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公开(公告)号：US10421530B2
公开(公告)日：2019-09-24
申请号：US15735554
申请日：2016-06-17
摘要： A device for controlling a propeller, having variable-pitch blades, of a turboprop engine, has a first hydromechanical device for controlling the pitch of the blades of the propeller and a second hydromechanical device for controlling the speed of rotation of the propeller. The device includes a single electromechanical actuator with a movable actuator member mechanically connected both to the first hydromechanical device for controlling the pitch, in order to manage the pitch setpoint, and to the second hydromechanical device for controlling the speed, in order to manage the speed setpoint.
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2.发明申请公开(公告)号：US20180354608A1
公开(公告)日：2018-12-13
申请号：US15735554
申请日：2016-06-17
摘要： A device for controlling a propeller, having variable-pitch blades, of a turboprop engine, has a first hydromechanical device for controlling the pitch of the blades of the propeller and a second hydromechanical device for controlling the speed of rotation of the propeller. The device includes a single electromechanical actuator with a movable actuator member mechanically connected both to the first hydromechanical device for controlling the pitch, in order to manage the pitch setpoint, and to the second hydromechanical device for controlling the speed, in order to manage the speed setpoint.
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公开(公告)号：US10807724B2
公开(公告)日：2020-10-20
申请号：US16337998
申请日：2017-10-02
发明人： Thomas Klonowski , Olivier Lafargue , Antoine Moutaux , Jean-Julien Camille Vonfelt , Bertrand Nogarede
IPC分类号： B64D15/12 , H02K16/02 , H02K21/48 , B64D27/24 , H01L35/32 , H02K7/18 , H02K7/20 , B64D27/02 , F04D25/06
摘要： The electrical machine according to the invention is a dual machine, and comprises a first machine which can be reversed and a second machine functioning through induction between two windings. The second machine can be used for de-icing a propeller, the induction-receiving winding being mounted on the propeller shaft. The first electrical machine can function as an electrical engine to ‘taxi’ the aircraft. In certain embodiments, the winding mounted on the stator is common to the two machines and different magnetic flows are utilised to control them. A separate functioning of the two machines and a very good integration into the aircraft engine, with space-saving and low mass, are possible.
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公开(公告)号：US10731504B2
公开(公告)日：2020-08-04
申请号：US16330138
申请日：2017-08-24
摘要： An electric actuator for inlet guide vanes of a gas turbine engine, the electric actuator including a fixed portion secured to a stationary portion of the engine and a movable portion that is mechanically connected to the inlet guide vanes, stationary electromagnets distributed at regular intervals around the periphery of the movable portion and fastened to the fixed portion, and movable electromagnets arranged between the stationary electromagnets, each movable electromagnet being secured on either side to first and second piezoelectric elements, the movable electromagnets and the first and second piezoelectric elements having a degree of freedom of movement relative to the movable portion and having inside faces forming a common line of contact that is tangential to the movable portion.
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公开(公告)号：US10023303B2
公开(公告)日：2018-07-17
申请号：US15365144
申请日：2016-11-30
发明人： Antoine Moutaux , Florent Nierlich
摘要： An actuating system for an aircraft having an electromechanical actuator (25) comprising a non-volatile memory (60) wherein stored data (61) including configuration data (62) specific to the electromechanical actuator is stored. The system also includes a control unit (22) using the configuration data to implement a servo-control loop, the output signal of which is a digital signal controlling the electric motor of the electromechanical actuator and at least one digital transmission channel (50) connecting the control unit and the electromechanical actuator.
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