公开(公告)号：US12098644B2

公开(公告)日：2024-09-24

申请号：US18056032

申请日：2022-11-16

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Keith Morgan ,  Eric Durocher

IPC分类号： F02C3/08 ,  B64C27/12 ,  B64D27/10 ,  B64D35/04 ,  F01D13/02 ,  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 turboshaft engine for a rotorcraft includes a first spool and an independently rotatable second spool. The first spool includes a low pressure compressor, a first set of variable guide vanes disposed at an entry of the low pressure compressor, and a low pressure turbine drivingly engaged to the low pressure compressor. The second spool includes a high pressure compressor, a second set of variable guide vanes disposed at an entry of the high pressure compressor, the second set of variable guide vanes independently operable relative to the first set of variable guide vanes, and a high pressure turbine drivingly engaged to the high pressure compressor. One or both of the low pressure compressor and the high pressure compressor includes a mixed flow rotor.

公开(公告)号：US11958619B2

公开(公告)日：2024-04-16

申请号：US16485846

申请日：2018-02-27

申请人： RPS AEROSPACE s.r.l.

发明人： Giacomo Lunerti ,  Nausicaa Asia Vezzoli ,  Andrea Berna

IPC分类号： B64D17/72 ,  B64C39/02 ,  B64D17/02 ,  B64D17/26 ,  B64D17/34 ,  B64D25/00 ,  B64D27/24 ,  B64U10/13 ,  B64U70/83 ,  B64D35/02 ,  B64D35/04 ,  B64U50/19

CPC分类号： B64D17/72 ,  B64C39/024 ,  B64D17/02 ,  B64D17/26 ,  B64D17/34 ,  B64D25/00 ,  B64D27/24 ,  B64D35/02 ,  B64D35/04 ,  B64D2201/00 ,  B64U10/13 ,  B64U50/19 ,  B64U70/83

摘要： A remote piloted aircraft comprising a secondary flight assembly adapted to intervene in case of failure or an emergency of the aircraft, said secondary flight assembly being provided with an additional control unit configured to process flight relevant data and which includes an additional receiver configured to receive commands from the remote pilot by means of a remote control unit, in case of failure or emergency said additional control unit being configured to generate, as a response, an activation command adapted to activate a first device to expel an upper wing placed in a first compartment of the aircraft and to inflate a lower wing housed in a second compartment of the aircraft, and also to generate an interdiction command of the primary propulsion unit, said upper wing being maneuverable by means of a further remote control unit.

公开(公告)号：US11939047B2

公开(公告)日：2024-03-26

申请号：US17746591

申请日：2022-05-17

申请人： AIRBUS HELICOPTERS

发明人： Kamel Abdelli

IPC分类号： B64C27/57 ,  B64C27/26 ,  B64D31/12 ,  B64D35/04

CPC分类号： B64C27/57 ,  B64C27/26 ,  B64D31/12 ,  B64D35/04

摘要： A method and a device for assisting the piloting of a propeller rotorcraft having a rotary wing and at least one propeller. The piloting assistance device comprises a computer configured to display the following on a display: (i) a first scale representing a power consumed by the at least one propeller and carrying a minimum power mark and a maximum power mark, (ii) a second scale graduated in forward speed of the propeller rotorcraft, (iii) an index comprising a power section representing a current power consumed by the at least one propeller, the index comprising a speed section indicating a current forward speed on the second scale.

公开(公告)号：US20240025542A1

公开(公告)日：2024-01-25

申请号：US18480338

申请日：2023-10-03

申请人： Textron Innovations Inc.

发明人： Jonathan Andrew Knoll ,  George Matthew Thompson ,  Charles Hubert Speller ,  Grant Michael Beall

IPC分类号： B64C29/00 ,  B64D27/24 ,  B64D29/02 ,  B64D35/02 ,  B64D35/04 ,  H02K7/108 ,  H02K7/116

CPC分类号： B64C29/0033 ,  B64D27/24 ,  B64D29/02 ,  B64D35/02 ,  B64D35/04 ,  H02K7/108 ,  H02K7/116 ,  F16D41/00

摘要： A rotor system for an aircraft includes an open rotor assembly comprising a plurality of rotor blades connected to a rotor mast via a yoke, wherein the rotor assembly is tiltable between a first position corresponding to an airplane mode and a second position corresponding to a helicopter mode; and a drive system for providing rotational energy to the open rotor assembly via the rotor mast, the drive system comprising at least one electric motor for providing rotational energy to a drive shaft and a gearbox connected to the drive shaft for receiving rotational energy from the at least one electric motor via the drive shaft and providing rotational energy to the rotor mast via a rotor shaft; wherein the drive system is rotatable relative to the wing about a tilt axis and the rotor shaft is coaxial with the drive shaft.

