808results about "De-icing equipments" patented technology

An integrated ice detector and ice protection system is provided. The integrated ice detector and ice protection system includes an electric resistance heater element layer, a sensing element, and at least one second electrically insulative layer positioned between the electric resistance heater element layer and the at least one first electrically insulative layer with the sensing element. The sensing element is disposed in at least one first electrically insulative layer and wherein the sensing element is positioned outward from the electric resistance heater element layer.

The application relates to the field of aviation deicing technology, and particularly discloses a low-energy-consumption deicing system and control method for limited onboard energy, which comprises: a plurality of deicing subzones, which are arranged symmetrically along an aircraft body axis; each deicing subzone is provided with independent heating devices and vibration devices; the heating devices are used for melting ice layers to reduce the adhesion between the ice layers and the skin; the vibration devices are used for making the skin produce pulse vibration so that the ice layers on the skin fall off; and a subzone control module is used for carrying out subzone round control on the plurality of deicing subzones, so that the plurality of deicing subzones carry out deicing work in turns, and the deicing subzones carrying out deicing at the same time are symmetric along the aircraft body axis. The application greatly reduces the energy demand of the deicing technology while ensuring the deicing efficiency.

The invention discloses a deicing system real-time state evaluation and fault prediction method and system, and the method comprises the steps: simulating the fault state of a deicing system through a ground state monitoring test of the deicing system, and obtaining sensor data in different fault states; constructing a data set by using sensor data in different fault states to train a state evaluation model and a fault prediction model; the method comprises the following steps: installing a sensor on an aircraft deployed with a deicing system to collect working data of the deicing system; and inputting data acquired by the sensor into the trained state evaluation model and the fault prediction model, evaluating the real-time state of the deicing system, and predicting possible faults. According to the invention, the current working state of the anti-icing and deicing system can be evaluated according to the current state monitoring data, and possible faults of the system can be predicted.

The invention relates to an electrically insulating composite material (40), characterized in that the material is a composite material comprising a matrix (42) made of an elastomer or a polymer, and inclusions (41) providing the material with a thermal conductivity of greater than 0.6 W / mK at room temperature, in particular greater than 1.5 W / mK at room temperature.

An assembly for an aircraft propulsion system (20) includes a propulsion module (24), a gas generator (26) and an anti-icing system (28). The propulsion module (24) includes an open propulsor rotor (30). The gas generator (26) is configured to drive rotation of the open propulsor rotor (30) and includes a flowpath (74), a compressor section (69), a combustor section (70), a turbine section (71) and an exhaust section (72). The flowpath (74) extends through the compressor section (69), the combustor section (70), the turbine section (71) and the exhaust section (72). The turbine section (71) is axially between the combustor section (70) and the open propulsor rotor (30) along the axis (22). The anti-icing system (28) is configured to bleed gas from the flowpath (74) in the exhaust section (72) to provide heated gas and to direct the heated gas to the propulsion module (24) to reduce or prevent ice accumulation on an exterior surface (50, 66, 108) of the propulsion module (24).

An assembly is provided for an aircraft propulsion system. This assembly includes a propulsion module, a gas generator and an anti-icing system. The propulsion module includes an open propulsor rotor. The gas generator is configured to drive rotation of the open propulsor rotor about an axis. The gas generator includes a flowpath, a compressor section, a combustor section, a turbine section and an exhaust section. The flowpath extends through the compressor section, the combustor section, the turbine section and the exhaust section. The turbine section is axially between the combustor section and the open propulsor rotor along the axis. The anti-icing system is configured to bleed gas from the flowpath in the exhaust section to provide heated gas. The anti-icing system is configured to direct the heated gas to the propulsion module to reduce or prevent ice accumulation on an exterior surface of the propulsion module.

The invention relates to an air system for an aircraft, that includes air consumers; air sources and a network of ducts and associated control valves controlled by a control unit. The air system is characterized in that: the network of ducts and associated valves includes at least one isolation valve, arranged between an air bleed device and an air duct connecting an air conditioning pack and an auxiliary power unit; the control unit is configured to be able to determine an ideal configuration of the control valves according to the identified requirements of each consumer and a degraded configuration that makes it possible to supply air to predetermined air consumers from the available air sources when the ideal configuration is not attainable.

