| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244134000 | Nature of surface | 7 |
| 20090032644 | Apparatus for Deicing a Surface of an Aircraft - An apparatus for deicing a surface of an aircraft includes a pair of adjacent movable surface elements that lie in a common plane and cover a portion of an aircraft. The pair of surface elements are connected to a reciprocating actuator through a bell crank for reciprocal movement and in opposite directions to one another. The apparatus also includes a tie bar at one end of the surface elements for maintaining the surface elements in a parallel relationship. In a second embodiment of the invention, the apparatus includes a pair of coaxial, coplanar circular disc and a reciprocating actuator for rotating the disc in opposite directions relative to one another. | 02-05-2009 |
| 20090294593 | DEVICE FOR PROTECTION AGAINST ICING FOR AIRCRAFT ENGINES AND RELATED DE-ICING METHOD - A device for protection against icing for aircraft engines including at least one sensor, sensitive to an amount of accumulated ice, arranged in the air intake of an aircraft engine, a system for measuring the amount and comparing the amount to be predetermined threshold and a triggering system for launching a response to the detection of the crossing of the predetermined threshold, the response may be an alarm, an increase in the engine power delayed by the engine control system or the return of hot air upstream of the engine. | 12-03-2009 |
| 20100155539 | IMPROVEMENTS RELATING TO TEMPERATURE MONITORING - A temperature monitoring arrangement for an electro-thermal ice protection system is provided for a slat of an aircraft wing, incorporating heater mats of composite material, wherein, in order to avoid or at least substantially reduce some of the problems associated with use of discrete temperature sensing elements, one or more optical fibre temperature sensors are embedded within the heater mats for sensing an overheating condition of each mat. Advantageously, a control system is used to monitor the temperature of the mats, and adjusts power supplied, or switches off power, in response to detection of an overheating condition. | 06-24-2010 |
| 20100243811 | ICE PROTECTION HEATER SYSTEM - There is disclosed an ice protection system for a structure ( | 09-30-2010 |
| 20110036950 | DE-ICING AND/OR ANTI-ICING SYSTEM FOR THE LEADING EDGE OF AN AIRCRAFT WING - The invention relates to a de-icing and/or anti-icing system for the leading edge of an aircraft wing or for the lip ( | 02-17-2011 |
| 20110297789 | Aircraft De-Icing System And Method - An aircraft de-icing system and method for removing the ice from the surface of an aircraft. The aircraft de-icing system reduces power requirements by allocating power from a single power source between the parting strip elements and the shed zone elements. The aircraft de-icing system may utilize a measurement of heat transfer to schedule the time necessary to shed ice from the surface of the aircraft. The de-icing system may also utilize a method for calculating the ice accumulation on the surface of the aircraft based on the outside air temperature. | 12-08-2011 |
| 20120241561 | METHOD AND APPARATUS FOR PROTECTING AIRCRAFT AND AIRCRAFT ENGINES AGAINST ICING - An aircraft engine generates engine power by burning hydrocarbon fuel such as Jet-A. A minute quantity of the fuel is burned in such a manner as to generate no engine power, and the heat generated by the burning fuel is used to protect a region of a surface of a component of an aircraft. In one application, burner assemblies are located inside the splitter of a turbofan engine and the heat generated is used to deice or anti-ice the splitter and the inlet guide vanes of the engine. In another application, burner assemblies are located in an engine nacelle to deice or anti-ice the leading edge of the nacelle. | 09-27-2012 |
| 20120261512 | FUEL CELL SYSTEM AND METHOD FOR DRYING OF EXHAUST GAS OF A FUEL CELL SYSTEM - A fuel cell system having an apparatus for gas drying that includes, but is not limited to at least one cooling element with at least one first surface and at least one detachment device. The cooling element is designed to be thermally connected to a heat sink and to come into contact with gas flowing past. The detachment device is movably held relative to the first surface and is designed to detach frozen water from the first surface. | 10-18-2012 |
| 20120312925 | ELECTROMECHANICAL ACTUATOR (EMA) HEAT SINK INTEGRATED DE-ICING SYSTEM - A de-icing system and method is disclosed. An electromechanical actuator heat sink is operable to receive heat from an electromechanical actuator, and a heat distribution element is operable to distribute heat to a surface. A heat transportation device is operable to transport heat from the electromechanical actuator heat sink to the heat distribution element. | 12-13-2012 |
| 20130032671 | METHOD AND APPARATUS FOR INHIBITING FORMATION OF AND/OR REMOVING ICE FROM AIRCRAFT COMPONENTS - Methods and systems are generally described that inhibit debris (such as ice) accretions and/or remove debris (such as ice) accretions from the exterior surface of an aircraft. In some embodiments, the invention is a system for an aircraft comprising: a component of the aircraft having a surface; a plurality of piezo-kinetic actuators each positioned proximate to a portion of the surface; and a control unit coupled to the plurality of actuators, the control unit configured to actuate one or more of the actuators at one or more frequencies between about 1 Hz and about 1 kHz; wherein the actuators are each configured to introduce a displacement of the surface in three dimensions to inhibit a formation of ice on at least the portion of the surface and to break up existing ice formations on at least the portion of the surface. | 02-07-2013 |
| 20130181093 | ANTI-ICING SYSTEM, WING, AIRCRAFT, AND ANTI-ICING METHOD - Provided are an anti-icing system, wing, aircraft, and anti-icing method which prevent icing on the aircraft flying in an environment under icing conditions, using a simple configuration. An anti-icing system according to the present invention generates a pressure wave by aiming at supercooled airborne water droplets existing in a traveling direction of an aircraft (10) and thereby changes the water droplets into ice by means of the pressure wave. To impart an acceleration of, for example, 10 G to the water droplets, the pressure wave is set to produce 0.9 to 3.3 [Pa] at a predetermined location by taking attenuation into consideration. | 07-18-2013 |
| 20130187007 | BLEED AIR SYSTEMS FOR USE WITH AIRCRAFTS AND RELATED METHODS - Bleed air systems for use with aircrafts and related methods are disclosed. An example apparatus includes a turbo-compressor including a compressor having a compressor inlet fluidly coupled to a low-pressure compressor of the aircraft engine and a compressor outlet fluidly coupled to a first system of an aircraft. The turbo-compressor also includes a turbine inlet fluidly coupled to a high-pressure compressor of the aircraft engine and a turbine outlet fluidly coupled to a second system of the aircraft. | 07-25-2013 |
| 20130341465 | ON BOARD INERT GAS GENERATION SYSTEM - An on board inert gas generation system for an aircraft receives air from a relatively low pressure source such as low pressure engine bleed air or ram air and passes it to a positive displacement compressor to increase the pressure thereof to be suitable for supply to an air separation module. All or a portion of the compressed air from the positive displacement compressor may be supplied by operation of a valve to one or more other aircraft components to provide at least one of power, heat or pressure thereto. | 12-26-2013 |
| 20140346278 | THERMAL PNEUMATIC DEICING SYSTEM FOR AN AIRCRAFT RAM AIR HEAT EXCHANGER - A thermal pneumatic deicing system for deicing a RAM air heat exchanger includes an environmental control system (ECS) including a RAM air heat exchanger and an outlet, an electronics housing including a plurality of electronic components, and a duct fluidically connecting the RAM air heat exchanger and the electronics housing. The duct includes a valve. A controller is operatively connected to the valve. The controller is configured and disposed to selectively fluidically connect the RAM air heat exchanger and the electronics housing to facilitate deicing of the heat exchanger. | 11-27-2014 |
| 20150298826 | High-Speed Airplane Deicing Installation Systems and Methods - The present disclosure provides an airplane ground deicing installation that minimizes the impact of deicing operations on the airport during icing conditions. The installation does not require alteration of a normal taxi pattern and can be performed as quickly as the average separation time between take-offs. The installation allows modification of its shape to adapt to the contour of almost all types of commercial passengers airplanes operating from major airports, and simultaneously deices large surfaces of the airplane. Deicing and anti-icing fluids are applied to airplane surfaces from nozzles positioned in close proximity to the airplane's surface. Speed and adaptability to different types of airplanes, combined with a design that allows rapid relocation of the installation, are key features that make it possible to place the installation on the taxiway, close to the head of the runway it serves, such that the taxi pattern and the separation in between takeoffs are not altered as compared to the normal operations of the airport. | 10-22-2015 |
