Systems and methods to facilitate a steep final approach phase of flight of an aircraft are disclosed. In one embodiment, a method for operating an aircraft during a steep approach phase of flight of the aircraft comprises operating an engine of the aircraft at an idle speed associated with the steep approach type that is lower than an idle speed associated with a non-steep approach type capable of being executed by the aircraft. The method also comprises operating an ice protection system of the aircraft during the steep approach phase of flight of the aircraft.

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.

Pressurized air systems for aircraft and related methods are described herein. An example pressurized air system includes a compressor having a compressor inlet and a compressor outlet. The compressor inlet receives air from a first air source and the compressor outlet supplies pressurized air to an environmental control system (ECS). The pressurized air system includes a turbine having a turbine inlet to receive air from a second air source, a first overrunning clutch operatively coupled between an output shaft of an accessory gearbox and the compressor, the accessory gearbox operatively coupled to a drive shaft extending from an engine of the aircraft, and a second overrunning clutch operatively coupled between the compressor and the turbine. The first and second overrunning clutches enable the accessory gearbox to drive the compressor during a first mode of operation and enable the turbine to drive the compressor during a second mode of operation.

An ice-management method for an aircraft includes scavenging torque from a mast of the aircraft with a system that is configured to provide an ice-management capability. The method includes using the scavenged torque to impart a vibratory force to an arm of the system and imparting the vibratory force from the arm to an inner surface of a spinner of the aircraft via a contact of the arm.

An ice-breaking system for an aircraft, comprising a pneumatic ice-breaking device, an air inlet adapted to receive air from the environment outside the aircraft and an air outlet adapted to discharge air into the outside environment, and a motorized valve having an air loading port connected to the air inlet and an air discharge port connected to the air outlet, the valve being configured to supply air to the pneumatic ice-breaking device in a pulsating way. When the aircraft is in motion, the kinetic energy of the air at the air inlet and originating from the relative motion between the air and the aircraft is converted into air pressure at the pneumatic ice-breaking device, and the air outlet is positioned so that when the aircraft is in motion the air pressure at the air outlet is lower than the outside ambient pressure.

An ice protection assembly includes a pneumatic de-icer attached to an aircraft surface by a vertically aligned carbon nanotube loaded adhesive. The adhesive can be a pressure sensitive adhesive or a chemical adhesive loaded with vertically aligned carbon nanotubes.

Systems and methods for de-icing an aircraft surface. The systems create a shock pulse to create a shock activation. The shock pressure is designed to deform the surface of an erosion shield on the surface in order to expulse ice from the wing. The deformation may be between a negative to a positive shape. In one example, the de-icing occurs from a pulse delivered by pressurized fluid injected into and quickly removed from a recess between the aircraft surface and an erosion shield. A pulse of pressurized air or fluid may be injected into one or more cells formed in the recess, together or alternatively, according to the designed effect on the erosion shield surface.

Systems and methods to facilitate a steep final approach phase of flight of an aircraft are disclosed. In one embodiment, a method for operating an aircraft during a steep approach phase of flight of the aircraft comprises operating an engine of the aircraft at an idle speed associated with the steep approach type that is lower than an idle speed associated with a non-steep approach type capable of being executed by the aircraft. The method also comprises operating an ice protection system of the aircraft during the steep approach phase of flight of the aircraft.

A de-icing assembly for a surface of an aircraft includes: a carcass with a first layer, a second layer, and a carcass centerline and a plurality of seams sewn into the carcass, wherein the plurality of seams join the first and second layers of the carcass together. The assembly includes a plurality of inflation passages formed by the plurality of seams and disposed between the first and second layers of the carcass. The system also includes a manifold fluidly connected to and disposed beneath the carcass, the manifold comprising a width and a manifold centerline oriented approximately perpendicular or parallel to the carcass centerline. The seams are sown by a stitchline formed of carbon nanotube yarn.

A method of attaching a pneumatic de-icer to an aircraft wing includes using two pressure sensitive adhesive layers. A first pressure sensitive adhesive layer is attached to a primed aircraft wing, while a second pressure sensitive adhesive layer is attached to the pneumatic de-icer. The two pressure sensitive adhesive layers are attached to each other to create a high energy bond between the pneumatic de-icer and the aircraft wing.