公开(公告)号：US11688723B1

公开(公告)日：2023-06-27

申请号：US17900046

申请日：2022-08-31

申请人： Rolls-Royce Deutschland Ltd & Co KG

发明人： Uwe Waltrich ,  Stanley Buchert

IPC分类号： H01L25/16 ,  H02M7/217 ,  H01L23/31 ,  H01L23/538 ,  B64D27/24 ,  B64D35/04 ,  B60L58/00 ,  B64C29/00 ,  B64D27/02

CPC分类号： H01L25/16 ,  B60L58/00 ,  B64C29/0008 ,  B64D27/24 ,  B64D35/04 ,  H01L23/3121 ,  H01L23/5383 ,  H01L23/5386 ,  H02M7/217 ,  B60L2200/10 ,  B60L2210/30 ,  B64D2027/026

摘要： An electrical vertical take-off and landing (eVTOL) aircraft includes a plurality of electrical propulsion units (EPUs), each EPU having a propeller or a fan configured to be driven to rotate by an electrical motor arranged to receive electrical power from a respective power electronics converter. Each power electronics converter includes a converter commutation cell having a power circuit and a gate driver circuit, the power circuit including at least one power semiconductor switching element and at least one capacitor. At least one terminal of each power conducting switching element is connected to at least one electrically conductive layer of a multi-layer planar carrier substrate at an electrical connection side of a power semiconductor prepackage, which includes at least one electrically conductive layer located on an opposite side of the power semiconductor switching element to the electrical connection side of the power semiconductor prepackage.

公开(公告)号：US20230159159A1

公开(公告)日：2023-05-25

申请号：US18089978

申请日：2022-12-28

申请人： Maglev Aero Inc.

发明人： Ian Morris Randall

IPC分类号： B64C29/00 ,  B64C27/20 ,  H02K21/22 ,  B64C27/32 ,  H02K1/18 ,  H02K1/2786 ,  H02K11/21 ,  B64C27/473 ,  H02K21/24 ,  H02N15/00 ,  B64C13/26 ,  F01D5/02 ,  B64C27/10 ,  B64C27/72 ,  B64D27/24 ,  B64D35/02 ,  B64D35/04 ,  H02K1/17 ,  H02K1/2793 ,  H02K1/28 ,  H02K16/00 ,  B64C27/68 ,  B64C29/02 ,  B64C13/50 ,  B64C27/00

CPC分类号： B64C29/0025 ,  B64C27/20 ,  B64C29/00 ,  H02K21/22 ,  B64C27/32 ,  H02K1/187 ,  H02K1/2786 ,  H02K11/21 ,  B64C27/473 ,  H02K21/24 ,  H02N15/00 ,  B64C13/26 ,  B64C29/0016 ,  F01D5/02 ,  B64C27/10 ,  B64C27/72 ,  B64D27/24 ,  B64D35/02 ,  B64D35/04 ,  H02K1/17 ,  H02K1/2793 ,  H02K1/28 ,  H02K16/00 ,  B64C27/68 ,  B64C29/02 ,  B64C13/50 ,  B64C27/001 ,  B64C27/14

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.

