1045results about "De-icing equipments" patented technology

A disclosed water droplet sensing system and methods using split-ring resonators, which may be embedded within a material. In use, a component includes at least one split-ring resonator (SRR) which may be embedded within a material of the component. The at least one SRR may be formed from a composite material. Additionally, the at least one SRR may be configured to form a signal that is correlated with a concentration of water proximate to the at least one SRR. In some aspects, each SRR may resonate at a first frequency in response to an electromagnetic ping when the material is in a first state, and may resonate at a second frequency in response to the electromagnetic ping when the material is in a second state. A resonant frequency of the material may be based on physical characteristics of the material (including fluid accumulation on the material).

The invention discloses an intelligent deicing method and system based on ultrasonic detection, a medium and equipment, and relates to the technical field of deicing. The intelligent deicing method based on ultrasonic detection is used for the intelligent deicing system and comprises the following steps that the surface temperature of an airplane is detected based on an infrared sensor, and the surface temperature value of the airplane is obtained; comparing the airplane surface temperature value with a temperature threshold value; if the aircraft surface temperature value is greater than the temperature threshold value, continuing to detect the aircraft surface temperature based on the infrared sensor; if the aircraft surface temperature value is smaller than or equal to the temperature threshold value, an ultrasonic pulse echo icing sensor is started to detect the icing thickness of the aircraft surface, and icing signal information is obtained; and based on the icing signal information, whether the automatic deicing system of the airplane is started for deicing treatment is judged. Through the steps, the deicing efficiency of the aircraft during flight is improved.

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 invention relates to an anti-icing-deicing composite surface and a preparation method thereof, and belongs to the field of anti-icing and deicing. The surface comprises a porous material substrate, a super-hydrophobic / hydrophobic lubricating fluid top microstructure and a hydrophobic / hydrophilic lubricating fluid internal microstructure, wherein the super-hydrophobic / hydrophobic lubricating fluid top microstructure and the hydrophobic / hydrophilic lubricating fluid internal microstructure are coupled to the surface of the porous material substrate; lubricating fluid is injected into the surface of the hydrophobic / hydrophilic lubricating fluid internal microstructure; the super-hydrophobic / hydrophobic lubricating fluid top microstructure is located on the surfaces of a plurality of columnar bodies arranged on the porous material substrate in an array mode, namely, the super-hydrophobic / hydrophobic lubricating fluid top microstructure has the super-hydrophobic characteristic to water and lubricating fluid. And the hydrophobic / lubricating fluid-loving internal microstructures are also arranged in the array form, surround the root of each cylindrical object, and have the characteristics of lubricating fluid loving and hydrophobicity. The surface can have anti-icing / ice-dredging properties of super-hydrophobic and super-smooth properties at the same time, that is, the surface can have excellent anti-icing properties of a super-hydrophobic surface, and can also be ice-dredging like a super-smooth surface after the surface is iced, so that ice is easier to remove.

The invention belongs to the field of aircraft anti-icing and de-icing, and particularly relates to an electric heating anti-icing and de-icing system and method based on a distributed optical fiber temperature sensor, and the system comprises the distributed optical fiber temperature sensor, a controller, and a heating assembly. The surface of the wing is divided into different subareas and numbered, and at least one heating assembly is arranged in each subarea; the distributed optical fiber temperature sensors are made of optical fibers, are pre-buried in the wing skin and pass through all the subareas, and each subarea is internally provided with at least two temperature measuring points; the distributed optical fiber temperature sensor is used for collecting temperature data of the surface of the wing and sending the temperature data to the controller; and the controller compares the temperature of each subarea with a theoretical temperature, when the temperature of each subarea is lower than the lower limit of the theoretical temperature, the heating assembly of the corresponding subarea is controlled to start heating, and when the temperature of each subarea is higher than the upper limit of the theoretical temperature, the heating assembly of the corresponding subarea is controlled to stop heating.

