Airbus Operations (s.a.s.)

Airbus France

Airbus Operations Gmbh

Gilles Chene

Alain Porte

Jacques Lalane

Arnaud Hormiere

Amelie Le Louarn

Fabrice Gantie

Fabienne Montetagaud

Nathalie Pascal

Pierre Jacquet-Francillon

A de-icing device includes a hot air circuit including an inlet for hot air bled from an engine, and a duct connecting the inlet to an outlet of the circuit which opens towards the leading edge. The device also includes electrical heating means associated with the duct, and control means for controlling the heating means connected to detection means that detect the temperature of the hot air downstream of the heating means and are able to activate these if the detected temperature of the bled air is below a value corresponding to a minimum temperature required for de-icing, increased by a predetermined margin. The range of temperatures of the hot air supplied to the leading edge is lowered overall, whereas the minimum de-icing temperature is assured. Composite materials can be used near the leading edge without being damaged.

Method and device for using hot air to de-ice the leading edges of a jet aircraft

An aircraft nacelle includes a pipe, a peripheral wall, a lip connecting the pipe and peripheral wall and delimiting an air intake. A frost treatment system treats a zone extending along a longitudinal section of a point A at the peripheral wall at a point B at the pipe and includes a front frame delimiting with the lip a pipe circulating de-icing hot air. An acoustic pipe coating includes a reflective layer, at least one alveolar structure, and at least one acoustically resistive structure. The front frame includes a junction zone with the lip and/or the pipe offset toward the nacelle front relative to B. Pipes inside the lip and the pipe convey hot air from the pipe to circularly arranged discharges corresponding to B. The pipes extend beyond the junction between the front frame and the lip and/or the pipe and are delimited by at least one isolating partition.

Aircraft nacelle including an optimised ice treatment system

A system for spraying liquid () for a windshield () of an aircraft including a spray-liquid supply circuit (), a pressurized-gas supply circuit () designed to purge the spray-liquid supply circuit, and at least one nozzle () disposed downstream from the circuits and designed to spray the spray liquid and pressurized gas on a windshield, characterized in that the system includes an auxiliary means of compression () ready to compress gas designed to circulate in the pressurized-gas supply circuit, the auxiliary means of compression being positioned near the nozzle. Also, an aircraft cockpit provided with at least such a spray system.

System for the spraying of spray liquid for aircraft windshield, and cockpit provided with such a spraying system

The invention relates to an aircraft nacelle that comprises a discharge means () for establishing a communication between the inside of the nacelle and the outside thereof, and a junction area between two members (), and at which the two members are superimposed, both members each having a surface defining the outer surface of the nacelle on either side of the junction area, characterized in that said discharge means () includes a dual-portion shim (), i.e. a first portion provided between the superimposed panels and including at least one protruding and/or recessed member for forming a passage between said panels in order to establish a communication between the inside and the outside of the nacelle, and a second portion at the level of only one panel, i.e. that located inside at the junction area, in order to protect the same against excessive temperatures.

Aircraft nacelle including hot air discharge means

The invention relates to acoustic lining for an aircraft, which can cover a leading edge, such as an air inlet in the nacelle of a propulsion unit, said lining comprising: (i) from the inside outwards, a reflective layer (), at least one cellular structure () and an acoustically resistive structure () having a pre-determined proportion of open surface; and (ii) at least one frost treatment system in the form of at least one heating layer () comprising open zones through which acoustic waves can pass, which co-operate at least partially with the open zones in the acoustically resistive structure. The invention is characterized in that the acoustically resistive structure () includes at least one structural layer () with openings () and in that said at least one heating layer () is disposed under the structural layer ().

Acoustic coating for an aircraft incorporating a frost treatment system by joule effect

A device for protection against icing for aircraft engines including at least one sensor, sensitive to an amount of accumulated ice, arranged in the air intake of an aircraft engine, a system for measuring the amount and comparing the amount to be predetermined threshold and a triggering system for launching a response to the detection of the crossing of the predetermined threshold, the response may be an alarm, an increase in the engine power delayed by the engine control system or the return of hot air upstream of the engine.

Device for protection against icing for aircraft engines and related de-icing method

A system for spraying liquid for a windshield of an aircraft includes a spray-liquid supply circuit, a pressurized-gas supply circuit designed to purge the spray-liquid supply circuit, and at least one nozzle disposed downstream from the circuits and designed to spray the spray liquid and pressurized gas on an aircraft windshield, wherein the system includes a control device able to simultaneously actuate the temporary spraying of spray liquid and of pressurized gas respectively in the spray-liquid spraying circuit and in the pressurized-gas spray circuit in such a way that a pressurized-gas spraying time is strictly greater than a spraying-liquid spraying time. For example, the control device includes a time-lag relay controlling the pressurized-gas supply circuit.

A process for de-icing an air intake cowling ( ) of a reaction motor, having an air intake lip ( ), a de-icing system ( ) and acoustic attenuation part ( ), where the acoustic attenuation part includes separate islands ( ) formed by a sandwich of an acoustically resistive porous layer forming a portion of the external envelope ( ) of the fan channel delimited by the air intake lip, a cellular core, and a reflector ( ), has the steps of sending into the lip, preferably in the direction of the acoustic attenuation islands, the warm fluid under pressure of the de-icing system, and causing the fluid to escape outside the cowling, through one or several openings ( ) of suitable shape and size, provided in the cowling.

Growing community of inventors

Toulouse, France

Gilles Chene