36 results about "Icing conditions" patented technology

The invention discloses an ice-coated blade aeroelastic flutter and complete machine mistuning identification method based on multi-dimensional dynamic feature engineering, and belongs to the technical field of wind power. Comprising the steps of collecting original multivariable time series data, preprocessing the original multivariable time series data, performing feature extraction on the preprocessed original multivariable time series data from three dimensions of time domain, time-frequency domain wavelet energy and control system domain to obtain basic physical features, performing feature screening on the basic physical features based on a Gini index, and obtaining the basic physical features. The method comprises the following steps: obtaining a fault seed feature, constructing an interactive feature and an adaptive feature based on the fault seed feature, fusing the basic physical feature, the interactive feature and the adaptive feature into a high-dimensional feature set, and inputting the high-dimensional feature set into a weighted ensemble learning classifier to realize the identification of the ice-coated blade health, aeroelastic flutter and complete machine detuning state. According to the method, the problems of poor fault identification robustness and low precision of a traditional method are solved, and reliable guarantee is provided for safe and stable operation of the wind turbine generator under the icing working condition.

The invention provides an aircraft deicing operation device and method. The device comprises a ground preheating and filling module; the vehicle-mounted deicing operation module comprises an electric chassis, a pressure-bearing heat preservation liquid tank, a spraying unit and a vehicle-mounted inert gas power unit. The high-pressure nitrogen source is communicated with the liquid tank through the pressure adjusting unit and provides spraying driving force for liquid in the tank. The spraying unit selectively communicates with the liquid tank for liquid spraying or communicates with the gas power unit for nitrogen purging. The method comprises the steps that the ground module is used for centralized heating and filling; in the deicing standby period, the liquid temperature is maintained through the heat preservation liquid tank; the high-pressure nitrogen source is started during operation, and a continuous injection mode and a pulse injection mode are selected according to ice conditions; during operation, the pressure is maintained to be stable by adjusting the pressure compensation liquid level change. According to the preheating and vehicle-mounted heat-source-free driving device, the safety of deicing operation of an airplane is improved.

According to the wind turbine generator blade icing dynamic early warning system provided by the invention, through omnibearing monitoring of the frequency modulation continuous wave radar group, the orthogonal weaving piezoelectric fiber array and the infrared temperature measurement unit, airspace water drop distribution, blade vibration characteristics and multi-dimensional dynamic changes of a surface temperature field are accurately captured; by combining improved Kalman filtering, wavelet transformation and a dynamic weight distribution algorithm of an intelligent decision module, traditional single threshold judgment is upgraded to comprehensive threat index deduction based on digital twinborn bodies, and the temporal-spatial resolution and reliability of icing threat assessment are remarkably improved; the execution control module achieves heating network partition accurate regulation and control and unit operation state collaborative optimization according to the generated anti-icing strategy, energy waste of traditional global heating is avoided, material damage caused by local overheating or underheating is effectively restrained, finally, anti-icing energy consumption is reduced under the complex meteorological condition, and the anti-icing efficiency is improved. And meanwhile, the power generation efficiency loss of the unit under the icing working condition is greatly reduced.

The present application relates to the technical field of deicing robot, and more particularly to a multi-split intelligent flying conductor deicing robot, which comprises a main body, a flying arm, a deicing execution assembly, a posture adjusting assembly and a control assembly. The present application synchronously collects multi-dimensional state parameters, identifies the envelope state according to the spatial mapping relationship of configuration and adhesion, calculates the consistency index of multi-station operation through the distribution dispersion of contact length and the cooperativity of vibration response, analyzes the deviation of walking load in different conductor directions, and jointly diagnoses the efficiency mismatch type. Then, according to the state type and the imbalance source, the contact compensation, configuration adjustment or collaborative balance strategy is dynamically matched and directional linkage adjustment is carried out. Finally, the convergence trend of the adjusted parameters is verified, effectively solving the problem of slow response speed and low deicing efficiency in the face of complex and variable icing conditions due to the dependence on fixed mechanical deicing mode.