| 20160009400 | ICE PROTECTION SYSTEM | 01-14-2016 |
| 20160068272 | METHOD AND A SYSTEM FOR TREATING ICE FOR AN AIRCRAFT WINDSHIELD - A method of treating ice for a windshield of an aircraft, in which method at least two distinct de-icing zones of the windshield are defined. During a de-icing step, at least one de-icing means is activated temporarily in order to de-ice the de-icing zones in succession and in a given cycle. | 03-10-2016 |
| 20160102610 | DE-ICING AND CONDITIONING DEVICE FOR AN AIRCRAFT - The present disclosure provides a device for de-icing an air inlet lip of an aircraft nacelle. The device includes a pre-exchanger, an intake orifice of taking in low-pressure air downstream from a fan, and two high-pressure air intake orifices downstream from a compressor in addition to controlled valves and check valves installed in an air flow network. In particular, the pre-exchanger includes a low-pressure air outlet capable of opening into the air inlet lip of the aircraft nacelle via a pipe of the air flow network. | 04-14-2016 |
| 20160185457 | DEVICE FOR REMOVING DEBRIS FROM AN AERODYNAMIC STRUCTURE - A device for removing debris, such as insects and ice, from an aerodynamic structure of an aircraft and in which the aerodynamic structure has upper and lower surfaces separated by a leading edge extending along the length of the aerodynamic structure. The device includes a spine positionable so as to extend between the upper and lower surfaces over the leading edge of the aerodynamic structure, a scraping edge carried by the spine facing a direction that extends along the length, and a drive mechanism configured to move the spine in the direction so that the scraping edge scrapes debris from along the length of the aerodynamic structure. The spine is configured to bias the scraping edge against the aerodynamic structure. | 06-30-2016 |
| 20160200442 | ANTI-ICING SYSTEMS | 07-14-2016 |
| 20100012784 | Method and Apparatus for De-Icing Aircraft and other Snow or Ice Covered Surfaces - Methods and devices for deicing aircraft and other snow or ice covered surfaces. The invention is based on warm moisture-laden air or steam that can be released over the surface to be thawed. The device consists of three components: a hot water or steam boiler with an associated pump; a plenum for heating and humidifying air; and a delivery unit or head that brings the moisture-laden air or steam into contact with the surface to be de-iced or thawed. Various delivery heads are also described. | 01-21-2010 |
| 20110266393 | METHOD AND DEVICE FOR EXTERNAL DE-ICING OF AIRCRAFT - In a method for exterior de-icing of an aircraft before takeoff, a region of the aircraft to be de-iced has hot air applied thereto and is heated, the air exiting a de-icing nozzle that can be disposed in the vicinity of the region to be de-iced, hot air exiting a hot air outlet opening of the aircraft is collected and fed to the de-icing nozzle. A device for externally de-icing aircraft, having a flexible hot air channel and a de-icing nozzle disposed at a first end of the hot air channel includes a collector device for hot air exiting the aircraft and connected to a second end of the hot air channel. | 11-03-2011 |
| 20120160963 | METHOD FOR PROTECTING THE SURFACE OF AN AIRCRAFT AGAINST CONTAMINATION WITH INSECT RESIDUES AND/OR ICING - Method of protecting a part of a surface of an aircraft against contamination with insect residues and/or against icing, comprising the following steps: | 06-28-2012 |
| 20130320145 | SYSTEM AND METHOD FOR MEASURING AND METERING DEICING FLUID FROM A TANK USING A REFRACTOMETER MODULE - A system and method is provided for measuring and metering deicing fluid as it is dispensed from a tank onto an aircraft to remove ice and to prevent subsequent icing. The system can include a guided wave radar gauge mounted on the tank to measure the volume of fluid in the tank in real-time. As fluid is dispensed from the tank, the gauge measures the change in the volume of fluid in the tank and transmits the volume of fluid in the tank and the volume of fluid dispensed from the tank to a display/controller. The system can also include a refractometer module to enable the measurement of the concentration of a first constituent fluid relative to a second constituent fluid in a mixture thereof. The system can further measure the concentration of one deicing fluid constituent (e.g. glycol) mixed with another fluid constituent (e.g. water) to determine the freeze point of the deicing fluid. | 12-05-2013 |
| 20140166812 | Condenser Ice Removal for Environmental Control System - Environmental control system bleed air is cooled by a heat exchanger. A fan pulls ambient air from a ram inlet duct across the at least heat exchanger and to an outlet. An air cycle machine drives the fan. The bleed air passes downstream of the at least heat exchanger to a compressor, and then drives a first stage turbine. The first stage turbine has an outlet communicating with a condenser, and then a second stage turbine. An icing control system taps hot air downstream of the compressor. An add heat valve is selectively moveable between a first position blocking flow from the tap passage. A second position where it passes air from the tap passage to the condenser inlet, and to a point downstream of the condenser and to the second stage turbine. In a third position, the valve only communicates air from the tap passage into the condenser. | 06-19-2014 |
| 20140203146 | Method And Device For Using Hot Air To De-Ice The Leading Edges Of A Jet Aircraft - A de-icing device includes a hot air circuit including an inlet for hot air bled from an engine, and a duct connecting the inlet to an outlet of the circuit which opens towards the leading edge. The device also includes electrical heating means associated with the duct, and control means for controlling the heating means connected to detection means that detect the temperature of the hot air downstream of the heating means and are able to activate these if the detected temperature of the bled air is below a value corresponding to a minimum temperature required for de-icing, increased by a predetermined margin. The range of temperatures of the hot air supplied to the leading edge is lowered overall, whereas the minimum de-icing temperature is assured. Composite materials can be used near the leading edge without being damaged. | 07-24-2014 |
| 20140231587 | ONBOARD MIXING OF DE-ICING FLUID - The invention pertains to a de-icer for airplanes, which comprises a self-propelled vehicle ( | 08-21-2014 |
| 20150122947 | MULTI-LAYER DE-ICING SKIN FOR AIRCRAFT PLATFORMS - An ice resistant structure is provided which includes a self-supporting, structural platform, a retaining, protective layer and a subsurface anti-icing (AI) and/or de-icing (DI) layer. The retaining, protective layer is disposed over the self-supporting, structural platform. The subsurface anti-icing (AI) and/or de-icing (DI) layer is located between the self-supporting, structural platform and the retaining, protective layer. The subsurface Al and/or DI layer is a functional layer such that an Al and/or DI agent is released to a surface of the retaining protective layer by an activation mechanism responsive to a change in an environmental condition. | 05-07-2015 |
| 20150360799 | High-Speed Airplane Deicing Installation Systems and Methods - The present disclosure provides an airplane ground deicing installation that minimizes the impact of deicing operations on the airport during icing conditions. The installation does not require alteration of a normal taxi pattern and can be performed as quickly as the average separation time between take-offs. The installation allows modification of its shape to adapt to the contour of almost all types of commercial passengers airplanes operating from major airports, and simultaneously deices large surfaces of the airplane. Deicing and anti-icing fluids are applied to airplane surfaces from nozzles positioned in close proximity to the airplane's surface. Speed and adaptability to different types of airplanes, combined with a design that allows rapid relocation of the installation, are key features that make it possible to place the installation on the taxiway, close to the head of the runway it serves, such that the taxi pattern and the separation in between takeoffs are not altered as compared to the normal operations of the airport. | 12-17-2015 |
| 20170233106 | METHOD OF SAMPLING DE-ICING FLUID AND SYSTEM FOR SAMPLING DE-ICING FLUID | 08-17-2017 |
| 20080251642 | METHOD AND A DEVICE FOR DE-ICING AN AIRCRAFT WALL - A device for de-icing an aircraft wall that comprises a composite structure ( | 10-16-2008 |
| 20090095842 | Power distribution architecture for an ice protection system - An ice protection system for a vehicle is disclosed which includes a plurality of de-ice power distribution units positioned proximate to a leading edge surface of the vehicle that is susceptible to ice accretion, at least two anti-ice power distribution units located within the vehicle, spaced from the de-ice power distribution units, and a point of power regulation located within the vehicle, spaced from the power distribution units, from which power is fed to the power distribution units through independent feeder wire bundles so as to distribute line current across the system in a manner that optimizes wire weight. | 04-16-2009 |
