公开(公告)号：US11773788B2

公开(公告)日：2023-10-03

申请号：US17126257

申请日：2020-12-18

Applicant: Safran Nacelles

Inventor： Patrick Gonidec ,  Jean-Paul Rami

IPC: H04B10/00 ,  F02C9/16 ,  B64D31/02 ,  B64D47/02 ,  H04B10/116 ,  H04J14/00

CPC classification number: F02C9/16 ,  B64D31/02 ,  B64D47/02 ,  H04B10/116 ,  B64D2203/00 ,  F05D2220/323 ,  F05D2270/01 ,  F05D2270/301 ,  F05D2270/3061

Abstract: The present disclosure concerns the communication between electronic systems in an aircraft subassembly such as a propulsion unit. This communication is at least partially carried out by light signals transmitted through at least one interior volume of the sub-assembly, this interior volume defining an optical channel. To this end, at least one of these systems includes an emitter arranged to emit a light signal and modulate it depending on data to be transmitted generated by this system, and at least one other of these systems includes at least one receiver capable of receiving this light signal.

公开(公告)号：US20220219831A1

公开(公告)日：2022-07-14

申请号：US17614146

申请日：2020-05-14

Applicant: SAFRAN NACELLES

Inventor： Patrick Gonidec ,  Jean-Paul Rami

IPC: B64D33/02 ,  B64D29/00 ,  F02C7/047 ,  B64C7/02 ,  B64D15/12

Abstract: The invention relates to an air intake lip of an aircraft engine nacelle extending along an axis X, in which an air flow circulates from upstream to downstream, the lip extending annularly about the X-axis and having an inner wall facing the X-axis and an outer wall which is opposite the inner wall, the inner wall and the outer wall being connected by an upstream wall and a partition so as to delimit an annular cavity, in which at least one infrared emission source is housed, wherein at least one wall, selected among the inner wall, the outer wall and the upstream wall, is made of a material configured to transmit on an outer face at least 30% of the infrared received on an inner face.

公开(公告)号：US11492128B2

公开(公告)日：2022-11-08

申请号：US17025051

申请日：2020-09-18

Applicant: Safran Nacelles

Inventor： Patrick Gonidec ,  Jean-Paul Rami ,  Hakim Maalioune ,  Rémi Billard ,  Vincent Rigolet ,  Jean-Denis Sauzade

IPC: B64D15/16 ,  B64D15/22

Abstract: A method for de-icing or anti-icing an aircraft portion having at least one piezoelectric element fastened on the inner face of the aircraft portion includes, during a design phase of the aircraft portion, placing the piezoelectric element on an area of the aircraft portion to determine frequencies of resonance and increased dynamic coupling, and during the de-icing or anti-icing of the aircraft portion, the same piezoelectric element is excited according to the natural frequencies of the area.