公开(公告)号：US20180297567A1

公开(公告)日：2018-10-18

申请号：US16010868

申请日：2018-06-18

Applicant: Safran Nacelles ,  Safran Landing Systems

Inventor： Patrick GONIDEC ,  Hakim MAALIOUNE ,  François TAILLARD ,  Denis JONTEF ,  Marie-Laure DE-CRESCENZO ,  Jean-François HAMMANN

IPC: B60T8/17 ,  B64C25/42 ,  F02K1/76 ,  B60T8/171 ,  B60T8/1761

CPC classification number: B60T8/1703 ,  B60T8/171 ,  B60T8/17616 ,  B64C25/42 ,  F02K1/76 ,  F05D2220/323 ,  F05D2260/90 ,  F05D2260/901 ,  F05D2260/902 ,  Y02T50/671

Abstract: The present disclosure relates to a method of controlling the braking of an aircraft equipped with a landing gear bearing braked wheels, the aircraft being propelled by jet engines and equipped with a thrust reversal system, the method involving the steps of estimating the grip/adhesion of the braked wheels and activating the thrust-reversal system or modulating the reverse-thrust generated by the thrust-reversal system if this system is already activated, based on the estimated grip/adhesion.

公开(公告)号：US20170327240A1

公开(公告)日：2017-11-16

申请号：US15655276

申请日：2017-07-20

Applicant: SAFRAN NACELLES

Inventor： Olivier KERBLER ,  Fabrice Henri Emile METEZEAU ,  Patrick GONIDEC ,  Loïc GRALL

IPC: B64D29/06 ,  B64D27/16 ,  F02K1/72

CPC classification number: B64D29/06 ,  B64D27/16 ,  B64D33/04 ,  F02K1/72 ,  F05D2220/323 ,  Y02T50/672

Abstract: The present disclosure relates to an aircraft turbojet engine nacelle, the nacelle including a rear section without a lower bifurcation, the rear section including a thrust reversal system, the thrust reversal system including a mobile cowl. The nacelle includes a guide system that translates as one with the mobile cowl, the guide system collaborating with at least one slide that is fixed in relation to the nacelle, the guide system and the slide being arranged near the position referred to as the 6 o'clock position.

公开(公告)号：US20250050148A1

公开(公告)日：2025-02-13

申请号：US18723071

申请日：2022-12-21

Applicant: Safran Nacelles

Inventor： Patrick GONIDEC ,  Patrick André BOILEAU

IPC: A62C3/08 ,  A62C37/36 ,  B64D45/00

Abstract: An assembly for an aircraft propulsion system including a nacelle extending around a longitudinal axis and including an internal face that delimits, with an external face of the aircraft propulsion system, a fire zone, an extinguisher for extinguishing a fire in the fire zone, the extinguisher including a tank for containing an extinguishing agent, and a spraying nozzle for spraying the extinguishing agent out of the tank and into the fire zone, an activation device for activating the extinguisher, and a controller that transmits a control order to the activation device, the activation device receiving the control order and transmitting an activation order to the extinguisher, the activation order activating the extinguisher so as to cause the expulsion of the extinguishing agent via the nozzle. The extinguisher is mounted on the nacelle. The assembly includes one or more of a wireless communicator and a cable.

公开(公告)号：US20240217667A1

公开(公告)日：2024-07-04

申请号：US18571073

申请日：2022-06-10

Applicant: SAFRAN NACELLES

Inventor： Patrick GONIDEC ,  Albin LAFONT ,  Virginie Emmanuelle Anne-Marie DIGEOS ,  Stuart HARDYMAN

IPC: B64D33/02 ,  F02C7/045 ,  G10K11/168

CPC classification number: B64D33/02 ,  F02C7/045 ,  B64D2033/0206 ,  F05D2220/323 ,  F05D2250/283 ,  F05D2260/96 ,  G10K11/168

Abstract: An acoustic treatment panel intended to be disposed on at least one wall of an aircraft propulsion unit in contact with a fluidic flow, the panel including a first, acoustically reflective skin, a second, acoustically porous skin intended to be in contact with the fluidic flow, and a honeycomb structure extending between the first skin and the second skin and having a plurality of cavities. The panel includes at least one acoustically transparent reinforcing wall passing through a plurality of cavities of the honeycomb structure and extending from the second skin to the first skin, forming a non-orthogonal angle with the first and second skins.