| 20090242703 | Heating architecture for a composite fairing - A composite fairing with embedded heating architecture for ice protection includes heating elements arranged on various fairing plies for heating substantially all of the composite fairing. The heating elements are positioned to provide ice protection to substantial portions of the external surface of the composite fairing. Junctions, busbars, and plated through holes are used for delivering electric current to the heating elements on the various fairing plies. | 10-01-2009 |
| 20100078521 | DEVICE FOR DETECTING AND ELIMINATING THE PRESENCE OF A LAYER OF ICE OR LIQUID - The invention concerns a device for detecting and eliminating a layer of ice formed on the surface of an aircraft structure ( | 04-01-2010 |
| 20100096507 | HEATING DEVICE FOR DEICING AIRCRAFT PARTS - A deicing pad for attachment to an aircraft, in particular to wings, propellers or helicopter rotors, that are formed with an attachment surface for the deicing pad to rest flat on the aircraft. The deicing pad has a heating layer and at least two electrodes which make electrical contact with the heating layer. The heating layer has a layer composed of an electrically conductive lacquer that forms the heating element. | 04-22-2010 |
| 20100102172 | AIRCRAFT STRUCTURE - A heated leading edge component for an aircraft and a method of manufacture thereof. The leading edge component includes an outer skin, a supporting rib for the outer skin, and a cavity located substantially in-between the outer skin and the rib for receiving a heater. The rib is attached to the outer skin on either side of the cavity. | 04-29-2010 |
| 20100123044 | Aircraft Ice Protection System - An ice protection system ( | 05-20-2010 |
| 20100155538 | ANTI-ICING SYSTEM AND METHOD FOR PREVENTING ICE ACCUMULATION - An anti-icing system includes a component surface having a composite structure including a composite layer, and at least one heating element formed within the composite layer, wherein the heating element is configured to provide a transfer of heat to the component surface. | 06-24-2010 |
| 20100206990 | System And Method For Icemaker And Aircraft Wing With Combined Electromechanical And Electrothermal Pulse Deicing - An apparatus for ice removal from a surface has an electrically resistive layer on the surface. An actuation device is provided for mechanically disturbing the surface, as for example deflecting, deforming, or vibrating the surface. When ice has accumulated, an interface layer of ice is melted by heating the electrically resistive layer with an electric current, and an electric current is applied to the actuation device to disturb the surface and release the ice. Alternative embodiments having various forms of actuation device are disclosed. An icemaker using the ice removal apparatus for ice release is described. | 08-19-2010 |
| 20100282910 | POWER CONTROL SYSTEM - A method is disclosed for controlling the distribution of power to a plurality of devices, the method being carried out during a plurality of time periods, and the method during each time period after the first comprising: determining (S | 11-11-2010 |
| 20100288882 | Electro-expulsive de-icing system for aircraft and other applications - An apparatus for removing ice from an object (e.g., in-flight ice removal from the skin of an aircraft) includes an actuator assembly that forms an elongated electrically conductive loop. The actuator is mounted in a position enabling it to impact the object to be de-iced in response to movement of the loop that is produced by electric current pulses flowing in opposite directions in two mechanically independent loop subassemblies. The loop subassemblies include multiple electrically conductive elements interconnected at their ends using elongated flexible connectors in order to introduce a physically discontinuity that reduces any restriction of relative movement of the subassembly ends caused by the connectors, thereby achieving enhanced operation and less fatigue failure as compared to a rigid structure having encapsulated element | 11-18-2010 |
| 20100308173 | BONDING OF THERMOPLASTICS - An aircraft leading edge ice protection system. The system includes: a thermoelectric heater mat ( | 12-09-2010 |
| 20110024567 | ELECTRICAL POWER GENERATION APPARATUS FOR CONTRA-ROTATING OPEN-ROTOR AIRCRAFT PROPULSION SYSTEM - An electrical power generation apparatus is embedded in a contra-rotating propulsion system that includes overlapping first and second shafts operatively connected for counter-rotation about a common axis. The electrical power generation apparatus includes a winding mounted to one of the shafts and a field array mounted to the other of the shafts adjacent to the winding. Relative rotation of the winding and the field array induces electrical current in the winding. | 02-03-2011 |
| 20110024568 | STRUCTURAL BONDING ARRANGEMENT - A leading edge component ( | 02-03-2011 |
| 20110049300 | Ice Protection System And Method - An ice protection system and method are provided that facilitate the prevention or reduction in ice formation upon an aerodynamic surface. The ice protection system may include at least one induction coil spaced apart from an electrically conductive layer of an aerodynamic surface and disposed interior of an exterior surface of the aerodynamic surface. For example, the ice protection system may include a plurality of induction coils with each induction coil being spaced apart from the other induction coils such that the respective induction coils are associated with different portions of the aerodynamic surface. The ice protection system may also include a signal source configured to provide alternating current to the induction coil(s) to thereby generate an electromagnetic field that creates an eddy current in the electrically conductive layer so as to heat the electrically conductive layer. | 03-03-2011 |
| 20110049301 | DE-ICER, A FIXTURE AND A METHOD OF ADJUSTING THE POSITION OF A DE-ICER - A de-icer including a bracket arranged on a structural member and a de-icer module mounted on the bracket. The de-icer module is adjustable arranged on the bracket such that a position of the de-icer module is adjustable in relation to the bracket. Also a fixture and a method of adjusting a position of a de-icer. | 03-03-2011 |
| 20110084171 | AIRCRAFT FUEL SYSTEM - An aircraft fuel system including a fuel line for carrying liquid fuel, and a microwave energy transmitter for energizing water carried in the fuel line. Also, a method of suppressing ice formation in an aircraft fuel system, the fuel system including a fuel line carrying liquid fuel, and a microwave energy transmitter, the method comprising transmitting microwaves along the fuel line to energize water carried with the fuel in the fuel line. | 04-14-2011 |
| 20110133035 | METHOD FOR MAKING DEICING SYSTEM ON A NACELLE PANEL - The invention relates to a method for making a deicing system on a panel ( | 06-09-2011 |
| 20110155855 | METHOD FOR MAKING AN ACOUSTIC PANEL FOR THE AIR INTAKE LIP OF A NACELLE - The invention relates to a method for making an acoustic panel ( | 06-30-2011 |
| 20110233340 | AIRCRAFT ICE PROTECTION SYSTEM - An ice protection system ( | 09-29-2011 |
| 20110290942 | ELECTRICAL POWER SUPPLY AND CONTROL DEVICE FOR EQUIPMENT OF A ROTOR, AND AN AIRCRAFT FITTED WITH SUCH A DEVICE - The present invention relates to an electrical power supply and control device ( | 12-01-2011 |
| 20120001026 | DE-ICING DEVICE, IN PARTICULAR FOR AN AIRCRAFT NACELLE - The invention relates to a de-icing device ( | 01-05-2012 |
| 20120280084 | ICE PROTECTION SYSTEM - An ice protection system ( | 11-08-2012 |
| 20120298803 | ELECTROTHERMAL HEATER - An electrothermal heater ( | 11-29-2012 |
| 20120298804 | ELECTROTHERMAL HEATER MAT - An electrothermal heater mat ( | 11-29-2012 |
| 20120318923 | ELECTROTHERMAL WING ICE PROTECTION SYSTEM - An electro-thermal wing ice protection solution controller for managing and controlling electrical power generated to heat and de-ice the wing of an aircraft. The system is comprised of a number of power control modules (PCMs) and at least one master control unit (MCU). These elements can be stacked together and mounted into rack systems in order to provide scalable organized power distribution for a wing de-icing and ice protection system. | 12-20-2012 |
| 20120318924 | AIR INTAKE OF AN AIRCRAFT NACELLE THAT INCORPORATES A REINFORCED LIP WITH A DEFROST SYSTEM BY JOULE-EFFECT - An air intake of an aircraft nacelle includes: | 12-20-2012 |
| 20130075531 | ELECTRIC CIRCUIT AND SENSOR FOR DETECTING ARCING AND A TRANSPARENCY HAVING THE CIRCUIT AND SENSOR - An electrical system responsive to overheating and/or electric arcing of an electrically conductive member, e.g. a heating member of an aircraft windshield, includes a first switch in a first current path, and a second switch in a second current path. The first current path is from an electrical power supply through the first switch, through an arc sensor to the heating member to the power supply. The second current path is from a temperature sensor monitoring the temperature of the heating member through the second switch to a temperature controller. When the temperature of the heating member is at or above a predetermined value, the temperature controller causes the first switch to open. When there is arcing, the second switch is moved to the open position. The temperature controller senses that the second switch is open and causes the first switch to open. | 03-28-2013 |
