accretions that may develop during flight of an aircraft. Example systems and methods generate heat at targeted areas of a propeller assembly by electric heating systems that utilize propeller motion.

The invention relates to the technical field of meteorological monitoring, and discloses a portable meteorological and icing monitoring station and a use method thereof.The portable meteorological and icing monitoring station comprises a meteorological monitoring station, the top of the meteorological monitoring station is fixedly connected with a microwave icing sensor, and the outer surface of the meteorological monitoring station is fixedly connected with a detection inflator; an inner plate, an outer plate and an air ring are fixedly connected to the inner wall of the detection air cylinder, a fixed circular ring is fixedly connected to the inner wall of the air ring, and an air inlet cavity and an air outlet cavity are formed in the inner wall of the fixed circular ring. The portable meteorological and icing monitoring station and the using method thereof can effectively solve the problems that in the prior art, when the air flowing speed in the external environment is low, air around a humidity sensor is updated slowly, the exchange rate of water vapor molecules and a humidity sensing element of the sensor is reduced, the response time of the sensor is prolonged, and the monitoring efficiency is low. And the sensor needs longer time to reflect the change of the actual humidity, so that the measurement lag phenomenon occurs.

The application relates to the technical field of aviation data recognition and analysis, and in particular to an icing prediction method and system based on observation data correction, a medium and a product. The method comprises the following steps: obtaining indirect indexes in a flight area of an aircraft through observation of a stationary satellite device; calculating initial membership degrees according to cloud top temperature and a first membership degree function; correcting the initial membership degrees according to cloud top phase states to obtain corrected membership degrees; obtaining direct indexes in the flight area in a flight interval; calculating direct membership degrees according to the direct indexes and a corresponding second membership degree function; selecting a recommended prediction area according to flight information, wherein the flight information comprises meteorological information; and calculating icing potential of a plurality of point positions in the recommended prediction area according to the corrected membership degrees and the direct membership degrees. The application can greatly improve the calculation efficiency and reduce the calculation cost in a complex flight scene of multiple aircrafts.

The utility model is suitable for the technical field of airplane ice accretion measurement, and provides an airplane ice accretion measuring device, which comprises a shell; the vacuum chuck is fixedly arranged on the shell; the negative pressure pump is fixedly arranged on the inner wall of the shell; the negative pressure pipe is arranged at the air inlet end of the negative pressure pump and is communicated with the vacuum chuck; the one-way valve is arranged on the negative pressure pipe; the exhaust pipe is mounted at the exhaust end of the negative pressure pump and extends to the outside of the shell; the ultrasonic ice accumulation measuring mechanism is installed on the shell and measures the thickness of ice accumulated on the surface of the airplane by means of the propagation velocity difference of ultrasonic waves in different media. The airplane ice accumulation measuring device provided by the scheme is relatively convenient to mount and dismount, can measure the thickness of the ice accumulation through the propagation velocity difference of ultrasonic waves in different media, can determine the thickness of the ice accumulation through the change of the surface capacitance of the airplane, and is relatively high in measurement accuracy of the thickness of the ice accumulation on the surface of the airplane.

The invention provides an airplane ice accretion forecasting model training method and an airplane ice accretion forecasting method. The airplane ice accretion forecasting model training method and the airplane ice accretion forecasting method are used for solving the problem that accuracy of forecasting ice accretion frequency data is insufficient. The airplane ice accretion forecasting model training method comprises the following steps: acquiring ice accretion frequency sample data; identifying icing states of frequency data in a plurality of continuous duration windows from the icing frequency sample data; determining a plurality of ice accumulation samples with ice accumulation in the ice accumulation state and a plurality of non-ice accumulation samples with no ice accumulation in the ice accumulation state from the ice accumulation frequency sample data; for each ice accretion sample in the plurality of ice accretion samples, determining an intensity grade of the ice accretion sample according to the frequency drop rate; and taking the ice accretion frequency sample data as training data, taking the ice accretion state and the intensity grade as training labels, training the neural network model, and obtaining an airplane ice accretion forecasting model used for predicting the corresponding ice accretion state and the intensity grade according to the ice accretion frequency data.

Embodiments of the present disclosure provide systems and methods for avoiding ice accretions that may occur during flight of an aircraft, shedding the ice accretions, or otherwise managing the ice accretions. Example systems and methods selectively adjust propeller parameters in a manner that does not disrupt a flight trajectory; directing oil from the lubrication and cooling path to a target section of the ice prone surface in a manner that does not excessively increase the total volume of oil, does not require a larger pump, or does not complicate the system to manage ice build-up; or heat is generated at a target area of the propeller assembly by an electrical heating system utilizing propeller motion.

Embodiments of the present disclosure provide systems and methods for averting, shedding, or otherwise managing ice accretions that may develop during flight of an aircraft. Example systems and methods selectively modulate propeller parameters in a way that does not disrupt a flight trajectory; direct oil from a lubrication and cooling path to targeted sections of ice-prone surfaces to manage ice accretion in a way that does not unduly increase the total volume of oil, require larger pumps, or complicate the system; or generate heat at targeted areas of a propeller assembly by electric heating systems that utilize propeller motion.

The application discloses a power transmission line short-time icing growth prediction method considering the influence of micro-topography, and particularly relates to the technical field of icing growth prediction, and comprises the following steps: acquiring a structure state sequence at a tower of a power transmission line and calculating disturbance features, and executing joint judgment to output a structure disturbance state identifier; acquiring the structure state sequence and executing disturbance feature calculation, and jointly judging the structure disturbance state; under the structure disturbance state, forming a disturbance corrected wind speed field based on disturbance calculation and terrain factors, identifying airflow stagnation and calculating water vapor accumulation; then, constructing a structure disturbance feedback path and executing icing growth prediction, dynamically updating feedback path weights based on prediction offset results; and rolling calculation of feedback score values and identification of a structure disturbance dominant area, so as to realize icing growth prediction path identification and incremental output under the linkage of the structure disturbance state, disturbance airflow features and terrain factors.

Embodiments of the present disclosure provide systems and methods for averting, shedding, or otherwise managing ice accretions that may develop during flight of an aircraft. Example systems and methods selectively modulate propeller parameters in a way that does not disrupt a flight trajectory; direct oil from a lubrication and cooling path to targeted sections of ice-prone surfaces to manage ice accretion in a way that does not unduly increase the total volume of oil, require larger pumps, or complicate the system; or generate heat at targeted areas of a propeller assembly by electric heating systems that utilize propeller motion.

A turbofan engine is provided. The turbofan engine includes: a fan including a plurality of fan blades; a turbine operably coupled to the fan for driving the fan, the turbine including a compressor section, a combustion section, and a turbine section in a serial flow sequence and together defining a core air flow path; a nacelle surrounding and at least partially surrounding the fan; an inlet pre-swirling feature upstream of the plurality of fan blades, the inlet pre-swirling feature attached to or integrated to the nacelle; and means on the inlet pre-swirling feature for reducing ice build-up or ice formation, the means being in communication with the inlet pre-swirling feature.

A method, comprising: providing a light source, a high contrast providing object, and an image acquisition device; emitting a light beam from the light source through the high contrast providing object, a transparent object and a surface of the transparent object toward the image acquisition device; exposing the surface of the transparent object to icing conditions such that a layer of ice is formed by ice accretion on the surface, wherein the light beam traverses the layer of ice after having traversed the transparent object; acquiring a series of images over time of the high contrast providing object using the image acquisition device; determining blur occurring in the series of images over the time; and quantifying the loss of visibility over the time through the transparent object on the basis of the determined blur.