Goodrich Corporation

Sugumaran Selvaraj

Jin Hu

Nathaniel Ching

Rhushikesh Patil

Sathish Thangavel

Galdemir Cezar Botura

Shyam Kumar Dattatri

Alex Zadell

Karthik Debbadi

Anagha Shivaprakash Gowda

Satish Thangavel

El Hassan Ridouane

A hybrid deicing system is disclosed herein. The hybrid deicing system includes a first deicing system coupled to a high critical zone of a control surface, the first deicing system providing thermal energy to the high critical zone of the control surface to remove ice from the control surface, a second deicing system coupled to a low critical zone of the control surface, the second deicing system configured to vibrate the control surface to remove ice from the control surface, and a controller configured to control the first deicing system and the second deicing system.

Hybrid ice protection system

A sustainable hybrid piezoelectric matrix ice protection system is provided. The system includes at least one energy harvester and anti-icing device and an energy storage device. Responsive to electrical power generated by the at least one energy harvester and anti-icing device being greater than a first threshold, the at least one energy harvester and anti-icing device stores the electrical power in the energy storage device. Responsive to the electrical power generated by the at least one energy harvester and anti-icing device being less than the first threshold, the at least one energy harvester and anti-icing device generates continuous, low-frequency vibrations for anti-icing.

Sustainable hybrid piezoelectric matrix ice protection system

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.

Systems and methods for gas generator for pneumatic deicer

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.

Ice protection system for a component of an aerodynamic system

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.

Growing community of inventors

Karnataka, India

Sugumaran Selvaraj