The embodiment of the invention provides an automatic activation control method for an intelligent anti-icing and snow-removing control system, and the method comprises the steps: dividing an anti-icing and snow-removing heating region based on the real-time temperature and icing condition data of the surface of an airplane; when it is detected that the icing risk exists in the specific area, the heating device in the corresponding area is activated; dynamically adjusting the power of each heating area according to the environment condition and the flight state; and the working state of each heating area is recorded and analyzed, and the future partitioning strategy is optimized to improve the energy efficiency ratio. Through the scheme of the embodiment of the invention, the problem of how to intelligently partition the heating area to solve the balance problem between the energy consumption and the anti-icing efficiency can be solved.

The invention provides an electric heating fabric and a preparation method and application thereof.The electric heating fabric comprises fiber cloth, an electric heating film is arranged on the surface of one side or two sides of the fiber cloth, the electric heating film has a wave-transparent function and is formed by curing conductive slurry, and the conductive slurry comprises resin, a dispersing agent, a carbon material, a functional compound and a solvent; the functional compound comprises a nitrogen-containing compound and / or an acidic compound; the specific functional compound is added into the preparation raw materials of the electric heating film, and the interface bonding performance between the electric heating film and the composite material is effectively improved by utilizing the cross-linking reaction between the functional compound and the resin in the composite material; therefore, the long-term stability and reliability of the obtained electric heating fabric and the integrated composite material thereof in an extreme use environment can be ensured, and the electric heating fabric has a wave-transparent function and is suitable for being applied to the surface of an aircraft.

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.

An inlet assembly of a nacelle includes an inlet cowl that has a leading edge, an outer side that extends from the leading edge to an outer aft edge, and an inner side that extends from the leading edge to an inner aft edge. An exterior surface of the inlet cowl is seamless along an entire length of the outer side from the leading edge to the outer aft edge. The inlet cowl includes a lipskin that has a metallic coating. The metallic coating defines the exterior surface of the inlet cowl along the leading edge and the entire length of the outer side.

An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inlet structure which extends axially along and circumferentially around a centerline. The nacelle inlet structure includes an inlet lip, an inner barrel, an outer barrel and a plurality of structure segments. The inlet lip forms a leading edge of the nacelle inlet structure. The inner barrel projects axially aft away from the inlet lip. The outer barrel projects axially aft away from the inlet lip. The outer barrel is radially outboard of and axially overlaps the inner barrel. Each of the structure segments includes an exterior skin, a mount and an electric heater configured to heat the exterior skin. The exterior skin forms a respective circumferential section of the inlet lip and a respective circumferential section of the outer barrel. The mount is bonded to the exterior skin and mechanically attached to the inner barrel.

The invention relates to the field of helicopter wing anti-icing and deicing, in particular to a helicopter anti-icing and deicing system applying rotor wing kinetic energy recovery and an operation method. The helicopter anti-icing and deicing system applying rotor wing kinetic energy recovery comprises an electric heating deicing device, a kinetic energy recovery device and a helicopter rotor wing key assembly. The electric heating deicing device is composed of a high-resistivity metal heating wire and an icing detector, and the device transfers heat to the surface of the wing for deicing through heating of the high-resistivity heating wire. The kinetic energy recovery device is composed of an electric energy rectification, voltage stabilization and energy storage device, a permanent magnet and a magnetic induction coil. Kinetic energy generated when the rotor rotates is converted into electric energy through the electromagnetic induction technology and stored in a battery pack. The helicopter rotor key assembly is composed of a helicopter blade and a helicopter swash plate and is a key component of the helicopter rotor. According to the invention, the kinetic energy of the helicopter rotor is recovered to prevent and remove ice, so that the overall energy utilization efficiency is improved, and the environmental adaptability and safety of the system are also improved.

The invention belongs to the technical field of ice prevention and removal, and relates to a combined unmanned aerial vehicle automatic deicing system. The system comprises a deicing controller, and an icing detection subsystem, an engine air inlet channel anti-icing subsystem and a wing empennage airbag deicing subsystem which are connected with the deicing controller, the icing detection subsystem is used for detecting whether the unmanned aerial vehicle is iced or not and the icing degree and outputting an icing signal; the deicing controller controls whether the engine air inlet channel anti-icing subsystem and the wing empennage air bag deicing subsystem work or not according to icing signals output by the icing detection subsystem.

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.

