54 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.

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 invention discloses an ice accumulation thickness detection method and device and an aircraft, and the method comprises the steps: obtaining a sampling signal when no ice is accumulated in a to-be-detected ice accumulation region through a transmitter-receiver pair which is disposed in the to-be-detected ice accumulation region and of which a signal transmission path passes through the to-be-detected ice accumulation region, and setting the sampling signal as a first baseline signal; subsequently calculating a first signal difference coefficient between the newly acquired sampled signal and the first baseline signal after acquiring the sampled signal by the transmitter-receiver pair; and based on the first signal difference coefficient and an ice accumulation thickness calculation model constructed in advance based on a coupling relationship between the signal difference coefficient and the ice accumulation thickness, determining the ice accumulation thickness of the ice accumulation area to be measured.

The invention belongs to the technical field of wind power generation, and relates to a comparative learning method and system for icing detection of wind turbine blades. The method comprises the steps of collecting data and performing data preprocessing; carrying out adaptive spectrum-time enhancement processing; optimizing a time mask and a frequency mask based on a combination of sparsity loss, mode retention loss and diversity loss; obtaining enhanced vibration signals as positive sample pairs; extracting a negative sample pair; identifying an abnormal sample through the abnormal score; and performing fine adjustment on the unsupervised contrast learning model by using a marked sample, and outputting an icing anomaly detection result through a lightweight classification head. According to the invention, a method of combining adaptive spectrum-time enhancement and negative sample pool contrast learning is provided to generate reliable positive and negative contrast sample pairs, and icing abnormity can be accurately detected under the conditions of mark scarcity and data imbalance; the problem of false negative sampling can be effectively relieved, the problem of class imbalance is solved, and high-quality feature learning can be achieved.

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.

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 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.

A method for controlling the type of ice accretion in ice accretion tests, which relates to the technical field of ice accretion. It solves the problem of accurately simulating the ice accretion test of large test pieces. The method includes: setting the humidity in the test chamber, turning on the defogger, running the circulation fan, and introducing low-humidity air; setting the temperature in the test chamber, turning on the cooling equipment, running the circulation fan, and introducing low-temperature air; when the temperature reaches the set value, setting the background fan frequency, turning on the background fan, and providing spray background wind; setting the air supply pressure, turning on the main air supply and secondary air supply, and the compressed air is ejected through the nozzle; setting the water supply pressure, turning on the main water supply and secondary water supply, transporting low-temperature ultrapure water, and starting spraying; after the test ends, closing the water supply pressure, closing the waterway valve, closing the air supply pressure, closing the air path valve, and stopping spraying; maintaining the set temperature and strengthening the ice layer on the surface of the test piece; after the ice accretion test ends, turning off the electrical equipment. It is used to evaluate the ice accretion performance of large test pieces in cold environments.

The present invention provides a mobile ice-melting disconnect switch and an ice-melting control method, belonging to the technical field of electrical switches. Specifically, it includes: a current monitoring module, a data processing module, and a control strategy output module. Among them, the current monitoring module is responsible for monitoring and processing the ice-melting current during the ice-melting process. The data processing module is responsible for determining the increase risk coefficient of the ice accretion amount on the transmission line, the ice-melting processing efficiency of the transmission line, and the ice-accrual risk area of the transmission line. The control strategy output module is responsible for determining the control strategy for the ice-melting process of the transmission line, improving the efficiency of the ice-melting process.

The invention provides a super-hydrophobic emulsion, a super-hydrophobic self-cleaning coating, a preparation method of the super-hydrophobic emulsion and the super-hydrophobic self-cleaning coating and an insulator composite structure. The preparation method of the super-hydrophobic emulsion comprises the following steps: uniformly mixing an HPMC solution, terpilenol and a SiO2 dispersion liquid to obtain the super-hydrophobic emulsion, wherein the mass ratio of the HPMC to the terpilenol to the SiO2 is (3-7): (60-90): (20-90). The silicon dioxide super-hydrophobic coating is prepared by adopting an efficient fluoride-free method, so that anti-icing application of the surface of a power transmission line insulator is facilitated. The water contact angle of the coating can reach 161 degrees, the sliding angle is smaller than 1 degree, in an anti-icing performance test, the freezing starting time of liquid drops is effectively delayed compared with that of a common surface, and the surface icing amount of the super-hydrophobic coating is reduced by 53.6% compared with that of the common surface. The coating provided by the invention has good corrosion resistance and low temperature resistance, has good anti-icing performance when being applied to the surface of the insulator, and can keep a stable structure.

