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Aircraft leading edge

A technology of aircraft and leading edge, which is applied in the direction of instruments, sound-generating devices, aircraft parts, etc., and can solve problems such as large temperature and pressure changes, and reduction of hot air

Inactive Publication Date: 2010-01-13
AIRBUS OPERATIONS (SAS)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Also, the use of hot air units in certain flight conditions creates certain problems, especially during the deceleration phase before landing, where less hot air is produced due to engine deceleration, which is generally the case with frost most favorable moment
[0015] Finally, this type of deicing treatment device also has the disadvantage that it produces large temperature and pressure changes

Method used

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  • Aircraft leading edge
  • Aircraft leading edge
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Embodiment Construction

[0031] The invention described here is applied to an air intake of an aircraft propulsion device. However, the invention can be applied to different leading edges of an aircraft, which have been treated with anti-icing and sound-absorbing treatments, such as the leading edges of wings.

[0032] In the following description, the so-called frost refers to ice and frost of various properties, structures and thicknesses.

[0033] figure 1 The propulsion device 10 of the aircraft is shown, which is connected under the wing by struts 12 . However, the propulsion unit can be connected to other areas of the aircraft.

[0034] The propulsion means comprise a nacelle 14 in which is mounted a power plant in a substantially concentric manner to drive an air intake mounted on a main shaft 16 . The longitudinal axis of the nacelle is indicated with reference numeral 18 .

[0035] The nacelle 14 includes an inner cavity wall 20 that forms an air intake 22 at the front end. The first part...

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PUM

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Abstract

The subject of the invention is an aircraft leading edge such as, for example, an air intake (22) of a nacelle (14) of a propulsion unit, comprising a covering (26) for acoustic treatment comprising, from the outside inwards, an acoustically resistive porous layer having a given proportion of open surface, at least one cellular structure and a reflective layer, said covering (26) incorporating a frost treatment system, characterized in that a frost treatment system comprises at least one vibration emitter (36).

Description

technical field [0001] The present invention relates to a leading edge of an aircraft, in particular to an air intake duct of a nacelle with a sound-absorbing lining for sound-absorbing treatment and a device capable of avoiding the formation and / or accumulation of ice and / or frost. Background technique [0002] The propulsion unit of the aircraft consists of a nacelle in which is mounted substantially concentrically a power unit driving an air intake unit mounted on the main shaft. [0003] The nacelle has an inner cavity wall that forms the air intake at the front end, the first part of the incoming airflow is called the primary airflow, which passes through the power plant to participate in combustion, and the second part of the airflow is called the secondary airflow, which is taken into The gas unit is guided into an annular duct defined by the inner cavity wall of the nacelle and the outer cavity wall of the power plant. [0004] The noise emitted by the propulsion de...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D15/16B64D33/02F02C7/045G10K11/172
CPCB64D2033/0286G10K11/172B64D2033/0233F02C7/045B64D2033/0206F02C7/047B64D15/163B64D33/02
Inventor 法布里斯·冈蒂耶阿兰·波特
Owner AIRBUS OPERATIONS (SAS)