公开(公告)号：US20180265188A1

公开(公告)日：2018-09-20

申请号：US15922391

申请日：2018-03-15

Applicant: AIRBUS HELICOPTERS

Inventor： Olivier HONNORAT ,  Francois MALBURET

IPC: B64C27/00

CPC classification number: B64C27/001 ,  B64C2027/002 ,  B64C2027/004 ,  B64C2027/005 ,  F16F7/1011 ,  F16F15/14

Abstract: A rotorcraft having an antivibration system, the antivibration system being arranged at the interface between a fuselage of the rotorcraft and a casing of a main power transmission gearbox, or “MGB”, in order to transmit rotary motion generated by an engine of the rotorcraft to a main rotor providing the rotorcraft at least with lift, and possibly also propulsion, the antivibration system including calculation means for analyzing as a function of time the dynamic excitation and the resulting vibration transmitted to the fuselage of the rotorcraft.

公开(公告)号：US20220135239A1

公开(公告)日：2022-05-05

申请号：US17517858

申请日：2021-11-03

Applicant: AIRBUS HELICOPTERS

Inventor： Luca COSSETTI ,  Francois MALBURET

IPC: B64D31/00 ,  B64D27/10 ,  B64D27/24 ,  B64D37/00 ,  B64C27/00 ,  F02C7/22

Abstract: A method for controlling at least a first turboshaft engine and a second turboshaft engine of a rotorcraft, which set a common kinematic linkage in motion, the rotorcraft having an output electric machine cooperating with a first output kinematic linkage of the first turboshaft engine, the rotorcraft having an input electric machine cooperating with a gas generator of the second turboshaft engine. The method includes the following steps: supplying fuel to the first turboshaft engine, operating the output electric machine in electrical energy generator mode, supplying fuel to the second turboshaft engine, and operating the input electric machine in motor mode in order to supply a second non-zero power to said common kinematic linkage.

公开(公告)号：US20210371095A1

公开(公告)日：2021-12-02

申请号：US17328896

申请日：2021-05-24

Applicant: AIRBUS HELICOPTERS

Inventor： Alexandre MADEIRA ,  Francois MALBURET ,  Lionel ROUCOULES

IPC: B64C27/467 ,  B64C27/473

Abstract: A blade in which the aerodynamic profiles of a blade root, a blade neck and a central part of a profiled zone of the blade respectively comprise a leading edge section and a trailing edge section that are symmetrical to each other relative to an axis of symmetry. The present disclosure also concerns a method for constructing such a blade. The axis of symmetry is perpendicular to a segment connecting the leading edge to the trailing edge of each profile and is positioned in the middle of the segment. An intermediate upper surface section and an intermediate lower surface section connect the leading edge section and the trailing edge section in order to respectively form a lower surface of the aerodynamic profile.