The present disclosure provides for pneumatic deicer boot assemblies, and related methods of fabrication and use. More particularly, the present disclosure provides for bartack stitched pneumatic deicer boot assemblies for aircraft or the like, with the bartack stitched pneumatic deicer boot assemblies having an inflatable carcass formed by two layers (e.g., a stretchable layer and a non-stretchable layer) stitched together using bartack stitches.

The invention discloses a wing icing full-period sensing and early warning method, and belongs to the field of aircraft icing detection and early warning. The method comprises the following steps: firstly, acquiring cloud particle data, flight parameter sensing data and planar electrode icing detection data; then, the cloud particle data and the flight parameter data are preprocessed, and the impact efficiency of the cloud particles impacting the surface of the wing and the icing mass flow rate are obtained; and finally, constructing a mixed model based on a BP neural network and a recurrent neural network, and processing the time sequence data through a long-short-term memory unit to realize prediction of the icing condition. According to the invention, a multi-scale dynamic cloud field in real flight can be monitored, the ice thickness and the ice type of predicted icing can be output in real time, and at the same time, multi-stage early warning thresholds are set to realize gradient early warning output of potential risk prompts; the icing prediction result correction in the real-time flight process can be realized, and the prediction accuracy is improved; the method has the advantages of high-precision prediction, real-time monitoring, strong generalization and the like, and is suitable for icing safety protection under complex meteorological conditions.

Aircraft ice protection systems and methods include an aircraft component having an internal layer and an external layer, a piezoelectric actuator element embedded within the aircraft component between material of the internal layer and the external layer, and a control system operably connected to the piezoelectric actuator element and configured to drive actuation of the piezoelectric actuator element to at least one of remove ice formed on the aircraft component and prevent the formation of ice on the aircraft component.

The invention relates to the technical field of aviation anti-icing and deicing, and particularly discloses a low-energy-consumption deicing system for limited airborne energy and a control method.The system comprises a plurality of deicing subareas which are symmetrically arranged along the axis of a fuselage; each deicing subarea is provided with an independent heating device and an independent vibration device; the heating device is used for melting an ice layer and reducing the adhesive force between the ice layer and the skin; the vibration device is used for enabling the skin to generate pulse vibration to enable the ice layer on the skin to fall off; and the zone control module is used for performing zone round-robin control on the plurality of deicing zones, so that the plurality of deicing zones perform deicing work in turn, and the deicing zones for deicing are symmetrical along the axis of the machine body. According to the invention, the energy demand of an anti-icing and deicing technology is greatly reduced while the deicing efficiency is ensured.

A gas turbine engine is provided that includes a fan section, a compressor section, a combustion section, a turbine section, an annular fan bypass air path, a bleed air structure, an annular compartment, and an anti-icing system. The compressor section has a low and high pressure compressor sections. The fan bypass air path is defined by inner and outer bypass wall structures. An outer radial boundary structure defines an outer radial boundary of a core gas path within the low pressure compressor section. The bleed air structure is disposable in an open state or in a closed state. The annular compartment is defined by the inner bypass wall structure, the outer radial boundary structure, and a firewall. The anti-icing system is disposable in an activated state or in a deactivated state. In the activated state the anti-icing system is configured to mitigate ice accumulation within the annular compartment.

The invention belongs to the technical field of electric heating deicing, and particularly relates to a surface heating electric heating film and a preparation method thereof. Comprising an outer surface insulating layer, a heating layer, a power supply electrode and an inner surface insulating layer, the heating layer is prepared from a carbon-based conductor composite polymeric material in a printing or coating mode, and the carbon-based conductor composite polymeric material is formed by mixing polyimide resin and carbon fibers (or one or more of graphene, carbon nanotubes and the like). The surface heating electric heating film provided by the invention has the characteristics of simple and reliable structure, light weight and surface heating performance, can be applied to ice prevention and removal operation of parts such as aircraft wings, empennages, propellers and the like, and has relatively high practical application value.

A system and a method include a control unit for determining a probable de-icing status for one or more aircraft scheduled to depart from one or more airports. The control unit is configured to determine the probable de-icing status based on a current date at the one or more airports, current weather at the one or more airports, and the actual de-icing status of a plurality of prior aircraft scheduled to depart from the one or more airports before the one or more aircraft.