METHOD AND CONTROL UNIT FOR CONTROLLING THE CLEARANCE OF A HIGH-PRESSURE TURBINE TO REDUCE THE IMPACT OF ICING. Method for controlling the clearance between the blade tips of an aircraft engine turbine rotor and a turbine ring, comprising estimating a nominal clearance to be controlled and controlling a valve delivering an airflow directed to the turbine ring as a function of the nominal clearance thus estimated, method wherein, to prevent the formation of ice that could affect the aircraft engine, the estimated nominal clearance is increased if the on / off result of a predetermined control logic indicates that icing conditions are present and until conditions for returning to normal operation are present, the predetermined control logic being a function of the following parameters: ambient temperature, altitude, temperature T12, and rotational speed of a low-pressure shaft. Figure for abstract: Fig. 3.

This invention provides a method and system for testing icing under rotating conditions of supercooled large water droplets, relating to the field of aero-engine icing testing. It aims to address the problem of excessive liquid water content caused by significant settling of supercooled large water droplets and the inability of the uniform cloud zone to cover the test specimen. The method includes: obtaining the projected area S of the rotating test specimen on the test cross-section under rotating conditions. A ; Obtain the overlapping area S of the cloud and fog region between the uniform cloud and fog region and the projected area of ​​the rotating test specimen. B The liquid water content obtained from the calibration test is L. B According to the projected area S A Area S where clouds and fog overlap B and liquid water content of L B The liquid water content L corresponding to the freezing condition of the rotating test piece was obtained. A By using the relative area of ​​the uniform cloud and fog zone and the test zone, liquid water is equivalently transformed. The freezing condition conversion method of the rotating state test under the freezing condition of supercooled large water droplets is adopted, which effectively supports the rotating state test under the freezing condition of supercooled large water droplets.

The present application relates to the field of power equipment performance detection, and discloses a device and method for detecting the service life of power lines under extremely cold conditions in remote mountainous areas, comprising an extreme temperature environment simulation unit, an icing simulation unit, a mechanical vibration unit, an observation and comparison unit and a control unit; at least two independent and symmetrical test cabins are formed in the insulation box for simultaneously accommodating power line samples from different manufacturers; the control unit is electrically connected with the extreme temperature environment simulation unit, the icing simulation unit, the mechanical vibration unit and the observation and comparison unit, used for adjusting the start and stop of the compression refrigerating machine of the extreme temperature environment simulation unit to maintain the temperature in the test cabin within a preset extremely cold temperature range, controlling the icing simulation unit to spray water mist into the test cabin to simulate icing conditions, controlling the rotational speed of the mechanical vibration unit to adjust the vibration frequency and amplitude of the power line sample, and comprehensively evaluating the service life of the power line sample based on the data collected by the observation and comparison unit.

The application provides a two-dimensional airfoil critical ice shape determination method, device and equipment and a storage medium, relates to the airfoil icing data processing technical field, and the method can more accurately describe the critical influence of the airfoil aerodynamic performance by determining the evaluation parameter corresponding to each icing condition in the current population, performs genetic operation on the current population to obtain a new current population, and determines the evaluation parameter corresponding to each icing condition in the current population again, determines a target icing condition based on the maximum value of the evaluation parameters corresponding to all icing conditions, and determines a two-dimensional airfoil critical ice shape based on the ice shape characteristic parameter corresponding to the target icing condition. By using the evaluation parameter and the genetic algorithm, the global optimal critical ice shape can be automatically found in the entire continuous flow field parameter set space, the locality and blindness of the manual point selection method are overcome, and the efficiency and accuracy of the critical ice shape determination can be improved.

The invention discloses a pneumatic thermal composite anti-icing and deicing device and a control method thereof, and relates to the technical field of plasmas, the pneumatic thermal composite anti-icing and deicing device comprises a composite heating film, the composite heating film comprises an insulating substrate layer, a functional heating layer, a lower electrode array, an upper electrode array and a surface protection layer, and the pneumatic thermal composite anti-icing and deicing device further comprises an airborne anti-icing and deicing power supply; and a plasma jet disturbance assembly is arranged at an easy-to-freeze area at the front edge of the device component. The functional heating layer provides stable and uniform substrate heating, and ensures that the whole protective surface is maintained in a non-icing temperature range; under the extreme icing condition, the composite working mechanism shows obvious advantages. The electrothermal film is responsible for melting an ice-film interface and reducing the adhesion strength; and the plasma-induced ion wind provides continuous pneumatic shear force to promote the overall stripping of the ice layer.