公开(公告)号：US20230144699A1

公开(公告)日：2023-05-11

申请号：US17916753

申请日：2021-04-03

申请人： Boris KIPNIS

发明人： Boris KIPNIS

IPC分类号： B60F5/02 ,  B64C37/00 ,  B64C29/00 ,  B64C11/28 ,  B64D35/04 ,  B64D17/80 ,  B64D27/24 ,  B60L50/60 ,  B60L53/00 ,  H01M10/46

CPC分类号： B60F5/02 ,  B64C37/00 ,  B64C29/0025 ,  B64C11/28 ,  B64D35/04 ,  B64D17/80 ,  B64D27/24 ,  B60L50/60 ,  B60L53/00 ,  H01M10/46 ,  B64D2027/026

摘要： A roadable VTOL flying vehicle having a road-configuration and a flight-configuration. The roadable VTOL flying vehicle includes a roadable vehicle; at least one rotor having at least one blade, the rotor is rotatably attached to an upper section of the roadable vehicle of the flying vehicle; at least one motor configured to operatively rotate the least at least one rotor; at least one angular position sensor configured to detect the angular position of each of the at least one rotor; and a vehicle control sub-system configured to affect automatic transformation of the flying vehicle from the road-configuration to the flight-configuration and from the flight-configuration to the road-configuration, wherein the vehicle control sub-system is configured bring the at least one rotor into a parking state, when in road-configuration.

公开(公告)号：US20180244396A1

公开(公告)日：2018-08-30

申请号：US15758056

申请日：2016-08-25

申请人： Sikorsky Aircraft Corporation

发明人： Mark R. Alber

IPC分类号： B64D35/08 ,  B64C27/14 ,  B64C27/82 ,  B64D35/02 ,  F02C6/20

CPC分类号： B64D35/08 ,  B64C27/14 ,  B64C27/82 ,  B64C2027/8236 ,  B64D35/02 ,  B64D35/04 ,  F02C6/20 ,  F05D2220/329

摘要： A drive system for a rotorcraft includes at least one engine, the engine including a compressor section, and a turbine section positioned rearward from the compressor section. A main rotor input shaft extends from a rotor power turbine of the turbine section and is connectable to a main rotor assembly of the rotorcraft to transfer rotational energy from the rotor power turbine to the main rotor assembly. An auxiliary input shaft extends from an auxiliary power turbine of the turbine section and is connectible to an auxiliary rotor assembly of the rotorcraft to transfer rotational energy from the auxiliary power turbine to the auxiliary rotor assembly.

公开(公告)号：US20180237147A1

公开(公告)日：2018-08-23

申请号：US15439988

申请日：2017-02-23

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： Gabriel L. Suciu ,  Jesse M. Chandler

IPC分类号： B64D27/26 ,  B64D27/20 ,  B64D35/04

CPC分类号： B64D27/26 ,  B64D27/20 ,  B64D35/04 ,  B64D2027/268

摘要： A propulsor and mount arrangement comprises a propulsor rotor and a fan casing surrounding the propulsor rotor. The fan casing receives two side mounts and a thrust link pivotally attached to the fan casing at a location that will be within 10° of a vertically lowermost location when the propulsor is mounted on an aircraft, and the side mounts being at circumferentially opposed positions, and within a lower 270° when the propulsor is mounted on an aircraft. At least a portion of both the side mounts, and a pivot point connect the thrust link to the fan casing in a common plane defined perpendicular to a rotational axis of the propulsor rotor. An aircraft is also disclosed.

公开(公告)号：US09975644B1

公开(公告)日：2018-05-22

申请号：US14976845

申请日：2015-12-21

申请人： Amazon Technologies, Inc.

发明人： Gur Kimchi ,  Dominic Timothy Shiosaki ,  Ricky Dean Welsh

IPC分类号： G01C23/00 ,  B64D35/04 ,  B64D35/02 ,  B64C39/02 ,  B64D27/24

CPC分类号： B64D35/04 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/141 ,  B64D27/24 ,  B64D35/02

摘要： An aerial vehicle may be equipped with propulsion modules that include motors, sensors, transceivers, controllers, power sources or other components therein. The propulsion modules may be releasably mounted to the aerial vehicle in a manner that allows a propulsion module to be removed and replaced when one or more of the components within the propulsion module requires maintenance or repairs, thereby enabling the aerial vehicle to return to service promptly. The propulsion modules may communicate via wired or wireless means with one another, or with a central computer system onboard the aerial vehicle. The propulsion modules may be interchangeably installed on each of the aerial vehicles in a class, or on aerial vehicles in different classes. Furthermore, aerial vehicles may be equipped with varying numbers of propulsion modules, as needed, subject to one or more operational requirements or constraints.