A system includes a foreign object damage (FOD) screen configured to be disposed upstream of an air intake of a gas turbine engine and to keep debris from entering the air intake. The FOD screen is configured to extend across a fluid flow path extending through the air intake into the gas turbine engine. The FOD screen includes a flexible, woven fabric made of a non-metal material and configured to absorb and dissipate energy from the debris, and the flexible, woven fabric includes a tensile strength ranging between 2700 megapascals (mPa) and 3700 mPa.

An aircraft has an outer skin defining a contour and an air intake assembly including an air cleaning assembly. The air cleaning assembly includes an exterior surface that conforms to the contour of the aircraft, and a lip secured to the outer skin. The air intake assembly includes a pressure recovery device including a flange secured to the lip of the air cleaning assembly, and also includes an outer wall spaced from the exterior surface of the air cleaning assembly.

A wing comprising a leading edge forming a caisson delimited by a wall and an electrically conductive skin forming a lower surface and an upper surface and pierced with holes. A pump is provided to suck the air present in the caisson and/or to inject air into the caisson. The wing includes a voltage generator. Each hole is equipped with an anti-clogging system which comprises an electrically conductive electrode, an electrically insulating body having a stem which lodges in the hole and which has a central orifice in which the electrode lodges. The outer face of the stem has at least one tooth, where each tooth protrudes from the outer face of the stem and extends over the height of the stem. The at least one tooth is distributed around the stem so as to create at least one channel.

An air inlet for an aircraft propulsion system nacelle includes an outer skin, an inner skin, a lip skin, and a forward bulkhead. The lip skin extends between and to an outer end and an inner end. The outer end is disposed at the outer skin. The inner end is disposed at the inner skin. The forward bulkhead includes a first bulkhead portion and a second bulkhead portion. The first bulkhead portion and the second bulkhead portion are mounted to the outer skin. The first bulkhead portion and the second bulkhead portion are mounted to the inner skin. The first bulkhead portion includes a rigid body material and the second bulkhead portion includes a flexible body material.

A propulsion system for an aircraft includes an engine, a plurality of sensors, and a controller. The engine includes an air intake. The plurality of sensors includes an outside air temperature (OAT) sensor and an air intake sensor. The OAT sensor is disposed outside the engine and configured to measure an OAT. The air intake sensor is disposed inside the air intake and configured to measure an air intake temperature (T.sub.1). The controller is configured to: calculate an actual charge heating value (CHactual), compare the CHactual to a charge heating threshold value (CHthresh) to identify the CHactual is greater than or less than the CHthresh, identify a presence or an absence of an unusual engine performance condition for the engine, and identify a presence or an absence of a blockage condition of the air intake based on the CHactual greater than the CHthresh and the presence of the unusual engine performance condition.

The invention relates to a turbomachine (24) of the open rotor type or a turboprop engine comprising a nacelle (26) defining an air inlet (28), a central hub (30) and an annular air intake section (32) surrounding the central hub (30) and opening into a air supply main section (34), with the central hub (30) comprising a central trap (36) having an aperture (38) for trapping the foreign objects in an air flow entering the turbomachine (24), and an air recovery channel (48) having a discharge end (48a), through which said air recovery channel (48) opens into the main section (34), provided on the central hub (30).

A three-dimensional auxetic structure, comprising a plurality of adjoining hollow cells, each hollow cell having cell walls and a transversal cross section of the plurality hollow cells following a two-dimensional auxetic pattern, each cell wall comprising folding lines parallel to a plane containing the auxetic pattern such that peaks and valleys are defined in the cell walls and the cell walls being foldable along the folding lines.

An air intake unit for an engine of an aircraft and having: a housing, inside which a plenum is defined, which can be connected to the engine of the aircraft; a main intake opening; an air filter which engages the main intake opening; a bypass intake opening; a shutter device, which is coupled to the bypass intake opening and has two partitions, which are mounted so as to rotate around respective rotation axes parallel to and spaced apart from one another; and an actuator, which moves the shutter device between a closed position and an open position. In the open position of the shutter device, an upper partition is arranged transversely to the wall of the housing and in a central area of the bypass intake opening, and a lower partition is arranged parallel to the wall of the housing and overlaps said wall.

A system includes an engine cover covering a side-facing rotorcraft engine and having an opening and an ice protection member mounted on the engine cover between the opening and the engine, an area of the ice protection member smaller than an area of the opening. The ice protection member is configured to partially cover the opening to prevent ice having a particular size from entering into the engine and to allow air flow downstream into the engine.

An energy absorbing arrangement may comprise an inner barrel comprising a centerline axis, an outer barrel, a webbing extending between the outer barrel and the inner barrel and configured to be offset from a nose lip by a distance, the webbing being folded together to form a plurality of folds, the plurality of folds being stitched together via a plurality of stitches, wherein the webbing is configured to absorb energy from an object in response to the object passing through the nose lip and applying a force to the webbing.