The invention relates to a method, a device and equipment for generating an anti-galloping strategy of an icing contact network, and a medium. The generation method comprises the following steps: acquiring contact network information, and constructing a first hydrodynamic simulation model of the contact network under an icing condition according to the contact network information and preset icing information; according to preset wind power information, carrying out aerodynamic characteristic analysis on the first fluid mechanics simulation model to obtain a first aerodynamic coefficient; according to the preset galloping information, the preset wind power information and the first aerodynamic coefficient, carrying out galloping instability analysis on the icing contact network to obtain a first galloping coefficient; constructing a second fluid mechanics simulation model according to the configuration information of the anti-galloping device, wherein the anti-galloping device is integrated on the contact network; performing aerodynamic and galloping analysis on the second fluid mechanics simulation model according to preset wind power information and preset galloping information to obtain a second aerodynamic coefficient and a second galloping coefficient; and according to the aerodynamic coefficient and the galloping coefficient, generating an anti-galloping strategy capable of efficiently inhibiting vertical galloping of the overhead line system.

The present invention discloses an air data probe integrated with an inverted single helix heater cable for controlling one or more icing parameters. The air data probe comprises a hollow structure and one or more grooves. The hollow structure is designed such that it is exposed to fluid during flight, allowing for interaction with one or more icing parameters. The one or more grooves provide a path for an electrical heater cable. The electrical heater cable, featuring an underside bend for efficient heat distribution is integrated into the one or more grooves. The inverted single helix heater cable significantly elevates performance during icing conditions by maintaining optimal temperatures at critical areas prone to icing.

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 pneumatic-performance-quality integrated monitoring method for an aircraft under the condition of cumulus icing comprises the following steps: acquiring geometric parameters, flight state parameters and environmental parameters of the aircraft, then sequentially calculating a pneumatic flow field and icing parameters of a clean aircraft configuration, performing surface equivalent roughness mapping, and obtaining a result obtained by pneumatic recalculation after icing; and then flight performance and flight quality evaluation is performed according to a result obtained by aerodynamic recalculation after icing, when a flight performance evaluation result or a flight quality evaluation result exceeds a preset safety threshold range, a flight control strategy is triggered, and compensation control is performed on the aircraft by adjusting engine thrust, a control surface deflection angle or flight control parameters, so that the flight quality is improved. Therefore, the aerodynamic stability and the flight safety of the aircraft under the icing condition are maintained. According to the method, the calculation complexity caused by traditional ice shape geometric reconstruction and re-division can be reduced, the flight parameter acquisition efficiency after icing is improved, and the flight state monitoring of the aircraft in the cumulus icing state is efficiently realized.

This invention discloses a safety distance early warning system and method for OPGW lines in icing areas, specifically relating to the field of power system line operation monitoring technology. The system includes the following steps: status acquisition, spatial modeling, distance calculation, dynamic comparison, and trend prediction. By acquiring meteorological parameters in real time, a position function of the conductor and optical cable in space is constructed, the minimum spatial distance is calculated, and compared with a dynamic distance threshold to identify the risk level. Historical data and a difference evolution algorithm are combined to predict the distance change trend, triggering an early warning in advance, thus achieving dynamic assessment and proactive intervention control of distance risks under icing conditions. This invention achieves accurate dynamic monitoring, real-time risk assessment, and trend early warning of the minimum spatial distance between the fiber-optic composite overhead ground wire and the conductor in icing areas. It possesses the beneficial effects of comprehensive data acquisition, accurate modeling and calculation, timely risk identification, and proactive early warning intervention, significantly improving the safety and responsiveness of line operation.