| 20130187006 | Electro-Expulsive De-Icing System for Aircraft and Other Applications - An apparatus for removing ice from an object (e.g., in-flight ice removal from the skin of an aircraft) includes an actuator assembly that forms an elongated electrically conductive loop. The actuator is mounted in a position enabling it to impact the object to be de-iced in response to movement of the loop that is produced by electric current pulses flowing in opposite directions in two mechanically independent loop subassemblies. The loop subassemblies include multiple electrically conductive elements interconnected at their ends using elongated flexible connectors in order to introduce a physically discontinuity that reduces any restriction of relative movement of the subassembly ends caused by the connectors, thereby achieving enhanced operation and less fatigue failure as compared to a rigid structure having encapsulated element | 07-25-2013 |
| 20130228653 | ELECTROTHERMAL AND ELECTRO EXPULSIVE HYBRID ICE PROTECTION SYSTEM FOR ENGINE INLET - A hybrid ice protection system (HIPS) including both an electro-expulsive de-icing system (EEDS) and electrothermal heaters to first break ice away from an outer surface of an engine nacelle inlet lip and then melt remaining residual ice from the outer surface of the inlet lip. The EEDS may have a plurality of EEDS actuators positioned to provide striking force to inner surfaces of both outer and inner walls of the inlet lip. The electrothermal heaters may be positioned to heat the inlet lip at areas between locations where the EEDS actuators provide striking force. The HIPS may also include a control system for actuating the EEDS actuators to strike the inner surface of the inlet lip when the inlet lip is at or below a predetermined temperature and then activating the electrothermal heaters to remove residual ice left on the inlet lip after actuation of the EEDS actuators. | 09-05-2013 |
| 20130228654 | ELECTRICAL GENERATOR FOR ROTATING STRUCTURE - An electrical generator assembly including a central rotatable shaft ( | 09-05-2013 |
| 20130284856 | AIRCRAFT ICE PROTECTION OPTIMIZATION BASED ON ICE-DETECTION INPUT - An aircraft ice protection system ( | 10-31-2013 |
| 20140014776 | SYSTEM CONTAINING AN ELECTRIC HEATING ELEMENT AND METHOD FOR INSTALLATION AND USE THEREOF - A system and method thereof is provided for electrically heating a component. The system includes at least one heating element adapted to be adhesively bonded to a surface on the component and means for controlling flow and duration of an electrical current to the heating element from a power supply. The controlling means comprises a first heating cycle for curing an adhesive to bond the heating element to the surface and has a second heating cycle for providing ice protection to the surface. | 01-16-2014 |
| 20140034783 | AIRCRAFT ELECTRICAL MAT WITH SOLDERLESS LEAD LINE CONNECTIONS - An electrical mat (20) is adapted for coupling to lead lines (30). The electrical mat (20) comprises a plurality of layers (41-48), a heater element (50), and a window (60) aligned with a connection face on a heater bus (52). A fastener part (71) extends through each window (60) so as to allow mechanical attachment of a terminal (32) and establish an electrical connection between the lead line (30) and a heater bus (52). | 02-06-2014 |
| 20140070054 | ANTI-ICING, DE-ICING, AND HEATING CONFIGURATION, INTEGRATION, AND POWER METHODS FOR AIRCRAFT, AERODYNAMIC, AND COMPLEX SURFACES - Anti-icing methods and aerodynamic structures having laminated resistive heaters for de-icing are described. Several of the inventive aspects utilize laminated resistive heaters comprising a carbon nanotube layer and/or capacitors to store and supply electricity. The invention also includes methods of making aerodynamic structures having de-icing or anti-icing functionality. | 03-13-2014 |
| 20140131520 | Thermal Insulation Barrier For An Aircraft De-Icing Heater - A structure for use with an electrothermal heating element is disclosed comprising a heating element contained in a mat and heater supports attached to one surface of the mat. The heating element is disposed between the skin and internal structure of an aircraft with the heater supports disposed toward the internal structure thereof. The heater supports maintain an insulating layer of air between the mat and the internal structure of the aircraft. | 05-15-2014 |
| 20140138490 | DEICER ZONES WITH HEATER-ENHANCED BORDERS - An ice protection system comprises deicing zones wherein each zone includes an envelope with an electrothermal heater layer Adjacent envelopes have edge regions flanking shared interzone borders. These edge regions can be configured to provide a higher heating power than the rest of the envelope so as to enhance deicing at the borders. | 05-22-2014 |
| 20140191083 | ICE PROTECTION SYSTEM - An ice protection system ( | 07-10-2014 |
| 20140191084 | ICE DETECTION AND MITIGATION DEVICE - A method for deicing an aerostructure includes driving a sensing current through a heater element coated to an aerostructure, the heater element having a resistance that is temperature dependent. A resistance of the heater element is monitored. It is determined whether there is icing at the heater element using the monitored resistance of the heater element. A melting current is driven through the heater element when it is determined that there is icing at the heater element. | 07-10-2014 |
| 20140319278 | RESISTIVE-INDUCTIVE DE-ICING OF AIRCRAFT FLIGHT CONTROL SURFACES - Embodiments of the disclosure include a de-icing system for an aircraft. The de-icing system includes a plurality of resistive-inductive heating elements inserted adjacent to a flight control surface and a controller configured to provide a supply current to each of the plurality of resistive-inductive heating elements. Each of the plurality of resistive-inductive heating elements produces an electromagnetic field normal to the flight control surfaces and resistive heat in response to the supply current. The electromagnetic field induces an eddy current in the flight control surface. | 10-30-2014 |
| 20140339366 | On-Blade Deice Heater Mat - A heater mat for a rotor blade includes a plurality of electrically conductive heater wires extending in a path along a span of the rotor blade and a plurality of yarn thread knitted to the plurality of heater wires, each of the yarn threads looping around at least one of the plurality of heater wires. A warp thread is positioned between adjacent heater wires and knitted to adjacent pairs of the yarn threads without looping around the plurality of heater wires, to maintain spacing between adjacent heater wires of the plurality of heater wires. An electrical current flowed through the plurality of heater wires inhibits ice accumulation on the rotor blade assembly. | 11-20-2014 |
| 20140367522 | ELECTRO-THERMAL ICE PROTECTION SYSTEM AND METHOD WITH SERIAL LOAD LEVELING - An electro-thermal ice protection system includes a controller for managing and controlling electrical power generated to heat and de-ice surfaces, such as aircraft wings. The system is comprised of a number of power control modules (PCMs) and at least one master control unit (MCU). These elements can be stacked together and mounted into rack systems in order to provide scalable organized power distribution for a de-icing and ice protection system. The electro-thermal system can be used with a load leveling system and method capable of controlling switches such that it appears to a generator that the load is constant. Switches can be scheduled such that, ideally, the power load seen by the power source has emissions of no more than one PWM load superpositioned with zero or more constant, non-modulated loads. | 12-18-2014 |
| 20150083863 | DEICING OF A SURFACE OF STRUCTURES IN GENERAL SUCH AS WIND TURBINE BLADES, AIRCRAFT WINGS USING INDUCTION OR RADIATION - A method is provided which allows the facile deicing of a surface of a structure in general. Electromagnetic induction or IR/Microwave radiation is used to heat up a layer or a coating on said surface of the structure in general whereby said layer preferably contains conductive particles such as carbon nano particles, such as graphite, carbon nano tubes, carbon nano cones, metal in powder form, metalized glass beads, carbon fibers, chopped or as woven structure, etc all collectively named Carbon Nano Tubes (CNTs) or cones or metallic particles at concentrations above 0.01% by weight. Heat conductors such as boron nitride may be used to improve the heat transfer to the surface. Constructions are disclosed which shield the microwave emitters from lightning receiving elements, and which protect the complete structure during lightning events. Radiation can be supplied both from the inside of the structure as well as from the outside. | 03-26-2015 |
| 20150129720 | Device and Method for Deicing and/or Preventing Ice Formation and Profile Element and Aircraft Having Such a Device - In order to maintain a surface region of an aircraft free of ice in a particularly energy-efficient manner, a device for deicing and/or for preventing ice formation is provided on an aircraft. The device includes a heat emitting device for emitting heat at a surface region of the aircraft, the heat emitting device is designed to dissipate heat along a line in order to produce a predetermined breaking point or a predetermined breaking line or parting line in ice accumulating on the surface region. | 05-14-2015 |