The invention relates to the technical field of aircraft electric heating deicing, in particular to a pulse heating aircraft deicing method and system.The method comprises the following steps that the ice layer thickness, the ice layer type, the airspeed and the attack angle of each aircraft surface area are collected, the inherent pneumatic sensitivity coefficient of each area is called, the aerodynamic penalty index of each area is established, and the aerodynamic penalty index of each area is calculated; and according to the values of the aerodynamic penalty indexes of the areas, performing descending order arrangement to generate a deicing area priority sequence. Through multi-parameter joint evaluation of the ice layer thickness, the ice layer type, the airspeed and the incidence angle, the heating resource distribution sequence is optimized, energy waste is avoided, in the local heating execution stage, temperature change slope real-time monitoring is adopted to replace fixed time control, the actual thermal response behavior of the ice layer can be dynamically responded, and the real-time thermal response performance of the ice layer is improved. The initial phase change process of the ice crystal is identified through a phase change starting slope threshold value, and then a medium-power pulse control mode is switched, so that a steady-state regulation heating path is formed, and the phase change control continuity is strengthened.

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 a laser processing microstructure electric heating anti-icing and de-icing skin and a using method thereof.The laser processing microstructure electric heating anti-icing and de-icing skin comprises a skin body arranged on the surface of an airplane, the skin body comprises an electric heating microstructure anti-icing and de-icing skin body, a microstructure anti-icing and de-icing skin body and a common skin body, and the input end of the electric heating microstructure anti-icing and de-icing skin body is connected with an airborne power source through a wire; the electric heating micro-structure anti-icing and deicing skin is arranged on the windward side, with the maximum airflow collection coefficient, of the outer surface of the aircraft, the micro-structure anti-icing and deicing skin is arranged on the upstream and downstream of the windward side of the outer surface of the aircraft, and the common skin is arranged on other parts, except the electric heating micro-structure anti-icing and deicing skin and the micro-structure anti-icing and deicing skin, of the outer surface of the aircraft. According to the laser processing microstructure electric heating anti-icing and deicing skin and the using method thereof, through matched arrangement of the electric heating microstructure anti-icing and deicing skin and the microstructure anti-icing and deicing skin, the purposes of being good in anti-icing and deicing effect, low in energy consumption, light in weight and good in maintenance performance can be achieved.

The invention relates to a method for detecting aircraft icing of an aircraft, the method comprising the following steps: - Recording at least a part of an outer flow surface of the aircraft by means of at least one optical image sensor of a detection device and generating digital image data containing the recorded part of the outer flow surface of the aircraft, - inputting the digital image data into a machine learning system of the detection device as input data, which has learned a correlation between digital image data as input data and various types of aircraft icing as output data by means of at least one machine-learned decision algorithm in order to obtain output data, and - Detecting aircraft icing depending on the output data received and, if aircraft icing has been detected, classifying the aircraft icing with regard to at least one icing type depending on the output data received.

The invention relates to a system (10) for de-icing the blades (14) of the propeller (12) of an aircraft, the system comprising an H-bridge inverter device (40); a rotary transformer (22) comprising a main primary winding (26), a primary measurement winding (28), and a secondary circuit (30) delivering a secondary alternating voltage (Vs); a rectifier device (50); a de-icing device (20); a control device (60) configured to control the switching elements of the inverter device in an out-of-phase manner, using the value of the voltage (Vpm) across the terminals of the primary measurement winding, measured during a measurement interval of predetermined duration starting at the instant (t11,t33) when the inverter device switches from a controlled state to a short-circuit state.

The invention relates to the technical field of aviation equipment, and discloses a wing-shaped structure suitable for anti-icing and deicing, which comprises a shell and an electric heating piece, an electric heating piece is arranged in a shell, a first heating layer is formed on the upper wing face and the lower wing face of the inner wall of the shell, a second heating layer is formed on the front edge of the inner wall of the shell, the first heating layer and the second heating layer are electrically connected, and the first heating layer and the second heating layer are connected with an external power source through an electrode layer so that power can be supplied to the electric heating piece, and temperature distribution of different parts can be controlled. After the electrode layer conducts electricity, a first temperature area is formed on the first heating layer, a second temperature area is formed on the second heating layer, and the temperature of the first temperature area is lower than that of the second temperature area, so that it is guaranteed that the front edge of the airfoil structure is kept at the high temperature, and the deicing and anti-icing requirements are met. According to the airfoil structure suitable for anti-icing and deicing, differentiated heating can be conducted according to icing characteristics of different parts of the airfoil structure, it is guaranteed that the anti-icing and deicing requirements are met, meanwhile, energy consumption is reduced, and the energy utilization rate is increased.

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.