The application discloses a polar ship icing condition limit stability evaluation method and system, and the method comprises the following steps: obtaining ship data and environmental parameters, inputting a dynamic icing calculation model, and calculating the ship icing distribution; obtaining the ship stability righting lever curve according to the real-time motion state of the ship and the ship icing distribution, processing the ship stability righting lever curve, and obtaining the dynamic stability curve; calculating the limit dynamic inclination and the maximum dynamic inclination lever under different icing conditions based on the dynamic stability curve, and solving the limit wind speed and the wind scale that can be borne by the ship under different icing conditions according to the calculation results, and comprehensively evaluating and judging the limit stability of the polar ship. The application realizes the dynamic update of the icing distribution with the change of the ship motion state by obtaining the state change parameters corresponding to the ship at each time step based on the six-degree-of-freedom motion equation of the ship, and the total amount of flying spray is calculated by combining the sea wave spray and the wind-generated flying spray, so that the ship stability analysis combines the icing and the wind wave, and the accuracy and the reliability of the stability evaluation are improved.

This invention proposes a method for monitoring early icing of aircraft based on ultrasonic pulse echo. The input parameters of this method include echo signals from ice-free structures, echo signals from iced structures, and the surface temperature of the structures. By analyzing and processing these input signals using the proposed method for early icing warning and ice thickness measurement based on ultrasonic pulse echo, early icing warning information and surface ice thickness data can be obtained, providing a basis for the activation and deactivation of the aircraft icing protection system. This invention can reduce the energy consumption of the aircraft icing protection system when removing ice from the aircraft surface, improving energy efficiency while ensuring flight safety, and has promising application prospects.

The application relates to a distributed electric heating icing protection system and relates to the technical field of electric heating deicing of an airplane, and comprises a surface coating layer covering the surface of the airplane skin, an electric heating layer and a detection layer below the surface coating layer; wherein the electric heating layer and the detection layer are arranged in layers, and are both distributed one-to-one unit structures; the heating components of the electric heating layer of each unit are uniformly arranged; the detection layer of each unit is provided with a detection element for detecting the icing condition; and the electric heating layer and the detection layer of each unit structure are independently controlled by a controller. Compared with the prior art, the uniformity of heat emission can be improved, and the deicing effect is better.

The invention provides a thyristor control method for an aircraft electric pulse deicing device, relates to the technical field of thyristor control and regulation, and aims to acquire and fuse multi-dimensional working condition data such as icing thickness, icing rate, environment temperature, environment humidity and flight data in real time, and calculate attitude influence factors to realize the control of the aircraft electric pulse deicing device according to the real-time attack angle and roll angle change of the aircraft. The icing aggravation trend of different pneumatic surfaces is predicted, the comprehensive icing severity index ISI is calculated for real-time quantitative evaluation, the deicing action can be automatically triggered in the early stage or the middle stage of ice condition development according to the icing speed, the low predefined interval, the middle predefined interval and the high predefined interval are judged according to the value of the ISI, and the deicing effect is improved. Compared with the prior art, the method has the advantages that deicing strategies with different emergency degrees are directly mapped, a time window from icing risk identification to effective deicing intervention application is shortened through a dynamic pre-judgment and hierarchical response mechanism, the coping capacity for sudden strong icing working conditions is improved, and the flight safety risk caused by untimely deicing is effectively reduced.

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 a flight safety assessment method and device based on icing condition inversion and uncertainty quantification. The method comprises the following steps: acquiring icing observation data on the surface of an aircraft; generating ice type prediction data based on the forward prediction model; defining an observation difference index through the icing observation data and the ice type prediction data; modeling an icing condition inversion problem as a Bayesian inversion problem for solving the flight environment parameter posterior probability distribution; performing adaptive iterative sampling in a parameter space through an adaptive Monte Carlo sampling algorithm to generate posterior probability distribution of the flight environment parameters; based on the posterior probability distribution, constructing an uncertainty quantification result of the icing condition; and generating a flight safety assessment result through the uncertainty quantification result. According to the method, the reliability and robustness of aircraft icing simulation and prediction can be remarkably improved, and the method has wide application value in aircraft design, airworthiness pre-analysis and icing test planning.

