An ice protection assembly on an airfoil includes a heater positioned on the leading edge, and one or more ice phobic layers positioned to inhibit runback ice formation on the surface of the airfoil downstream of the heater.

An angle of attack sensor includes a vane assembly and a multi-piece faceplate adjacent the vane assembly. The faceplate includes a mounting plate having an opening and a heated chassis positioned adjacent the mounting plate and having a ring portion extending into the opening. The ring portion includes a narrow fore portion extending into the opening, a wide aft portion extending into the opening, and an aft-located ramp connected to the wide aft portion and extending through the opening beyond an exterior surface of the mounting plate.

Presented herein are articles and methods relating to manufactured superhydrophobic, superoleophobic, and/or supermetallophobic surfaces with macro-scale features (macro features) configured to induce controlled asymmetry in a liquid film produced by impinging phase (e.g., impinging droplet(s)) onto the surface, thereby further reducing the contact time between an impinging liquid and the surface.

A gas turbine engine for an aircraft comprises a high-pressure (HP) spool comprising an HP compressor and a first electric machine driven by an HP turbine; a low-pressure (LP) spool comprising an LP compressor and a second electric machine driven by an LP turbine; a combustion system comprising a fuel metering unit; and an engine controller configured to, in response to a change of a power lever angle setting indicative of a deceleration event, reduce fuel flow to the combustion system by the fuel metering unit, and to operate the first electric machine in a generator mode to reduce the HP spool rotational speed and engine core mass flow.

An aerodynamic friction energy deicing system can include a heat energy device configured to be operatively connected to an aircraft structure and to convert heat energy due to aerodynamic friction on the aircraft structure into another form or to store heat energy due to aerodynamic friction on the aircraft structure. The converted or stored energy can be used for any suitable purpose, e.g., for use in ice prevention and/or deicing and/or powering one or more aircraft systems.

This invention provides durable, low-ice-adhesion coatings with excellent ice-adhesion reduction. Some variations provide a low-ice-adhesion composition comprising a composite material containing at least a first-material phase and a second-material phase that are nanophase-separated on a length scale from 10 nanometers to less than 100 nanometers, wherein the first-material phase and the second-material phase further are microphase-separated on a length scale from 0.1 microns to 100 microns. The larger length scale of separation is driven by an emulsion process, which provides microphase separation that is in addition to classic molecular-level phase separation. The composite material has a glass-transition temperature above 80 C. The coatings may be characterized by an AMIL Centrifuge Ice Adhesion Reduction Factor up to 100 or more. These coatings are useful for aerospace surfaces and many other applications.

A magnet for an anti-ice system includes a core and at least one coil wound about a perimeter of the core. The core includes a first material having a first epoxy composition. The at least one coil includes a second material having a second epoxy composition. The first epoxy composition and the second epoxy composition each include a bisphenolic resin composition including bisphenol AF and at least one of a filler or a conductivity modifier.

Viscoelastic icephobic surfaces of the present disclosure include organogel particle beads dispersed in an elastomer matrix. The surfaces are highly repellant to ice formation, easy and cost efficient to apply, and have long term durability for harsh outdoor applications.

Systems and methods for operating sensors in an aircraft are provided. Aspects include receiving, by a processor associated with a sensor, a first request to test a transmitter function of the sensor, transmitting a test message to one or more other sensors associated with the aircraft, and listening to a transmitter associated with each of the one or more other sensors to determine a transmitter status of the sensor, wherein the transmitter status of the sensor is a pass status based on receiving a confirmation from at least one of the one or more other sensors. Aspects also include transmitting air data parameters and health status parameters associated with the air data probe to the one or more other air data probes.

An aircraft includes an environmental control system having a bleed air inlet, a gas turbine engine having a low pressure bleed air supply and a high pressure bleed air supply, and a turbo air cycle machine. The turbo air cycle machine includes a compressor fluidly coupled to the low pressure bleed air supply, as well as a turbine fluidly coupled to at least one of the low pressure bleed air supply or the high pressure bleed air supply.