| 20150314879 | DE-ICING ARRANGEMENT AND METHOD FOR DE-ICING A STRUCTURAL ELEMENT - A de-icing arrangement and method for de-icing a structural element. The arrangement includes at least one electromagnetic actuator, a capacitive storage bank, a control unit arranged to provide an excitation pulse to the at least one electromagnetic actuator, and a charging circuit arranged to charge the capacitive storage bank. The at least one electromagnetic actuator is arranged to expand in at least one direction when fed with the excitation pulse. The at least one electromagnetic actuator is placed in relation to the structural element so as to apply a mechanical force caused by the expansion on the structural element. The capacitive storage bank includes a plurality of selectable capacitors of different size. The control unit is arranged to select at least one capacitor for charging having a size such that current discharge of the capacitive storage bank into the at least one electromagnetic actuator generates a desired distribution between heat and mechanical power. | 11-05-2015 |
| 20150329211 | AIRCRAFT ICE PROTECTION SYSTEM AND METHOD - A system and method for ice protection of a component, wherein the system is adapted to be adhesively bonded to a surface of the component. The system includes a heating element layer, at least one thermally conductive adhesive layer that adhesively bonds a first side of the heating element layer to the component, an insulation layer, at least one thermally insulating adhesive layer that adhesively bonds a second side of the heating element to the insulation layer, an electrical bus bar adapted to provide a connection between a power supply and the heating element layer, and at least one temperature sensor. | 11-19-2015 |
| 20160114895 | ANTI-ICING / DE-ICING SYSTEM FOR AIRCRAFT DOOR AND AIRCRAFT DOOR EQUIPPED WITH SUCH A SYSTEM - The invention aims to make aircraft doors easier to open by preventing ice formation or, at the very least, favoring rapid breaking of the ice on the door edges connected to the skin of the fuselage. To that end, it is provided to supply energy along the door when specific conditions are met. According to one embodiment, an anti-icing/de-icing system for an aircraft door ( | 04-28-2016 |
| 20160159485 | AIRCRAFT WING ELEMENT - An aircraft wing element comprises two temperature sensors that are situated on each side of an electrothermal mat, between a structure portion and a shield of said wing element. A shield temperature can be measured more accurately, and a thermal energy flow that is transferred to the shield can be evaluated. | 06-09-2016 |
| 20160185458 | Electro-Expulsive De-Icing System for Aircraft and Other Applications - An apparatus for removing ice from an object (e.g., in-flight ice removal from the skin of an aircraft) includes an actuator assembly that forms an elongated electrically conductive loop. The actuator is mounted in a position enabling it to impact the object to be de-iced in response to movement of the loop that is produced by electric current pulses flowing in opposite directions in two mechanically independent loop subassemblies. The loop subassemblies include multiple electrically conductive elements interconnected at their ends using elongated flexible connectors in order to introduce a physically discontinuity that reduces any restriction of relative movement of the subassembly ends caused by the connectors, thereby achieving enhanced operation and less fatigue failure as compared to a rigid structure having encapsulated element | 06-30-2016 |
| 20090072091 | ENERGY-EFFICIENT ELECTRO-THERMAL AND ELECTRO-MECHANICAL ICE-PROTECTION METHOD - A region of an airfoil to be protected from accreted ice is heated to reduce the strength of the bond between the ice and the airfoil, and is mechanically deformed to shed the accreted ice after the bond has been sufficiently weakened. Heating ceases before substantial water runback is generated. The mechanical deformation and the cessation of heating occur approximately simultaneously. | 03-19-2009 |
| 20120074262 | DE-ICING SYSTEM FOR A FIXED OR ROTARY AIRCRAFT WING - A de-icing system for a fixed or rotary aircraft wing, the system including means for generating ultrasound that is transmitted at least locally to an outside surface of the wing, which means comprise a base structure ( | 03-29-2012 |
| 20120091276 | ENERGY-EFFICIENT ELECTRO-THERMAL AND ELECTRO-MECHANICAL ICE-PROTECTION METHOD - A region of an airfoil to be protected from accreted ice is heated to reduce the strength of the bond between the ice and the airfoil, and is mechanically deformed to shed the accreted ice after the bond has been sufficiently weakened. Heating ceases before substantial water runback is generated. The mechanical deformation and the cessation of heating occur approximately simultaneously. | 04-19-2012 |
| 20130277501 | DE-ICING SYSTEMS AND METHODS - An de-icing system comprising a shield that is configured to deform in a pre-determined way that de-bonds accreted ice. In some embodiments, the shield has a variable (non-uniform) stiffness across its width and/or length such that it undergoes a twist-like or other suitable deformation when subjected to a force. In some embodiments, the system includes a plurality of electro-mechanical actuators configured to generate the force applied to the shield. | 10-24-2013 |
| 20130299637 | ICE PROTECTION FOR AIRCRAFT USING ELECTROACTIVE POLYMER SURFACES - An electro-active polymer (EAP) surface having a plurality of actuators adapted to prevent the formation of ice on an external surface, such as a leading edge of an aircraft. The EAP surface may also be adapted to remove ice formed on the external surface. The actuators of the EAP surface may be oscillated to prevent and/or remove ice from the surface of an aircraft. A signal generator may be used to individually oscillate the actuators in a first mode to prevent the formation of ice and a second mode to break up ice formed on the EAP surface. The signal generator may oscillate all of the actuators at the same frequency, may individually oscillate the actuators to form a pattern on the EAP surface, or may individually oscillate the actuators to form a wave along the EAP surface. The actuators may be dimple actuators, wrinkle actuators, and/or bump actuators. | 11-14-2013 |
| 20140191082 | METHOD AND ARRANGEMENT FOR DE-ICING A STRUCTURAL ELEMENT - The present invention relates to a de-icing arrangement for de-icing a structural element { | 07-10-2014 |
| 20140252172 | SINGLE SURFACE ELECTRO-MECHANICAL ACTUATOR ASSEMBLY - The current invention is directed to a self-contained electro-expulsive actuator assembly capable of being attached and operating external to an object, and methods of providing an electro-expulsive force external to an object. During operation the deformation or flexing of the electro-expulsive actuator causes deformation of an integral outer skin which is overlaid over the outer surface of the underlying structure, thereby causing unwanted build-up of residues on the outer skin of the actuator assembly to be expelled. | 09-11-2014 |
| 20170233085 | Deicing Apparatuses | 08-17-2017 |
| 20090020647 | SYSTEM FOR DEICING AN AIR INLET COWL FOR A TURBINE ENGINE - According to the invention, a scaled articulation device ( | 01-22-2009 |
| 20090078828 | ANTI-ICE VALVE COMPONENTS AND METHODS OF COUPLING A VALVE ASSEMBLY TO A SERVO CONTROLLER OF ANTI-ICE VALVE COMPONENTS - Anti-ice valve components are provided that include a servo housing, a valve body, and a transfer tube. The servo housing includes a surface having a cavity formed therein. The valve body is spaced apart from the servo housing and includes a surface having a cavity formed therein. The transfer tube has a first end, a second end, and a length, where the first end is disposed in the servo housing cavity, the second end is disposed in the valve body cavity, and the length extends between the first end and the second end and has a portion forming a bend of at least 180 degrees. | 03-26-2009 |
| 20090090814 | METHOD OF DE-ICING THE LEADING EDGE OF AN AERODYNAMIC SURFACE AND AIRCRAFT IMPLEMENTING SUCH A METHOD - According to the invention, on at least one of the faces (1E, 1I) of said leading edge (1), forward of the partition (3), an action is exerted on the fluid flow (EF) so as to cause the latter to switch from the laminar state (EFL) to the turbulent state (EFT) in order to increase the thermal exchanges and minimize the thermal stresses on siad leading edge. | 04-09-2009 |
| 20090108134 | ICING PROTECTION SYSTEM AND METHOD FOR ENHANCING HEAT TRANSFER - An icing protection system and method for enhancing heat transfer includes a substrate having an inner wall, an outer wall and a thickness separating the inner wall and the outer wall. A metallic layer deposited on the inner wall of the substrate by an electric arc thermal spray deposition process using at least one metallic wire has a thickness between about 0.203 mm (0.008 inches) and about 0.432 mm (0.017 inches), a surface roughness greater than about 12.7 microns (500 micro-inches) Ra, and a heat transfer augmentation of at least about 1.1. The metallic layer is formed on the inner wall from an M-Cr—Al alloy where M is selected from Fe, Co and Ni. The metallic layer defines a plurality of turbulators that act as micro-fins to enhance heat transfer from a heated gas in flow communication with the metallic layer through the substrate to prevent the formation of ice on the outer wall. | 04-30-2009 |