The invention relates to a distributed electric heating icing protection system, which relates to the technical field of aircraft electric heating deicing, and comprises a surface coating layer covering the surface of aircraft skin, and an electric heating layer and a detection layer below the surface coating layer, wherein the electric heating layer and the detection layer are arranged in a layered mode and are each of a distributed one-to-one unit structure, heating assemblies of the electric heating layer of each unit are evenly arranged, the detection layer of each unit is provided with a detection element used for detecting the icing condition, and the electric heating layer and the detection layer of each unit structure are independently controlled by a controller. Compared with the prior art, heat dissipation uniformity can be improved, and the deicing effect is better.

This invention discloses a method for analyzing and monitoring the stress on conductors under icing conditions, relating to the technical field of conductor monitoring. Upon detecting signs of icing retreat, the system acquires conductor state data within the icing retreat trigger window, forming a comparison segment before and after retreat. Based on this, it calculates the retreat morphology index, stress release index, and stress transmission closure index, further obtaining an ice-rebound risk index to determine whether icing retreat corresponds to true stable recovery. Therefore, the system no longer simply cancels the warning based on reduced icing thickness, decreased static tension, or sag recovery, but comprehensively judges whether the icing retreat morphology is stable, whether the stress release has converged, and whether cross-span disturbances have closed. When there is local detachment, segmented residue, eccentric residue, or cross-span stress transfer, the warning continues or an inspection is triggered, thereby identifying secondary risks caused by ice-rebound, residual ice overloading, and stress redistribution, reducing the possibility of prematurely canceling the warning and missing cascading stress anomalies.

Wind turbine, control system, and method of operating a wind turbine (1) under potential icing conditions to reduce vibrations during idling or standstill operation, comprising: determining a potential icing condition for one or more blades (2,3,4), establishing a danger zone (10) where the falling of ice is to be avoided, identifying a risk of falling ice within the danger zone (10, wherein if a risk of falling ice in the danger zone (10) is identified, the method comprises: a) setting a pitch angle (P) of a first rotor blade (2) close to 0º, wherein a one or more further blades (3,4) comprise a pitch angle (P) differing by at least 30º from the first rotor blade (2); and b) adjusting the rotor yaw orientation (W) away from the danger zone (10).

Ice detection test apparatuses, systems, and methods are disclosed. In some cases, ice detection and precautionary system shut-down event reduction systems and related methods are provided. The system utilizes a turbine engine ice detection apparatus that includes and engine pressure simulation device, an air moving device, and a first air pressure sensor associated with the engine pressure simulation device. The embodiment further includes an ice monitor controller that receives inputs from the first air pressure sensor and at least one second sensor located adjacent a turbine engine intake. The ice monitor controller performs comparisons of inputs from these sensors against each other and stored values to determine actual icing conditions then generate warnings on a display to an operator. The exemplary control section has multiple modes including manual, semi-manual and automatic.

The present invention relates to an icing detection system for an aircraft, comprising: a first detector arranged in a first region of a nose of the aircraft and symmetrically arranged on both sides of the nose with respect to a symmetry plane of the aircraft; the second detectors are arranged in a second area of the nose of the aircraft and symmetrically arranged on the two sides of the nose with respect to the symmetry plane of the aircraft, and the second area is located on the rear side of the first area in the heading direction of the aircraft; and the icing signal processing device integrates the icing signals fed back by the first detector and the second detector, and judges whether the aircraft encounters a conventional icing condition or a supercooled large-water-drop icing condition. The icing detection system can detect and discriminate the overcooled large water drop icing condition existing in the flight environment where the aircraft is located, is high in reliability, can reduce misjudgment, and is suitable for various working conditions of the aircraft. In addition, the invention also relates to an icing detection method and an aircraft.

According the present invention, air velocity and speed of sound which can be used to estimate air temperature can be measured from a sonic anemometer system attached to an airborne platform. Using multiple sonic emitters and receivers coupled to an assembly attached to an airborne platform where the atmosphere is free to pass through the volume between the acoustic elements, air data products can be estimated from the acoustic transit time between acoustic emitters and receivers for use in an airborne data system. The measurement method has high update rates and is resilient against acoustic noise and icing conditions making it a robust sensing platform for use on aircraft.

