Method of managing an engine failure on a multi-engined aircraft having a hybrid power plant

摘要

A method of managing an engine failure on a rotary wing aircraft (1) having a hybrid power plant (5) with at least two fuel-burning engines (13, 13′), at least one electric machine (12), and a main gearbox (11). Said aircraft (1) also has electrical energy storage means (14) and a main rotor (2) mechanically connected to said hybrid power plant (5). In said method, during each flight, the operation of said engines (13, 13′) is monitored in order to detect a failure of any one of them, and then once a failure of one of said engines (13, 13′) has been detected, said electric machine (12) is controlled, if necessary, to deliver auxiliary power We in order to avoid a deficit appearing in the total power WT of said hybrid power plant (5), thereby enabling the pilot of said aircraft (1) to fly said aircraft (1) safely without degrading said hybrid power plant (5).

主权项

1. A method of managing an engine failure on a rotary wing aircraft, said aircraft comprising:
a hybrid power plant having at least two fuel-burning engines, at least one electric machine, a main gearbox “MGB”, and at least one electronic engine control unit “EECU”, each EECU being connected to a respective engine, each engine being capable of delivering at least a maximum continuous power MCP rating and OEI 30″, OEI 2′, and OEI Cont power ratings, said hybrid power plant delivering total driving power WT to said MGB; at least one electrical energy storage means; and at least one main rotor that is driven in flight at an instantaneous speed of rotation Nr by said hybrid power plant; the method being characterized by:
a checking step, in which the operation of each engine is checked during each flight by means of said EECU in order to detect a failure, if any, of at least one engine, an engine being considered as having failed when at least one other engine delivers said OEI power rating;a monitoring step during which a monitoring value is determined relating to at least one monitoring parameter of said aircraft and a detection threshold is determined for detecting a deficit in said total power WT, a comparison then being performed by comparing said monitoring value with said detection threshold in order to identify a risk of a deficit in said total power WT, said deficit in the total power WT appearing whenever at least one engine needs to deliver power greater than a predetermined power WP; anda control step, during which, when a failure of at least one engine is detected and said detection threshold is crossed, said electric machine is controlled to deliver auxiliary power We so that said total driving power WT from said hybrid power plant is sufficient to fly said aircraft safely, each engine that remains operational not delivering power greater than said predetermined power WP.