The invention provides a method for analyzing wake flow galloping characteristics of a non-parallel double-cable and four-cable model, which is a method for analyzing wake flow galloping characteristics of a non-parallel double-cable and four-cable model under a crescent icing condition, and comprises the following steps of: establishing a three-dimensional crescent icing non-parallel double-cable and four-cable model by adopting a numerical wind tunnel method; the wake flow galloping phenomenon of the unparallel double cables and four cables under the crescent icing condition is analyzed; and carrying out three-dimensional numerical simulation on four ice-coated cables and non-parallel cables on a double-cable surface, and researching aerodynamic characteristics and galloping characteristics of the inhaul cable. The device has high pertinence on research on wake flow galloping of the crescent-shaped icing inhaul cable, and wake flow galloping characteristics of double crescent-shaped icing unparallel cables and four crescent-shaped icing cables can be fully discussed; the probability of galloping of the downstream cable of the crescent ice-coated unparallel double cables under the working condition is small. The galloping force coefficient of each cable in the crescent icing four-cable model under the working condition is larger than 0, and the galloping possibility is small.

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 generate heat at targeted areas of a propeller assembly by electric heating systems that utilize 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 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.

The invention discloses a construction method of an ice accretion thickness calculation model. The construction method comprises the following steps: setting a transmitter-receiver pair of which a signal transmission path passes through an ice accretion area to be measured in the ice accretion area to be measured; the temperature of the ice accumulation area to be measured is adjusted to be in a set temperature range, liquid is continuously sprayed to the ice accumulation area to be measured, and ice accumulation with the thickness gradually increased is formed in the ice accumulation area to be measured; the method comprises the following steps: periodically measuring the thickness of accumulated ice while periodically acquiring a sampling signal through a transmitter-receiver pair to obtain an accumulated ice thickness change sample set; setting a sampling signal obtained when no ice is accumulated in the ice accumulation area to be detected as a first baseline signal; after each sampling signal is obtained, calculating a first signal difference coefficient between the newly obtained sampling signal and the first baseline signal to obtain a first signal difference coefficient change sample set; and based on the first signal difference coefficient change sample set and the icing thickness change sample set, constructing a first sub icing thickness calculation model.

The invention relates to the technical field of aviation safety, and provides a method, system and device for identifying airplane ice accretion through satellite original data and a medium, and the method comprises the steps: building an identification algorithm model based on an inversion product, and setting an identification algorithm threshold value; performing back calculation on the basis of the preprocessed historical inversion product by using an identification algorithm model based on the inversion product to obtain first historical ice accumulation identification data; training a deep learning model by using the preprocessed first historical original data and the first historical ice accretion identification data to obtain a model for identifying airplane ice accretion based on the satellite original data; and based on the model for identifying the airplane icing on the basis of the original data of the target satellite, identifying and monitoring the airplane icing by using the real-time original data of the target satellite. The airplane ice accretion is directly identified based on the satellite original data, errors caused by an inversion algorithm are avoided, the airplane ice accretion is identified in real time by using the satellite data, and airplane ice accretion monitoring can be carried out in real time in all weathers.

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.

A method for operating a wind power installation, the wind power installation including an aerodynamic rotor having rotor blades of adjustable blade angle, being controlled by an operation control system, and being configured to generate an installation power, comprises activating a blade-angle adaptation routine when an ice accretion situation occurs, when ice accretion on the rotor blades has been detected or is expected, modifying a collective blade angle of the rotor blades using the blade-angle adaptation routine to adapt the rotor blades to an altered aerodynamic situation caused by the ice accretion, in order to increase the installation power, and selecting an aerodynamically improved blade angle as a modified collective blade angle and specifying the aerodynamically improved blade angle as an iced-blade angle.

An aircraft system includes a gas turbine engine, an altitude sensor configured to measure an altitude of the aircraft, and an electrostatic charge sensor inlet debris monitoring system configured to detect particulates entering the engine. The aircraft system further includes a precipitation monitoring controller configured to determine the presence of sea spray based on the altitude and the presence of precipitation based on an amount of particulates entering the inlet, and detects an ingestion of salt into the gas turbine engine in response to detecting a presence of both the sea spray and the amount of particulates entering the inlet. In addition, the precipitation monitoring controller is configured to determine a presence of ice accretion in the engine based on the temperature and an amount of the particulates, and to activate an anti-icing system in response to determining the presence of ice accretion.

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 invention provides an aero-engine air inlet icing environment simulation test cloud and mist parameter control method, which is characterized by comprising the following steps: S1, establishing the influence of water pressure and air pressure of a spraying system on the average water drop diameter; s2, calculating the influence of the height simulation parameter and the wind speed on the average water drop diameter; s3, carrying out coupling analysis on the liquid water content parameter and the intake and exhaust parameters, and calculating the amount of water to be sprayed; s4, a one-way air supply system is adopted to achieve accurate control over the air pressure of the spraying system; s5, stable control over the water pressure of the spraying system is achieved through a circulating water supply system. According to the method, through cooperative control of the spraying system and the air intake and exhaust system, the precision of icing environment simulation is remarkably improved, more reliable test conditions are provided for an aero-engine air intake icing test, and the method is particularly suitable for cloud field simulation under complex environmental parameters (such as high wind speed and low air pressure).

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.