公开(公告)号：US20210078711A1

公开(公告)日：2021-03-18

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.

公开(公告)号：US20200347800A1

公开(公告)日：2020-11-05

申请号：US16930524

申请日：2020-07-16

Applicant: Safran Nacelles

Inventor： Patrick GONIDEC ,  Olivier KERBLER ,  Alexandre PHI ,  Jean-Paul RAMI ,  STEPHANE TIREL ,  Jean-Baptiste GOULARD ,  Matthieu VANDERLINDEN ,  Arnaud CARLES-ESPITEAU

IPC: F02K1/62 ,  B64D29/06 ,  F02K1/76

Abstract: An improved thrust reverser for an aircraft propulsion assembly includes redirection of the air flow for performing the thrust reversal by one or more closure membranes, i.e. by thin and flexible structures deployed across the propulsion assembly. The improved thrust reverser includes at least one closure membrane arranged to deflect at least one portion of the air flow in the direction of the evacuation structure when the thrust reverser is in the reverse jet position and an intermediate structure movable in rotation relative to the fixed structure.

公开(公告)号：US20180187630A1

公开(公告)日：2018-07-05

申请号：US15904671

申请日：2018-02-26

Applicant: Safran Nacelles

Inventor： Patrick GONIDEC ,  Hakim MAALIOUNE

IPC: F02K1/76 ,  B64D29/06 ,  B64D33/04 ,  F02K1/70

CPC classification number: F02K1/763 ,  B64D27/16 ,  B64D29/06 ,  B64D33/04 ,  B64D2221/00 ,  F02K1/70 ,  F05D2220/323

Abstract: The present disclosure relates to a nacelle for an aircraft turbofan engine and an aircraft that includes a nacelle that includes a supply device for supplying electric power to an electric actuator system allowing movement of a mobile member for deflecting a stream between a first position parallel or substantially parallel to the flow of the stream and a second position allowing the flow of the stream to be deflected so as to modify the path of the stream in one direction and/or the speed of the stream.

公开(公告)号：US20170328305A1

公开(公告)日：2017-11-16

申请号：US15371281

申请日：2016-12-07

Applicant: SAFRAN NACELLES

Inventor： Patrick GONIDEC ,  Olivier KERBLER ,  Corentin HUE ,  Patrick BOILEAU

IPC: F02K1/72 ,  F02K1/76 ,  F02K1/12

CPC classification number: F02K1/72 ,  F02K1/1261 ,  F02K1/763 ,  Y02T50/671

Abstract: A thrust reverser for a nacelle of an aircraft turbojet engine includes at least one movable thrust reverser cowl, a means for locking the cowl, a variable section outlet nozzle, and at least one actuator including an actuator rod. The thrust reverser is provided with a resilient coupler comprising a body which is rigidly connected to the thrust reverser cowl and a resilient return and abutment device that engages with the actuating rod of the actuator such as to resiliently return the nozzle to a neutral position. The return device is calibrated such that, when the cowl is unlocked, the return device opposes the relative movement of the actuating rod relative to the cowl, such as to enable the movement of the cowl and the nozzle, and when the cover is locked, the actuator drives the actuating rod against the return device to enable the movement of the nozzle.

公开(公告)号：US20170082064A1

公开(公告)日：2017-03-23

申请号：US15364623

申请日：2016-11-30

Applicant: SAFRAN NACELLES

Inventor： Sarah TISSOT ,  Xavier BOUTEILLER ,  Olivier KERBLER ,  Patrick GONIDEC

IPC: F02K1/72 ,  F02K3/06

CPC classification number: F02K1/72 ,  F02K1/09 ,  F02K1/1261 ,  F02K3/04 ,  F02K3/06 ,  F05D2250/42

Abstract: The present disclosure relates to a turbojet engine nacelle having an external cowling with an internal wall defining, with an internal fixed structure, an annular flow channel for a secondary airflow and an exhaust nozzle for said secondary airflow. The nozzle includes at least one opening, at least one continuous downstream end portion, downstream of said opening, and at least one door moving between a closed position and an open position allowing the passage of a part of said airflow through said opening. The nacelle is notable in that it includes a shaped device for activation of the door, during their activation from a closed position to an open position of the door, to drive the door in a combined movement that is translational in the direction running upstream from the nacelle and rotary towards the exterior of the nacelle.