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公开(公告)号：US12071232B2
公开(公告)日：2024-08-27
申请号：US17786194
申请日：2020-12-17
申请人： LEONARDO S.P.A.
IPC分类号： B64C29/00 , B64C1/20 , B64C1/22 , B64C3/52 , B64C27/22 , B64D27/02 , B64D27/24 , B64D29/00 , B64D35/04 , B64D35/08 , H02K7/18
CPC分类号： B64C29/0033 , B64C1/20 , B64C1/22 , B64C3/52 , B64C27/22 , B64D27/24 , B64D29/00 , B64D35/04 , B64D35/08 , H02K7/1861 , B64D27/026
摘要： A convertiplane is described that comprises: a fuselage, having a first longitudinal axis and, in turn, comprising a nose and a tail portion; a pair of wings arranged on respective opposite sides of the fuselage, carrying respective rotors and generating a lift value; and a pair of engines operatively connected to respective rotors; each rotor comprising a mast rotatable about a second axis between a helicopter configuration and an aeroplane configuration; each rotor is interposed between the fuselage and the relative rotor along the direction of extension of the relative wing.
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49.发明授权公开(公告)号：US11958596B2
公开(公告)日：2024-04-16
申请号：US16748254
申请日：2020-01-21
申请人： MagLev Aero Inc.
发明人： Ian Morris Randall
IPC分类号： B64C29/02 , B64C13/26 , B64C13/50 , B64C27/00 , B64C27/10 , B64C27/14 , B64C27/20 , B64C27/32 , B64C27/473 , B64C27/68 , B64C27/72 , B64C29/00 , B64D27/24 , B64D35/02 , B64D35/04 , B64U10/13 , B64U50/19 , F01D5/02 , H02K1/17 , H02K1/18 , H02K1/2786 , H02K1/2791 , H02K1/2793 , H02K1/2795 , H02K1/28 , H02K11/21 , H02K16/00 , H02K21/22 , H02K21/24 , H02N15/00 , B64C27/80 , B64C39/02 , B64D35/06 , B64U30/20
CPC分类号： B64C29/0025 , B64C13/26 , B64C13/50 , B64C27/10 , B64C27/20 , B64C27/32 , B64C27/473 , B64C27/68 , B64C27/72 , B64C29/00 , B64C29/0016 , B64C29/02 , B64D27/24 , B64D35/02 , B64D35/04 , F01D5/02 , H02K1/17 , H02K1/187 , H02K1/2786 , H02K1/2791 , H02K1/2793 , H02K1/2795 , H02K1/28 , H02K11/21 , H02K16/00 , H02K21/22 , H02K21/24 , H02N15/00 , B64C2027/003 , B64C2027/004 , B64C27/14 , B64C27/80 , B64C39/024 , B64D35/06 , B64U10/13 , B64U30/20 , B64U50/19
摘要： Systems and methods relate to a vertical takeoff and landing (VTOL) platform that can include a stator and a rotor magnetically levitated by the stator. The rotor and stator can be annular, such that the rotor rotates about a rotational axis. The stator can include magnets that provide guidance, levitation, and drive forces to drive the rotor, as well as to control operation of rotor blades of the rotor that can be independently rotated to specific pitch angles to control at least one of lift, pitch, roll, or yaw of the VTOL platform. Various controllers can be used to enable independent and redundant control of components of the VTOL platform.
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公开(公告)号：US11920479B2
公开(公告)日：2024-03-05
申请号：US16535256
申请日：2019-08-08
IPC分类号： F01D13/02 , B64C27/12 , B64D27/10 , B64D35/04 , F01D15/12 , F01D17/16 , F02C6/02 , F02C6/20 , F02C7/36 , F02C9/56
CPC分类号： F01D13/02 , B64C27/12 , B64D27/10 , B64D35/04 , F01D15/12 , F01D17/162 , F02C6/02 , F02C6/20 , F02C7/36 , F02C9/56 , F05D2220/329 , F05D2240/12 , F05D2240/60 , F05D2260/4031
摘要： A method of operating a multi-engine system of a rotorcraft includes, during a cruise flight segment of the rotorcraft, controlling a first engine to provide sufficient power and/or rotor speed demands of the cruise flight segment; and controlling a second engine to by providing a fuel flow to the second engine that is between 70% and 99.5% less than a fuel flow provided to the first engine. A turboshaft engine for a multi-engine system configured to drive a common load is also described.
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