| 20090152401 | NACELLE INLET THERMAL ANTI-ICING SPRAY DUCT SUPPORT SYSTEM - An anti-icing system for an aircraft engine nacelle comprises a generally ring-shaped hollow spray tube for directing hot gasses toward a portion of the nacelle; a plurality of fasteners for attaching the spray tube to a support structure of the aircraft engine; and a supply duct for delivering the hot gasses from the aircraft engine to the spray tube. The spray tube includes two closed ends which define a thermal expansion gap therebetween to accommodate thermal expansions and contractions caused by the hot gasses. Each of the fasteners comprises a support bracket for attachment to the support structure of the aircraft and a guide assembly for supporting the spray tube to the support bracket. The guide assembly includes a generally ring-shaped block for encircling the spray tube, a bushing positioned within the block for contact with a bearing sleeve of the spray tube, and a pair of bushing retainers positioned on opposite sides of the block for retaining the bushing within the block. The bushings permit the spray tube to slip relative to the fasteners to further accommodate thermal expansions and contractions. | 06-18-2009 |
| 20100001138 | DUAL VALVE APPARATUS FOR AIRCRAFT ENGINE ICE PROTECTION AND RELATED METHODS - A thermal anti-ice system in an aircraft. A controlled valve receives air from a compressor bleed port of an engine of the aircraft. A self-regulating valve is fluidly connected between the controlled valve and an inlet of the engine. A first pressure sensor senses pressure between the valves. A second pressure sensor senses pressure between the self-regulating valve and the inlet. The system can be used to de-ice aircraft inlet lip skins made of composite materials that have comparatively lower design temperatures than other comparable materials. | 01-07-2010 |
| 20100108814 | ANTI-ICING APPARATUS FOR HONEYCOMB STRUCTURES - An apparatus comprises a structure having a leading edge, a skin covering the structure, a tip, and a channel. The tip is located at the leading edge, wherein the tip has a number of openings. The channel extends through the structure to the tip, wherein the channel is in communication with the number of openings in the tip. | 05-06-2010 |
| 20100163677 | METHOD AND APPARATUS FOR AIRCRAFT ANTI-ICING - An aircraft anti-icing system includes a source of high temperature gas, a housing, at least one conduit to carry the high temperature gas from the source to the housing, the at least one conduit coupled to the housing and the source, at least one nozzle coupled to the at least one conduit, at least one nozzle configured to impart a rotational motion to the high temperature gas before exhausting the high temperature gas into the housing, and a port for exhausting air from the housing. | 07-01-2010 |
| 20100163678 | THERMAL ANTI-ICING SYSTEM - An air intake duct of an aircraft engine or other component is provided with a thermal anti-icing system. The front of the air intake duct comprises a toroidal outer skin ( | 07-01-2010 |
| 20100176243 | Anti-Icing Piccolo Tube Standoff - A standoff structure for an anti-icing piccolo tube wherein a flexible structure is formed from support ribs, a support bar and a diverter bar for supporting the piccolo tube within the slat or other aircraft leading edge, and for diverting hot gas from the piccolo tube across the inner surface of the slat or other aircraft leading edge. | 07-15-2010 |
| 20100200699 | SYSTEM FOR DEFROSTING THE LEADING EDGE SHEATH OF AN AIR INLET HOOD FOR A TURBOENGINE - The system for defrosting the leading edge sheath of an air intake hood for a turboengine comprises a hot pressure air supply duct ( | 08-12-2010 |
| 20100252685 | AIRCRAFT NACELLE INCLUDING AN OPTIMISED ICE TREATMENT SYSTEM - An aircraft nacelle includes a pipe, a peripheral wall, a lip connecting the pipe and peripheral wall and delimiting an air intake. A frost treatment system treats a zone extending along a longitudinal section of a point A at the peripheral wall at a point B at the pipe and includes a front frame delimiting with the lip a pipe circulating deicing hot air. An acoustic pipe coating includes a reflective layer, at least one alveolar structure, and at least one acoustically resistive structure. The front frame includes a junction zone with the lip and/or the pipe offset toward the nacelle front relative to B. Pipes inside the lip and the pipe convey hot air from the pipe to circularly arranged discharges corresponding to B. The pipes extend beyond the junction between the front frame and the lip and/or the pipe and are delimited by at least one isolating partition. | 10-07-2010 |
| 20110011981 | AIR INTAKE STRUCTURE FOR AN AIRCRAFT NACELLE - The invention relates to an air intake structure capable of being mounted upstream of a central structure of a nacelle for an aircraft engine, the said air intake structure comprising: —an external wall incorporating a lip, —an upstream partition ( | 01-20-2011 |
| 20110068230 | DETECTING ICE PARTICLES - Systems and methods for detecting ice particle accumulation is disclosed herein. In one exemplary implementation, a method for detecting ice is described in which a parameter within an interior volume of a heated conduit is measured. The method also includes detecting the presence of an accumulation of ice particles based on the parameter measured within the interior volume of the heated conduit. | 03-24-2011 |
| 20110121136 | AIRCRAFT DE-ICING DEVICE AND ENGINE NACELLE OF AN AIRCRAFT GAS TURBINE WITH DE-ICING DEVICE - An aircraft de-icing device and an engine nacelle of an aircraft gas turbine is provided with a de-icing device, with the engine nacelle | 05-26-2011 |
| 20110168843 | TURBOMACHINE NACELLE AND ANTI-ICING SYSTEM AND METHOD THEREFOR - An anti-icing system for a nacelle of an aircraft engine. The nacelle has an inlet lip that defines a leading edge of the nacelle, and further has an annular-shaped cavity adjacent and delimited in part by an interior surface of the inlet lip. An anti-icing system is located within the cavity and includes a manifold with a cross-sectional shape that conforms to the interior surface of the inlet lip. A wall of the manifold faces the interior surface of the inlet lip, and air is conducted to the manifold to cause heating of the inlet lip via the manifold wall. | 07-14-2011 |
| 20110226903 | DE-ICING DEVICE COMPRISING MEANS FOR DETECTION OF A LEAKAGE IN A HOT AIR SUPPLY SYSTEM - A device for defrosting a leading edge of an aircraft, includes at least one opening ( | 09-22-2011 |
| 20120085867 | HEATING SYSTEM - A heating system for heating at least a portion of a leading edge ( | 04-12-2012 |
| 20120248249 | AIR INLET OF AN AIRCRAFT NACELLE INCLUDING OPTIMIZED FROST TREATMENT - An air inlet of an aircraft nacelle includes a pipe, extending over the circumference of the air inlet and defined in the back by a front frame, and an element for the localized injection of hot air into the pipe, thus ensuring the flow of hot air into the pipe in one direction along the circumference of the nacelle. The inlet includes at least one vortex generator ( | 10-04-2012 |
| 20120248250 | AIRCRAFT NACELLE AIR INTAKE INCORPORATING OPTIMIZED ICE-TREATMENT HOT AIR INJECTION MEANS - An aircraft nacelle air intake includes a duct extending around the circumference of the air intake and elements ( | 10-04-2012 |
| 20120298802 | De-icing device of an aircraft gas-turbine engine - The present invention relates to a de-icing device of an aircraft gas-turbine engine with an engine cowling enclosing at least one inflow region, with the engine cowling having a double-walled design and including at least one annular tube element extending in the circumferential direction and being provided with outlet openings for passing hot air to an inflow region, in order to de-ice it, with the tube element in the circumferential direction including multiple individual tube segments which can be attached relative to one another. | 11-29-2012 |
| 20120318922 | DEICING DEVICE FOR WING LEADING EDGE OF AIRCRAFT AND AIRCRAFT MAIN WING - A deicing device for a wing leading edge of an aircraft and an aircraft main wing are constituted by providing a hot air passage ( | 12-20-2012 |
| 20140263837 | NACELLE INLET THERMAL ANTI-ICE SPRAY DUCT - An anti-icing system for a nacelle inlet of an aircraft engine includes a spray tube for directing hot gasses toward a portion of the nacelle inlet. The spray tube includes a plurality of sections arranged such that the ends of adjacent sections are separated by a space thereby defining a thermal expansion gap between the sections. A plurality of expansion joints interconnect adjacent ends of the spray tube sections and enclose the expansion gaps. The joints allow the spray tube to expand and contract without adversely affecting the performance or structure of the spray tube. Annular sealing elements positioned in opposed axial margins of the expansion joints provide an air-tight or nearly air-tight seal between the expansion joints and the spray tube sections. | 09-18-2014 |
| 20150034767 | Method For Regulating The De-Icing Of A Leading Edge Of An Aircraft And Device For Its Implementation - A method of regulating the de-icing of a leading edge of an aircraft includes regulating the flow of air used for de-icing by at least a first regulator valve in accordance with two regulation levels, a first regulation level corresponding to the regulated position of the first regulator valve and a second regulation level corresponding to the fully open position of the first regulator valve. A de-icing device enables implementation of the regulation method. | 02-05-2015 |
