An air data probe includes a faceplate, a body connected to the faceplate, and a heating system comprising a coil, the coil being connected to the faceplate. The coil generates an electromagnetic field that couples with the body to heat the body.

Ice protection systems of aircraft and related methods are disclosed. In one embodiment of the present invention, the system includes a gas-discharge lamp and an electric power source. The gas-discharge lamp is configured to emit infrared radiation toward an inner surface of an aircraft skin. The electric power source is operatively connected to the gas-discharge lamp.

Ice protection systems of aircraft and related methods are disclosed. In one embodiment of the present invention, the system includes a gas-discharge lamp and an electric power source. The gas-discharge lamp is configured to emit infrared radiation toward an inner surface of an aircraft skin. The electric power source is operatively connected to the gas-discharge lamp.

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.

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 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.

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.

An arrangement for mechanically changing a surface includes an insulating layer, a pair of electrodes, which is arranged on or in the insulating layer, and a piezo element, which is arranged on or in the insulating layer. The piezo element is separated from the pair of electrodes by the insulating layer. The pair of electrodes is designed to generate in a region of the piezo element an electric field, which causes the piezo element to carry out a mechanical change of shape, in order in this way to mechanically change a surface of the arrangement. The pair of electrodes is also designed to generate the electric field such that the electric field has a minimum field strength in a surrounding area of the arrangement, in order in this way to generate a plasma in the surrounding area of the arrangement.

A method of forming an ice resistant surface includes determining, based at least in part on a desired pattern of frost formation, a vertex angle for a ridge that is to be formed on a substrate. The method also includes determining, based at least in part on the desired pattern of frost formation, a vertex height for the ridge that is to be formed on the substrate. The method further includes forming a plurality of ridges on the substrate, where each ridge in the plurality of ridges has the vertex angle and the vertex height.

Aspects of the present disclosure provide coatings and methods for depositing coatings onto surfaces. In one aspect, a method for forming a coating includes applying a composition to a surface of a component, the composition including a first polymer, a second polymer that is a fluoropolymer, an isocyanate, and a curative. The method includes curing the mixture at a first temperature of about 50° C. or greater and increasing the first temperature to a second temperature of about 80° C. or greater. The method includes obtaining a coating disposed on the surface of the component, the coating having a thickness of from about 10 mils to about 50 mils and a void density of less than 5 voids of size 0.5 mm or greater per cm.sup.2.