公开(公告)号：US20190233127A1

公开(公告)日：2019-08-01

申请号：US16253397

申请日：2019-01-22

Applicant: Airbus Operations SAS

Inventor： Jonathan CARCONE ,  Pierre-Louis ROUX

IPC: B64D15/06 ,  B64D15/12 ,  B64D15/22

CPC classification number: B64D15/06 ,  B64D15/02 ,  B64D15/04 ,  B64D15/12 ,  B64D15/22

Abstract: A device for deicing a wall of an aircraft, comprising a closed circuit. The closed circuit comprises at least one condenser, positioned in the environment of the wall that is to be deiced, and in which a heat-transfer fluid condenses, generating energy in the form of latent heat which is transmitted to the wall that is to be deiced, at least one evaporator positioned in the environment of a heat source sited remotely with respect to the wall, and in which the heat-transfer fluid evaporates, absorbing energy in the form of latent heat coming from the heat source. At least part of the closed circuit is facing, in contact with, or positioned in, the wall that is to be deiced, being made of a material transparent to electromagnetic fields.

公开(公告)号：US20190118955A1

公开(公告)日：2019-04-25

申请号：US16156272

申请日：2018-10-10

Applicant: Airbus Operations SAS

Inventor： Alain PORTE ,  Jonathan CARCONE

IPC: B64D15/04

Abstract: A frost protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud provided with at least one acoustic panel and an air intake lip forming a leading edge of the nacelle. The protection system comprises a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the at least one acoustic panel.

公开(公告)号：US20190308737A1

公开(公告)日：2019-10-10

申请号：US16377813

申请日：2019-04-08

Applicant: Airbus Operations SAS

Inventor： Alain PORTE ,  François PONS ,  Jonathan CARCONE

IPC: B64D15/22 ,  B64D29/00 ,  B64D15/12 ,  H05B1/02 ,  H05B3/00

Abstract: An aircraft engine nacelle comprising an icing protection system and an icing protection method for such an aircraft engine nacelle. The aircraft engine nacelle comprises an air inlet comprising a lip, a tubular air inlet piece and an icing protection system. The icing protection system comprises an icing prevention means powered continuously by a first electrical energy source and wholly or partly covering the lip, a de-icing means powered by a second electrical energy source covering the tubular air inlet piece and a controller configured to acquire a current total air temperature value, and control the second electrical energy source as a function of the current total air temperature value.