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Document Title |
JP6719992B2 |
A device (24; 124) configured to prevent ice accumulation includes at least one wall (40, 42) defining a leading edge (44) and a pneumatic passage (46) configured to receive pressurized fluid. The device also includes at least one ejecti...
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JP2020100393A |
To provide an improved ice protection assembly, an improved method of preparing an adhesive, and an improved method of removing an adhesive from a component.A method of making an adhesive for an ice protection assembly includes mixing fe...
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JP2020093783A |
To provide an ice protection assembly having an adhesive for facilitating rearrangement of a deicer.A method of making an adhesive for an ice protection assembly includes transferring Z-CNTs from a substrate carrier into the adhesive. De...
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JP2020095960A |
To provide multilayer structures comprising carbon nanotube heaters.There is disclosed a multilayer structure including: a first heater layer including a CNT heater, the CNT heater comprising a composite of carbon nanotubes and silicone;...
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JP2020082735A |
To provide passive anti-icing and/or deicing systems.A passive anti-icing and/or deicing device includes an icephobic outer layer configured to prevent ice from forming and/or building up on the outer layer by preventing ice from adherin...
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JP2020079074A |
To provide an intelligent window heat control system.A system for monitoring performance of an aircraft windshield includes a sensor, which comprises a sensory contact and an evaluation unit. The sensory contact is in physical contact wi...
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JP2020077616A |
To provide an additionally manufactured heater element.An additionally manufactured heating element is printed on a flexible substrate 14 and attached to an aircraft component having complex geometric surfaces. The heating element is for...
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JP2020066424A |
To provide an ice protection system and an H-shaped heater that are capable of preventing ice from growing in a joint area of an aircraft component.An ice protection system for an aircraft component comprises multiple heaters. The aircra...
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JP2020063040A |
To provide systems and methods that allow improved bus bars.A resistive heating circuit for a heated or ice-protected aircraft structure includes a flexible dielectric substrate, a resistive heating element supported by the substrate, an...
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JP2020050333A |
To provide a technique capable of eliminating concerns about a starting delay phenomenon in an anti-icing system for an aircraft.Ice detection systems 102 for aircraft and related methods are disclosed. A disclosed example ice detection ...
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JP2020040655A |
To provide a hybrid heater system for aircraft wing ice protection.A hybrid heater system includes a voltage source, a carbon nano-tube (CNT) heater, a first positive temperature coefficient (PTC) heater disposed in parallel with the CNT...
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JP6666159B2 |
An anti-icing system according to the present invention includes: a piccolo tube (11) that includes a flow path through which heated gas flows in the longitudinal direction from a rear end to a front end, and a plurality of ejection hole...
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JP6661369B2 |
Temperature of a structural member is maintained at allowable temperature or less by suppressing heat transfer from a high-temperature duct to the structural member. An insertion sheet according to the present invention is inserted betwe...
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JP6654483B2 |
An anti-icing system at least includes: a precooler that exchanges heat between bleed air and outside air; and an anti-icing unit that receives the bleed air passed through the precooler. A bleed air flow rate adjusting section that adju...
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JP6637856B2 |
In one embodiment, a system includes an inlet grid configured to reduce distortion of an incoming airflow. The system may also include a vibration device coupled to the inlet grid and a controller communicatively coupled to the vibration...
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JP6632845B2 |
An induction heating system employs a ferromagnetic susceptor mounted proximate an exterior of flight surface of an aircraft. At least one electrically conductive coil is mounted proximate the ferromagnetic susceptor. The at least one el...
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JP2020006948A |
To provide an ice protection system for an aerodynamic surface of an aircraft.An aerodynamic surface of an aircraft has a flow facing side 120 and an inwardly facing side 130 that opposes the flow facing side. An ice protection system 14...
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JP6609483B2 |
A monitored deicing system is disclosed. The monitored deicing system may have a pneumatic deicer 3 and a signal wire 4 running through the pneumatic deicer. The signal wire may break in response to a failure of the pneumatic deicer, suc...
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JP2019531967A |
The electromechanical machine according to the invention is a dual machine, comprising a reversible first machine (32, 33, 34) and a second machine (30, 35) that functions by induction between two windings. .. A second machine can be use...
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JP2019529213A |
Devices and methods for deicing ice-accumulating surfaces (50, 52, 66), for example on the wings (14) of an aircraft (10). Devices and methods for deicing modules (26, 126) include moving parts (64), casings (28, 128), and moving members...
