公开(公告)号：US20190128780A1

公开(公告)日：2019-05-02

申请号：US16225285

申请日：2018-12-19

Applicant: Airbus Operations SAS

Inventor： Antoine PILON ,  Natalino AGOSTINO ,  Adrien PIERREL

IPC: G01M15/14 ,  B64D45/00 ,  F02C9/00 ,  F02D41/22 ,  G05B23/02 ,  G07C5/08

Abstract: A monitoring method, the purpose of which is, when a loss of power is detected in an aircraft engine, to generate an alarm in the form of a single message displayed on a display screen in the cockpit, in order to indicate if the level of damage suffered by the engine is critical or not. The steps implemented are based on alarm signals transmitted by a central processing unit of the engine and also on alarm signals transmitted by a diagnostic device for the onboard systems of the aircraft, in order to take account of both the situation of the engine and also the situation of the systems surrounding the engine which can be affected by damage to an engine.

公开(公告)号：US20250025724A1

公开(公告)日：2025-01-23

申请号：US18775921

申请日：2024-07-17

Applicant: AIRBUS OPERATIONS SAS

Inventor： Antoine PILON

IPC: A62C3/06 ,  A62C2/04 ,  A62C3/08

Abstract: A method for monitoring an engine of an aircraft supplied with dihydrogen, comprising a safety device including a safety valve that is movable between an open position in which the engine is supplied with dihydrogen and a closed position in which the engine is no longer supplied with dihydrogen, an engine fire detection system, a dihydrogen leak detection system and an engine damage detection system, and comprising electronic circuitry adapted to implement the monitoring method. If a locking authorization is given and if one out of three conditions A, B and C is true, then the safety device closes the safety valve, with: the condition A is true if an engine fire detection system detects a fire, the condition B is true if a dihydrogen leak detection system detects a dihydrogen leak, and the condition C is true if an engine damage detection system detects engine damage.

公开(公告)号：US20170363514A1

公开(公告)日：2017-12-21

申请号：US15621416

申请日：2017-06-13

Applicant: Airbus Operations SAS

Inventor： Antoine PILON

IPC: G01M15/14 ,  F02D41/22 ,  G05B23/02 ,  G07C5/08

CPC classification number: G01M15/14 ,  B64D45/00 ,  B64D2045/0085 ,  F02C9/00 ,  F02D41/22 ,  F05D2260/80 ,  F05D2270/303 ,  F05D2270/334 ,  F05D2270/335 ,  G05B23/0213 ,  G05B23/0218 ,  G05B23/0235 ,  G05B2219/45071 ,  G07C5/085

Abstract: A monitoring method, the purpose of which is, when a loss of power is detected in an aircraft engine, to generate an alarm in the form of a single message displayed on a display screen in the cockpit, in order to indicate if the level of damage suffered by the engine is critical or not. The steps implemented are based on alarm signals transmitted by a central processing unit of the engine and also on alarm signals transmitted by a diagnostic device for the onboard systems of the aircraft, in order to take account of both the situation of the engine and also the situation of the systems surrounding the engine which can be affected by damage to an engine.