Abstract: Ice may form along the leading edge of an aircraft wing. A pneumatic deicing system may be configured to crack and dislodge ice along the leading edge of the wing. The pneumatic deicing system may comprise a deicing boot assembly having a deicing boot attached to the leading edge, and a gas generator fluidly coupled to the deicing boot assembly. The gas generator may comprise a propellant and may decompose the propellant, liberating a compressed gas. The compressed gas may be directed to the deicing boot assembly, inflating the deicing boot, which may crack and dislodge the ice.

Abstract: A pressure regulator system is disclosed. The system includes: a valve module; a controller; and a plurality of sensors. The controller is operably coupled to the valve module to adjust outflow of gas from an outlet of the valve module to a plurality of masks in an interior of an aircraft. The plurality of sensors comprises at least one of a pressure sensor and a temperature sensor and the controller is configured to receive feedback of sensed data at the outlet of the valve module about at least outlet pressure and ambient temperature from at least the pressure sensor and the temperature sensor and adjust the outflow of gas from the outlet of the valve module by determining an open-valve time based on the feedback of sensed data received from each sensor.

Abstract: Ice may form along the leading edge of an aircraft wing. A pneumatic deicing system may be configured to crack and dislodge ice along the leading edge of the wing. The pneumatic deicing system may comprise a deicing boot assembly having a deicing boot attached to the leading edge, and a gas generator fluidly coupled to the deicing boot assembly. The gas generator may comprise a propellant and may decompose the propellant, liberating a compressed gas. The compressed gas may be directed to the deicing boot assembly, inflating the deicing boot, which may crack and dislodge the ice.

Abstract: Disclosed is an ice protection system for an aerodynamic surface of an aircraft, a surface having a flow facing side and an inwardly facing side that opposes the flow facing side, the system having: a perforated sheet configured for disposal in the surface; a heating source connected to the perforated sheet; and a suction source disposed to draw ice melted by the heating source through the perforated sheet and heating source.

Abstract: A system for heating an aircraft surface having a thermally disadvantaged zone includes a carbon nano-tube (CNT) sheet heating element having a power inlet configured to receive power from an external electrical power source and provide it to the CNT sheet heating element that extends across the thermally disadvantaged zone. The CNT sheet heating element is configured and arranged such upon application of power from the external electrical power source to the CNT sheet heating element, the CNT sheet heating element produces a first heat output in a first zone and a second heat output in the thermally disadvantaged zone with the second heat output being greater than the first heat output.

Abstract: A valve includes a valve body having an input port and an outlet port. The valve body defines a fluid passageway extending between input port and an outlet port. The valve also includes a valve element disposed in the fluid passageway that controls a flow a fluid through the valve body from the input port to the outlet port. One or more of the fluid passageway and the valve control element is coated with a phobic coating.

Abstract: An aircraft flight surface deicing system includes an electromagnetic field generator and a deicing boot configured for attachment to an aircraft flight surface. The boot includes: one or more inflation regions including a first inflation region; one or more magnetic fluid reservoirs in fluid communication with the first inflation region, the one or more fluid reservoirs including a first fluid reservoir; a magnetic fluid contained in a combination of the first inflation regions and the one or more magnetic fluid reservoirs. In a first state, the magnetic fluid is contained in the first fluid reservoir and, in a deicing state, the electromagnetic field generator generates one or more fields that cause the magnetic fluid to exit the first fluid reservoir and travels along a length of the inflation region.

Abstract: Disclosed is an ice protection system for an aerodynamic surface of an aircraft, a surface having a flow facing side and an inwardly facing side that opposes the flow facing side, the system having: a perforated sheet configured for disposal in the surface; a heating source connected to the perforated sheet; and a suction source disposed to draw ice melted by the heating source through the perforated sheet and heating source.

Abstract: Disclosed is an ice protection system for an aerodynamic surface of an aircraft, a surface having a flow facing side and an inwardly facing side that opposes the flow facing side, the system having: a perforated sheet configured for disposal in the surface; a heating source connected to the perforated sheet; and a suction source disposed to draw ice melted by the heating source through the perforated sheet and heating source.

Abstract: A system for heating an aircraft component of an aircraft includes a heater mat located adjacent the aircraft component and to generate heat. The system further includes a controller coupled to the heater mat and configured to receive an aircraft speed of the aircraft and an outside air temperature (OAT), and to control the heater mat based on the OAT and the aircraft speed.

Abstract: A multi-layered ice detector apparatus includes a first heater strip, a second heater strip, and a plurality of temperature sensors. The first heater strip is configured to be mounted to a surface, the first heater strip forming a first heater layer of the multi-layered ice detector apparatus. The second heater strip is coupled in proximity to the first heater strip, the second heater strip forming a second heater layer of the multi-layered ice detector apparatus. The plurality of temperature sensors are coupled to at least one of the first heater strip and the second heater strip, wherein the plurality of temperature sensors are configured to detect a temperature profile of the multi-layered ice detector apparatus, wherein the temperature profile is indicative of an extent of icing.

Abstract: An ice detection system for an aircraft surface includes a sensor assembly comprising a plurality of temperature sensitive elements configured to be arranged at respective points on the aircraft surface, a control unit arranged to receive signals indicative of a temperature sensed by each of the temperature sensitive elements, a signal conducting bus to transmit the signals from the temperature sensitive elements to the control unit, and means for providing power to the sensor assembly, wherein the sensor assembly further comprises a multiplexer arranged to multiplex the signals from the plurality of temperature sensitive elements into a single signal for transmission on the signal conducting bus to the control unit.

Abstract: An aircraft flight surface deicing system includes an electromagnetic field generator and a deicing boot configured for attachment to an aircraft flight surface. The boot includes: one or more inflation regions including a first inflation region; one or more magnetic fluid reservoirs in fluid communication with the first inflation region, the one or more fluid reservoirs including a first fluid reservoir; a magnetic fluid contained in a combination of the first inflation regions and the one or more magnetic fluid reservoirs. In a first state, the magnetic fluid is contained in the first fluid reservoir and, in a deicing state, the electromagnetic field generator generates one or more fields that cause the magnetic fluid to exit the first fluid reservoir and travels along a length of the inflation region.

Abstract: Disclosed is an ice protection system for an aerodynamic surface of an aircraft, a surface having a flow facing side and an inwardly facing side that opposes the flow facing side, the system having: a perforated sheet configured for disposal in the surface; a heating source connected to the perforated sheet; and a suction source disposed to draw ice melted by the heating source through the perforated sheet and heating source.