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JP6591181B2 |
The present invention provides a windshield device including: a windshield; a heater that is provided in the windshield and configured to generate heat by energization; a temperature sensor that is provided in the windshield and configur...
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JP6513392B2 |
Systems, methods, and apparatus are disclosed for preventing formation of ice on an engine. Apparatus may include a nozzle housing (300) coupled to a compression stage of the engine and further coupled to a leading edge housing of the en...
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JP6503406B2 |
A coating includes at least one coating layer containing first particles, second particles, and third particles distributed throughout a cross-linked, continuous polymer matrix. An outer surface of the coating layer includes surfaces of ...
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JP6501553B2 |
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JP6501552B2 |
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JP6495150B2 |
Within examples, systems for multiple zone heaters for rotor craft are provided and methods for operation. An example system for a rotor craft comprises multiple blades coupled to a rotor and areas of the multiple blades divided into sec...
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JP6496704B2 |
A thermal management system for a gas turbine engine and/or an aircraft is provided including a thermal transport bus 102 having a heat exchange fluid flowing therethrough. The thermal management system also includes one or more heat sou...
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JP6487658B2 |
In one aspect, methods of detecting ice formation on an aircraft are described herein. In some implementations, a method of detecting ice formation on an aircraft comprises disposing an ice detector (100) on an exterior surface of the ai...
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JP6482759B2 |
A structural substrate (300) for an aircraft structure (606) and methods are presented. A multi-layer hybrid composite material comprises an outermost layer (302), an intermediate layer (304), and an innermost layer (306). The outermost ...
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JP6466198B2 |
A system and method for operating an ice detection and deicing system are provided herein. The ice detection and deicing system may use changing magnetic properties of various components caused by temperature changes to detect conditions...
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JP6466185B2 |
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JP6449019B2 |
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 ...
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JP6420858B2 |
An apparatus for providing foreign object debris protection and anti-icing capabilities to an air intake of an aircraft engine 12. The apparatus includes a frame 53 having at least a portion configured to conduct fluids. A tube 74 is pos...
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JP6419293B2 |
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JP6381668B2 |
The present invention is directed to a method of mitigating ice build-up on a substrate, comprising applying to the substrate curable film-forming compositions comprising isocyanate-functional curing agents, film-forming compositions wit...
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JP6377315B2 |
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JP6351968B2 |
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JP6352187B2 |
Systems to apply heat to an aircraft surface are disclosed. In some embodiments, heaters are embedded in a composite structure of an aircraft. In one embodiment, a composite aircraft structure comprises a base comprising a plurality of r...
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JP6340035B2 |
A thermal management system 100 for a gas turbine engine and/or an aircraft is provided including a thermal transport bus 102 having a heat exchange fluid flowing therethrough. The thermal management system also includes a plurality of h...
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JP6333522B2 |
A method and apparatus for detecting an icing condition. The apparatus comprises a piezoelectric material (304) and a vibration detector (308). The piezoelectric material (304) has a surface proximate to a surface of a vehicle. The piezo...
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JP6282400B2 |
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JP6267329B2 |
The present invention relates to a method for reprocessing aircraft de-icing agents comprising glycol, in which (1) the used aircraft de-icing agent, which is possibly contaminated with runway de-icing agents, is collected in a suitable ...
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JP6258328B2 |
A de-icing system for a hemispherical protective housing mounted on an aircraft structure is described. The system can include a series of piezo-electric devices mounted at the boundary of the housing. The piezo-electric devices generate...
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JP6244276B2 |
The present invention relates to a system for monitoring the wing anti-icing valve, comprising: time record device configured to record the time for opening or closing the anti-icing valve; data acquisition device configured to obtain th...
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JP6193691B2 |
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JP6194201B2 |
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 tha...
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JP2017141015A |
To provide an anti-icing system that reduces a direct impingement of a high temperature gas stream on an inner surface of an inlet lip of a jet turbine engine for an aircraft.A system 1 includes vanes 56 extending from a bulkhead into an...
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JP2017136893A |
To provide an anti-icing device which has a simple structure and which can acquire anti-icing performance corresponding to displacement of a stagnation point without increasing air resistance.An anti-icing device 10 blows a heating gas t...
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JP2017132456A |
To provide propeller blades having an icephobic coating.A propeller blade for rotation about a hub assembly is provided. The propeller blade defines a radial direction along its length from a blade root to a blade tip. The propeller blad...
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JP6170531B2 |
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