Aircraft ice protection systems and methods include an aircraft component (200) having an internal layer (202) and an external layer (204), a piezoelectric actuator element (208) embedded within the aircraft component (200) between material of the internal layer (202) and the external layer (204), and a control system operably connected to the piezoelectric actuator element (208) and configured to drive actuation of the piezoelectric actuator element (208) to at least one of remove ice formed on the aircraft component (200) and prevent the formation of ice on the aircraft component (200).

The invention provides an electric heating shock-resistant leading edge and a using method thereof.The electric heating shock-resistant leading edge comprises an outer side skin, a leading edge heating layer, a leading edge inner skin, an energy absorption structure layer, an energy absorption inner skin, ribs and a control module which are sequentially arranged in a stacked mode from outside to inside, the energy absorption structure comprises a Z-shaped body and a supporting body, one end of the supporting body is connected with the end of the Z-shaped body, the other end of the supporting body is connected with a bent portion of the Z-shaped body, the Z-shaped body is connected to the front edge inner skin, the supporting body is made of negative thermal expansion materials, and a probe is arranged at the position, corresponding to the supporting body, of the rib and comprises a pressure sensor and a distance monitor. And the probe and the front edge heating layer are electrically connected to the control module. The electric heating deicing function of bird impact resistance and automatic control of the front edge structure is achieved, the temperature control reliability is improved, the structural weight is reduced, and the technical problems of temperature control, bird impact resistance, structural weight reduction and the like are solved.

An air data reasoner system for evaluating aircraft sensor data obtained from aircraft sensors performs the following steps to generate organized outputs of aircraft sensor data. The system receives aircraft parameter values for various aircraft parameters from the plurality of aircraft sensors. The system selects applicable performance models for the aircraft parameter values from the repository of performance models. The system executes the applicable performance models to generate accuracy values corresponding to each of the aircraft parameter values. The system determines the most accurate parameter values and corresponding source aircraft sensor. The system compiles a list of available redundant source aircraft sensors. The system generates a threshold table with operating thresholds for each parameter. The system outputs the most accurate parameter values, the corresponding source aircraft sensors, the list of available redundant source aircraft sensors, and the threshold table to consuming systems.

The application discloses a kind of deicing system real-time state evaluation and fault prediction method and system, the method includes: through the ground state monitoring test of deicing system simulates deicing system fault state, obtains the sensor data under different fault states;Different fault states are used to train state evaluation model and fault prediction model by the sensor data set constructed with data;Sensor is installed on the aircraft deployed with deicing system, to collect the working data of deicing system;The data collected by sensor is input into trained state evaluation model and fault prediction model, the real-time state of deicing system is evaluated, and the possible fault is predicted.The application can evaluate current anti-icing system working state according to current state monitoring data, and predict the possible fault of system.

Provided are embodiments for method and system for performing an integrated ice protection with prognostics and health management using fiber optic sensors. Embodiments can include reading a signal from each sensor of an array of sensors installed on a surface of a structure or equipment, wherein each sensor is a fiber optic sensor, and generating a map based on reading the signal from each sensor, wherein the map monitors a condition of the surface detected by each sensor. Embodiments can also include determining at least one of an abnormal condition or a failure based at least in part on reading the signal from each sensor; and performing at least one of adjusting power control for the structure or equipment or communicating the abnormal condition or failure of the structure or equipment.

The air inlet functional lip component of the unmanned aerial vehicle comprises a functional lip, the outer end of a functional lip body is provided with an outer side connecting part, and the inner end of the functional lip body is provided with an inner side connecting part; the outer side connecting part comprises an elastic shifting piece fixed to the outer end of the functional lip body, the free end of the elastic shifting piece is provided with a locking block, and the locking block is matched with a locking groove formed in the outer wall of the air inlet channel; the inner side connecting part comprises a positioning pin, and the positioning pin is matched with a positioning sleeve on the inner wall of the air inlet channel; the locking block on the elastic shifting piece is pressed to the inner side of the outer wall of the air inlet channel, moves forwards and then is inserted into the locking groove to be locked, so that the positioning pin is inserted into the positioning sleeve while the functional lip body and the outer wall of the air inlet channel are fixed, and the functional lip body and the inner wall of the air inlet channel are fixed. The component can realize quick disassembly and assembly, connection stability and sealing performance of the lip, and the maintenance efficiency and reliability of the unmanned aerial vehicle are improved. The invention further discloses an unmanned aerial vehicle which has the same advantages.