| 20150291284 | DE-ICING SYSTEM WITH THERMAL MANAGEMENT - An aircraft component assembly has a structural body and a thermal management de-icing system for minimizing or preventing ice build-up on leading edges of the body. The system includes a supply line for flowing heated fluid to the leading edges and a cooling device that interposes the supply line to prevent overheating of the leading edges thus protecting bodies that may be made of composite materials that are more susceptible to heat. | 10-15-2015 |
| 20160376010 | SYSTEMS AND METHODS FOR PREVENTING ICE ACCUMULATION - A device configured to prevent ice accumulation includes at least one wall defining a leading edge and a pneumatic passage configured to receive pressurized fluid. The device also includes at least one ejection port formed in at least one of the leading edge and the at least one wall, the at least one ejection portion fluidly coupled to the pneumatic passage to receive the pressurized fluid therefrom, the at least one ejection port configured to form fluid jets to divert liquid water droplets away from the leading edge of the device. | 12-29-2016 |
| 20170233084 | ANTI-ICING SYSTEM AND AIRCRAFT | 08-17-2017 |
| 20080258010 | System for Deicing and/or Defogging an Aircraft Surface, Method for Controlling Same, and Aircraft Equipped with Same - The invention concerns a system for deicing and/or defogging an aircraft surface ( | 10-23-2008 |
| 20090189020 | Aerodynamic Profile for Aircraft and Wind Power Stations and Method of Measuring the Thickness of Ice on an Aerodynamic Profile - An aerodynamically shaped profile member for aircraft and wind power stations includes, for example, phased-array ultrasonic generator arrangement is arranged therein. During operation of the profile member, the ultrasonic generator emits ultrasonic waves in a targeted manner in multiple directions to determine a profile of the thickness of an ice layer on the surface of the aerodynamic profile. The structure may be, for example, a composite fiber material arranged around a foam core, with the ultrasonic generator arrangement being laminated into the composite fiber material. For measurement of the ice thickness, ultrasonic waves are transmitted in a targeted manner to different positions of the surface of the aerodynamic profile, and the ultrasonic waves reflected on the interfaces of the ice layer are detected. At least one region of the surface is scanned by means of the targeted ultrasonic waves, to determine an ice thickness profile. | 07-30-2009 |
| 20090289147 | METHOD OF COLLECTING INFORMATION RELATING TO A MOVABLE AIRFOIL SURFACE OF AN AIRCRAFT - The invention relates to a method of collecting information relating to a movable airfoil surface ( | 11-26-2009 |
| 20090321576 | Method and Apparatus for Detecting Conditons Conducive to Ice Formation - A method for detecting ambient conditions conducive to ice formation. The method includes the steps of measuring at least one parameter selected from a group of parameters consisting of a static pressure, a total pressure, a total temperature, a dew point temperature, and a liquid water content, and determining whether ambient conditions are conducive to ice formation based on the measured parameter. | 12-31-2009 |
| 20100012785 | WING DEBRIS DETECTOR - An apparatus and method for wind debris detection comprises a spring loaded probe that is deployed on the leading edge of an aircraft wing into an area where debris formation might impact wing aerodynamic performance. The probe travel is sensed by sensors (angular displacement, linear displacement, proximity, torque, load cell on spring, and the like), and if the sensor(s) detect that probe travel is limited then presence of debris is indicated. | 01-21-2010 |
| 20100116940 | METHOD AND DEVICE FOR DETECTING RIME AND/OR RIME CONDITIONS ON A FLYING AIRCRAFT - According to the invention, the method comprises exposing a surface ( | 05-13-2010 |
| 20100140410 | AIRCRAFT ICING INDICATOR - The icing indicator for an aircraft, of the type that can be directly and visually read by a pilot, includes means of installation at the surface of the fuselage and projecting therefrom, in combination with an already-existing device positioned above a through-hole in the fuselage, the device being modified to allow a power cable that powers the icing indicator to pass through the fuselage within its fastening. The icing indicator is preferably combined with a rain repellent spray device or on the spindle about which the windscreen wiper rotates. | 06-10-2010 |
| 20100206991 | DETECTING ICE PARTICLES - Systems and methods for detecting ice particle accumulation is disclosed herein. In one exemplary implementation, a method for detecting ice is described in which a parameter within an interior volume of a heated conduit is measured. The method also includes detecting the presence of an accumulation of ice particles based on the parameter measured within the interior volume of the heated conduit. | 08-19-2010 |
| 20100282911 | DETECTION SYSTEM AND METHOD FOR ICE AND OTHER DEBRIS - A system and method for detecting debris on the surface of a member are provided, for example, for detecting ice or other debris on an outer surface of an aircraft. The detection system includes a heating device in thermal communication with the member, an infrared sensing device configured to sense infrared radiation emitted from the member, and a monitoring device in communication with the sensing device. The monitoring device is configured to monitor a change in emission from the member and thereby detect the presence of debris on the surface of the member. | 11-11-2010 |
| 20110036948 | AUTOMATIC RECYCLING ICE DETECTOR - An automatic recycling ice detector includes a sensor for sensing the formation of ice on an aircraft surface and a heater for melting the detected ice. The detector also includes a timing circuit for indicating the time to melt any detected ice and automatically recycling the detector when the ice is melted. A computer including a look up table or the like are provided for measuring and indicating the thickness of the accumulated ice based on a relationship between melting time and thickness. | 02-17-2011 |
| 20110036949 | STRUCTURAL MEMEBER OF AN AIRCRAFT HAVING A HOLLOW PART AND INDICATOR OF ICE FORMATION IN SUCH A HOLLOW PART - A structural element of an aircraft includes a hollow part. An indicator provides a visual indication, for example by moving, if ice forms in a given region of the hollow part. | 02-17-2011 |
| 20110147526 | Aircraft - An aircraft having a fuselage and a detecting device for detecting the presence of ice caused by solidification of supercooled liquid droplets having a characteristic dimension above a threshold value. The detecting device has a preferential first portion for accumulating the droplets, and the preferential first portion is located so as to be visible from inside the fuselage. | 06-23-2011 |
| 20110210207 | MECHANICAL VIBRATION DEICING SYSTEM - An aircraft deicing system including at least one motor operative to drive at least one eccentric mass in rotational motion and at least one displacer coupled to at least one location on at least one aircraft surface and coupled to the at least one eccentric mass such that forces produced by the rotational motion of the eccentric mass are applied to the at least one displacer, causing the at least one displacer to displace the at least one aircraft surface in a plurality of directions at each of the at least one location, thereby causing disengagement of ice from the at least one aircraft surface. | 09-01-2011 |
| 20110226904 | VIRTUAL ICE ACCRETION METER DISPLAY - A flight display for an aircraft includes a virtual ice accretion meter having a liquid water content portion and an ice thickness portion. A method for determining ice accretion includes integrating over a time period a constant K multiplied by a liquid water content (LWC) and true airspeed (TAS). | 09-22-2011 |
| 20110253841 | METHOD AND SYSTEM FOR CHECKING THE FORMATION OF ICE ON AN AIRCRAFT IN FLIGHT - The invention relates to a method for checking the formation of ice on an aircraft in flight, characterized in that the method comprises:
| 10-20-2011 |
| 20120085868 | AIRCRAFT ICING DETECTOR - A method for aircraft surface contamination detection and measurement includes: mounting a laser probe on an airfoil; positioning the laser probe to emit laser energy at multiple pre-determined surface points along the leading edge of the airfoil; and using a processor device for activating the laser probe and obtaining measurement data for generating a surface contour of the shape and accurate measurement of the depth of airfoil icing in the surface target area. The icing data is presented to the pilot in a display that alerts him to the icing and accurately shows the depth and shape of the airfoil icing. | 04-12-2012 |
| 20120193477 | DEVICE AND METHOD FOR DETECTING ICE DEPOSITED ON AN AIRCRAFT STRUCTURE - The invention relates to an ice detection device and method for detecting ice on an aircraft in flight. The device includes a transmitter which emits a first and a second radiation in the direction of a reflective surface, these two radiations respectively being within a first wavelength band and a second wavelength band; and a receiver which captures the reflected radiations. The transmitter and said receiver are fixed on an external surface of the aircraft. Then a computer determines the presence or absence of ice as a function of the intensity of the captured radiations. The reflective surface is located outside the boundary layer of the aircraft during flight and includes a heating/cooling device. | 08-02-2012 |