A system is provided for an aircraft. This aircraft system includes an engine, a fuel system and an air system. The fuel system includes a fuel circuit, a fuel source, a heat exchanger and a turboexpander. The fuel circuit is configured to direct fuel from the fuel source, through the heat exchanger and the turboexpander, to the engine for combustion. The heat exchanger is configured to transfer heat energy from combustion products generated by the combustion of the fuel in the engine into the fuel in the fuel circuit. The air system is discrete from the engine. The air system includes an air compressor and the turboexpander. The air system is configured to expand the fuel directed across the turboexpander by the fuel circuit to power operation of the air compressor.

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 provides an aircraft icing detection method and device and an aircraft, and relates to the technical field of icing detection.The method comprises the steps that a first data set of the aircraft at a first time point and a second data set of the aircraft at a second time point are obtained, and meanwhile total temperature data of the second time point are obtained; comparing the second data set with the first data set to detect a change in the aircraft exterior environment or windshield field of view; if the change in the external environment of the aircraft and the view field of the windshield shows visible moisture, and the total temperature data is lower than a preset threshold value, it is judged that the change in the external environment of the aircraft and the view field of the windshield meets a first icing condition. According to the invention, the workload of a pilot in icing judgment can be reduced, and the flight safety performance is further improved.

The invention provides a low-energy-consumption mechanical anti-icing and de-icing device and method and an aircraft skin structure, and the device comprises a passive anti-icing part which comprises an elastic interlayer, and the elastic interlayer is used for being adhered to the first side face of a skin of an aircraft; the elastic interlayer at least comprises a lubricating material capable of reducing the ice adhesion strength; the active deicing part comprises a force applying device, and the force applying device faces the second side face, away from the first side face, of the skin; wherein the aircraft is frozen to form an ice layer-elastic interlayer-skin three-layer structure under the freezing condition, the force application device applies stress load to the second side face of the skin, and the ice layer is actively induced to be broken; through deformation of the elastic interlayer, stress load is concentrated on the ice layer, critical fracture displacement needed for inducing fracture of the ice layer is passively reduced, and meanwhile, through the anti-adhesion effect of the elastic interlayer, the fractured ice layer is promoted to fall off from the elastic interlayer. Through the device provided by the invention, efficient deicing with low energy consumption, repeated use and no damage to the skin structure is realized.

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.

The invention provides an anti-icing and de-icing structure function integrated electric heating material for wings and a preparation method and application thereof, and relates to the technical field of aerospace anti-icing and de-icing, and the preparation method comprises the following steps: taking fiber cloth obtained by weaving pre-oxidized fibers and carbon fibers as a raw material, and carbonizing the fiber cloth to obtain the electric heating material, and packaging the electric heating material to obtain the electric heating material for the anti-icing and de-icing structure and function integrated wing. Wherein the pre-oxidized fiber is a PAN (Polyacrylonitrile)-based pre-oxidized fiber. According to the preparation method of the electric heating material for the anti-icing and de-icing structure and function integrated wing, the electric heating efficiency of the aircraft wing can be remarkably improved while the material is uniformly heated.

A system and a method include a heating layer including perforations extending from a first surface to a second surface opposite from the first surface. The perforations provide acoustic paths. The heating layer is configured to provide electrically resistive heating to a component. An acoustic layer can be coupled to the heating layer. The perforations extend to the acoustic layer.

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.

An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inlet structure extending axially along and circumferentially about an axis. The nacelle inlet structure includes an inlet lip, an inner barrel, an outer barrel and a plurality of supports. The inlet lip forms a leading edge of the nacelle inlet structure. The inner barrel projects axially aft away from the inlet lip. The outer barrel projects axially aft away from the inlet lip. The outer barrel is radially outboard of and axially overlaps the inner barrel. The supports are arranged circumferentially about the axis in an array. Each of the supports extends longitudinally along the axis. Each of the supports extends radially between and is connected to the inner barrel and the outer barrel.

The present invention belongs to the field of aircraft anti-icing systems, and particularly relates to a deicing assembly based on excitation vibration and heating. The assembly comprises: an excitation vibrator and a heater; the excitation vibrator is arranged on the inner surface of the skin and located at the edge of the ice protection area; the heater is arranged on the inner surface of the skin and located at the edge of the skin or the support part of the structural member.

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.