A supercooled large droplet icing detector capable of automatically adapting to a sideslip angle of an aircraft, and an aircraft. The supercooled large droplet icing detector capable of automatically adapting to a sideslip angle of an aircraft comprises a probe (1), a wind vane structure (2), a transition structure (3), a support structure (4), a bearing (6), and a rotating shaft (7), wherein a first icing sensor (21) and a second icing sensor (22) are arranged on the probe (1), and are used for detecting an icing condition and distinguishing a supercooled large droplet icing condition; the wind vane structure (2) is connected between the probe (1) and the transition structure (3), and is used for automatically adjusting the probe (1) to follow the airflow direction under the action of wind; the transition structure (3) is connected between the wind vane structure (2) and the rotating shaft (7), and is used for generating an eccentric effect, so that the rotating shaft (7) can be driven to rotate under the force of the wind vane structure (2); the support structure (4) is mounted to an aircraft skin (5), and is used for supporting the supercooled large droplet icing detector; the bearing (6) is sleeved on the outer side of the rotating shaft (7), and is used for supporting and lubricating the rotating shaft (7) to rotate.

This application relates to the field of aircraft door mechanisms, specifically a door pressurization and prevention mechanism applied to aircraft doors, which enables control of the door pressurization and prevention mechanism's movement trajectory. It achieves control over the door's opening and closing movement trajectory, allowing the sealing strip to gradually move away from the door skin during closing. This solves the problem of traditional fixed-axis rotating pressurization and prevention doors where the sealing strip near the rotating shaft is "clamped" or excessively compressed, leading to increased operating force. Simultaneously, through the design of the pressurization and prevention door's opening and closing movement trajectory, the initial opening direction of the door can be rationally selected, achieving higher opening and ice-breaking efficiency and solving the problem of rapid opening under icing conditions. It also prevents the pressurization and prevention door from reversing its driving mechanism, improving safety.

The invention belongs to the technical field of anti-icing and deicing system test evaluation, and discloses a discontinuous maximum icing test area selection and flight test method, which comprises the following steps: step 1, predicting the cumulus icing probability and the cumulus icing strength corresponding to a cloud layer by using a refined cumulus icing weather forecasting platform, and completing discontinuous maximum icing condition airspace capture; 2, based on the safety and the data validity, establishing a discontinuous maximum icing condition test area selection criterion, and selecting a proper test area in a discontinuous maximum icing condition environment given by the forecasting platform; 3, debugging the icing meteorological detection equipment, and confirming that the key physical parameters are accurately measured; and 4, completing the design of a natural icing test flight program in the intermittent maximum icing environment, and carrying out the function verification of the anti-icing and deicing system under the intermittent maximum icing condition. According to the invention, the problem that existing aircrafts do not carry out flight tests under the cumulus cloud condition is solved, and the success rate and the efficiency of test flight under the extreme climate condition are improved.

The invention provides a cable deicing device based on a floating airship, and relates to the technical field of cable deicing equipment, and the cable deicing device comprises an airship which comprises an airship main body and a helium tank fixed below the airship main body, and a pipeline of the helium tank is communicated with an air bag of the airship main body; the mechanical claws are arranged on the front portion and the rear portion of the lower portion of the airship body correspondingly; the deicing device is mounted below the airship main body; the deicing device comprises a mounting base and two deicing subunits, the mounting base is fixedly hung below the airship body, and the two deicing subunits are fixed to the mounting base in the advancing direction of the airship; the deicing subunit comprises a motor and two rotating shafts, each rotating shaft is connected with a plurality of ice beating heads, and the petal-shaped part of each ice beating head is provided with an ice beating rod, so that the ice beating heads are driven to rotate through the rotating shafts, and ice on the cable is removed through the ice beating rods. According to the deicing device, the deicing effect under the complex icing condition is guaranteed, and meanwhile the cruising ability of the deicing device and the adaptive capacity of the deicing device in the severe environment are improved.