| 20120256053 | Rotor Blade De-Icing System - An aircraft includes a heat absorbent material carried by an airfoil susceptible to ice buildup and a transmitter spaced apart from the heat absorbent material. A method includes the process of transmitting the heat energy from the transmitter to the heat absorbent material that in turn warms the airfoil to break apart ice buildup. | 10-11-2012 |
| 20130105631 | ICING DETECTOR PROBE AND ICING DETECTOR WITH THE SAME | 05-02-2013 |
| 20130175396 | Supercooled Large Drop Icing Condition Detection System - An ice detection system comprising a first group of sensors and a second group of sensors. The first group of sensors is located in a first group of locations on an aircraft. The first group of sensors in the first group of locations is configured to detect a first type of icing condition for the aircraft. The second group of sensors is located in a second group of locations on the aircraft. The second group of sensors in the second group of locations is configured to detect a second type of icing condition for the aircraft. | 07-11-2013 |
| 20130175397 | Supercooled Large Drop Icing Condition Detection System - A method and apparatus for an ice detection system. The ice detection system comprises a first sensor located on a leading edge of a vertical stabilizer on an aircraft, a second sensor located on a first side of the vertical stabilizer, and a third sensor located on a second side of the vertical stabilizer. The first sensor is configured to detect a first type of icing condition for the aircraft. The second sensor is configured to detect a second type of icing condition for the aircraft. The third sensor is configured to detect the second type of icing condition for the aircraft. | 07-11-2013 |
| 20130240672 | Laser-Based Supercooled Large Drop Icing Condition Detection System - A method and apparatus for detecting icing conditions. An icing condition detection system comprises a number of sensors and an icing condition detector. The number of sensors is located in a number of locations on an aircraft. A sensor in the number of sensors is configured to emit electromagnetic radiation into drops of water in an environment around the aircraft. The sensor in the number of sensors is configured to detect responses to the electromagnetic radiation. The sensor in the number of sensors is configured to generate data from the responses. The icing condition detector is configured to monitor for the data from the number of sensors. The icing condition detector is further configured to detect a presence of a number of types of icing conditions for the aircraft using the data from the number of sensors. | 09-19-2013 |
| 20130299638 | MECHANICAL VIBRATION DEICING SYSTEM - An aircraft deicing system including at least one motor operative to drive at least one eccentric mass in rotational motion and at least one displacer coupled to at least one location on at least one aircraft surface and coupled to the at least one eccentric mass such that forces produced by the rotational motion of the eccentric mass are applied to the at least one displacer, causing the at least one displacer to displace the at least one aircraft surface in a plurality of directions at each of the at least one location, thereby causing disengagement of ice from the at least one aircraft surface. | 11-14-2013 |
| 20130341464 | ICE DETECTION SYSTEM AND METHOD - An ice detection system, in particular a method, apparatus and controller for detecting icing conditions and the presence of ice formed on a structure. Also, a method, apparatus and controller to detect the prevailing environmental conditions to determine whether or not ice may form on a structure. Two heaters of an ice protection system (experiencing substantially the same environmental conditions) are driven to different temperatures (the first greater than or equal to 0° C., and the second less than 0° C.). A difference in the powers required to drive the two heaters indicates the prevailing environmental conditions. In another embodiment, a heater of an ice protection system is driven and the rate of change of surface temperature is measured over several periods. A substantial deviation from a rate of change of surface temperature, which indicates the presence of ice on the surface of the structure, is detected. | 12-26-2013 |
| 20140166813 | DETECTION OF ICING CONDITIONS ON AN AIRCRAFT - A controller for determining when icing conditions are present on an outside surface of an aircraft may include a first input receiving a moisture condition on a windshield of the aircraft, a second input receiving an outside temperature, and an output that provides an icing condition determined as a function of the first input and the second input. The moisture condition can be provided by a moisture sensor positioned on an interior surface of the windshield and the windshield may include a heating system. | 06-19-2014 |
| 20140263838 | METHODS AND SYSTEM FOR DEICING A SURFACE - A method of an embodiment includes receiving data from a sensor that is configured to supply data related to an ice layer thickness on a skin surface, calculating the ice layer thickness, comparing the ice layer thickness to a threshold thickness, vibrating the skin surface using at least one mechanical element for a sufficient duration, sufficient frequency, and sufficient displacement to result in removal of a first portion of the ice layer thereby resulting in at least a partially deiced skin surface, and heating the partially deiced skin surface using at least one heating element. The method of an embodiment further includes heating from a leading edge of the skin surface to a trailing edge of the skin surface and heating the surface to result in a sufficient temperature increase in the skin surface for removal of a second portion of the ice layer. | 09-18-2014 |
| 20150115105 | AIRCRAFT ICING DETECTOR - A system capable of detecting the hazardous accumulation of ice on the surfaces, engines, instruments and air intakes of aircrafts or other objects of interest. The system consists of an electromagnetic microwave resonator capable of detecting the formation of ice directly where it could cause problems. The sensor could be mounted around the air intake of pitot tubes, static ports, engines intake, engines core, and can be embedded in the aircraft skin. The system uses algorithms based on the variations of the complex dielectric permittivity of water substance with frequency to distinguish the various types of ice from each other and from water. | 04-30-2015 |
| 20090039200 | EROSION RESISTANT FILMS FOR USE ON HEATED AERODYNAMIC SURFACES - The present disclosure provides a tape comprising: a) a single layer comprising a crosslinked polymer, selected from the group consisting of crosslinked polyurethane, crosslinked polyurea, and crosslinked mixed polyurethane/polyurea polymer, and b) an adhesive layer. In another embodiment, the disclosure provides an erosion resistant construction comprising, first, an element of an aircraft comprising: an aircraft skin segment having an external surface, and a deicing mechanism associated with said aircraft skin segment capable of heating said external surface to temperatures in excess of 65° C.; and, second, a tape comprising: at least one layer comprising a crosslinked elastomeric polymer, which may be a crosslinked polymer selected from the group consisting of crosslinked polyurethane, crosslinked polyurea, and crosslinked mixed polyurethane/polyurea polymer, and an adhesive layer; wherein the tape is bonded to the external surface of the aircraft skin segment by the adhesive layer. In another embodiment, the tape comprises at least one layer comprising a semi-interpenetrating polymer network of a crosslinked acrylate and an uncrosslinked polymer selected from the group consisting of polyurethane, polyurea, and mixed polyurethane/polyurea polymer. | 02-12-2009 |
| 20090159751 | DEVICES AND METHODS FOR PREVENTING ICE BUILD-UP AND ARTICLES OF MANUFACTURE THAT ARE RESISTANT TO ICE BUILD-UP - Embodiments of the present invention feature heat exchange surfaces having a layer or coating having a lower surface tension than water, to repel water and prevent the formation of condensate on said surface. | 06-25-2009 |
| 20090272850 | ICE SHED REDUCTION FOR LEADING EDGE STRUCTURES - A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface. | 11-05-2009 |
| 20120091277 | EROSION RESISTANT FILMS FOR USE ON HEATED AERODYNAMIC SURFACES - The present disclosure provides a tape comprising: a) a single layer comprising a crosslinked polymer, selected from the group consisting of crosslinked polyurethane, crosslinked polyurea, and crosslinked mixed polyurethane/polyurea polymer, and b) an adhesive layer. In another embodiment, the tape comprises at least one layer comprising a semi-interpenetrating polymer network of a crosslinked acrylate and an uncrosslinked polymer selected from the group consisting of polyurethane, polyurea, and mixed polyurethane/polyurea polymer. | 04-19-2012 |
| 20120312924 | ICE SHED REDUCTION FOR LEADING EDGE STRUCTURES - A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface. | 12-13-2012 |
| 20130056585 | AIRCRAFT TAIL SURFACE WITH A LEADING EDGE SECTION OF UNDULATED SHAPE - An aircraft tail surface ( | 03-07-2013 |
| 20160023771 | AIRCRAFT ELEMENT REQUIRING AN ANTI-FROST TREATMENT - The present disclosure provides an aircraft element including a leading edge section and a trailing edge section, and the leading edge section includes an anti-frost treatment device. This aircraft element is remarkable in that the trailing edge section includes a superhydrophobic surface. | 01-28-2016 |
