公开(公告)号：US20180346139A1

公开(公告)日：2018-12-06

申请号：US15984638

申请日：2018-05-21

Applicant: Airbus SAS

Inventor： Benoit FERRAN ,  Emmanuel JOUBERT ,  Nicolas Fouquet ,  Jonathan LANDOLT

IPC: B64D31/06 ,  B64D27/24 ,  G10K15/00

CPC classification number: B64D27/24 ,  B64D2027/026

Abstract: A method and an architecture for implementing the method for the management of a hybrid thermal/electrical propulsion aircraft in the course of its various flight phases. The hybrid propulsion receives at each instant i a total power command Ptot,com,i distributed between thermal Pth,com,i and electrical Pe,com,i power commands. The method includes steps of calculating a maximum admissible thermal power command Pth,com,max,i for compliance with acoustic objectives on the ground, selecting the thermal power command Pth,com,i in a bounded range of values, determining the electrical power command Pe,com,i. The thermal Pth,com,i and electrical Pe,com,i power commands supplied by the hybrid propulsion are thus adjusted in the course of the different flight phases depending on a height hi of the aircraft in order to make it possible to comply with acoustic requirements on the ground.