公开(公告)号：US20190210717A1

公开(公告)日：2019-07-11

申请号：US15864702

申请日：2018-01-08

申请人： Sikorsky Aircraft Corporation

发明人： Timothy F. Lauder

IPC分类号： B64C27/14 ,  B64C27/32 ,  B64C27/10 ,  B64D35/02 ,  H02K7/14

CPC分类号： B64C27/14 ,  B64C27/10 ,  B64C27/32 ,  B64D35/02 ,  H02K7/10 ,  H02K7/14 ,  H02K11/0094 ,  H02K16/04 ,  H02K21/24

摘要： A rotor system of an aircraft includes a rotor hub rotatable about an axis of rotation, and a power generation system. The power generation system includes a generator stator and a generator rotor. The generator rotor is coupled to the rotor hub. At least one induction type magnet is mounted to at least one of the generator stator and the generator rotor. A control unit is operably coupled to the at least one induction type magnet to selectively deliver power to the at least one induction type magnet to alter a torque of the rotor hub without decreasing a rotational speed of the rotor hub.

公开(公告)号：US20180339780A1

公开(公告)日：2018-11-29

申请号：US15605247

申请日：2017-05-25

申请人： General Electric Company

发明人： Dominic Barone ,  Paul Robert Gemin

IPC分类号： B64D27/24 ,  B64D27/10 ,  B64D27/16 ,  F02C3/04 ,  F01D15/10

CPC分类号： B64D27/24 ,  B64D27/10 ,  B64D27/16 ,  B64D35/02 ,  B64D2027/026 ,  B64D2221/00 ,  F01D15/10 ,  F02C3/04 ,  F05D2220/323 ,  Y02T50/64

摘要： A propulsion system for an aircraft includes an electric generator mechanically driven by a combustion engine, with the electric generator configured to generate alternating current electrical power. The propulsion system additionally includes a power bus electrically connected to the electric generator and configured to receive and transmit the alternating current electrical power generated by the electric generator. Additionally, the propulsion system includes, an electric propulsor assembly comprising an electric motor and a propulsor drivingly connected to the electric motor, the electric motor electrically coupled to the power bus for the receiving alternating current electrical power from the power bus.

公开(公告)号：US20180306121A1

公开(公告)日：2018-10-25

申请号：US15765450

申请日：2016-10-05

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Augustin Marc Michel Curlier

IPC分类号： F02C7/36 ,  F01D15/12 ,  F02C3/107 ,  F16H1/20

CPC分类号： F02C7/36 ,  B64D35/02 ,  F01D15/12 ,  F02C3/107 ,  F05D2250/312 ,  F05D2250/314 ,  F05D2260/40311 ,  F16H1/203 ,  Y02T50/671

摘要： The present invention relates to an aircraft propulsion assembly comprising a turbine (15), at least one fan (10) and a mechanism for transmitting power between the turbine and the fan, characterized in that the power transmission mechanism comprises a speed reducer (20) with a motion input and a motion output, the input being in the continuation of the axis (16) of the turbine and the output connected to the fan.

公开(公告)号：US20180050816A1

公开(公告)日：2018-02-22

申请号：US15239784

申请日：2016-08-17

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Ella YAKOBOV ,  James Robert JARVO

IPC分类号： B64D45/00 ,  B64C11/30 ,  B64D35/02

CPC分类号： B64D45/0005 ,  B64C11/30 ,  B64C11/301 ,  B64D35/02

摘要： An aircraft propeller control system for an aircraft propeller with adjustable blade angle has a blade angle feedback ring and a sensor, one of which is mounted for rotation with the propeller. The blade angle feedback ring moves longitudinally along with adjustment of the blade angle and has position markers circumferentially spaced apart at distances that vary along a longitudinal axis. The sensor is positioned adjacent the feedback ring for producing signals indicative of passage of the position markers. Intervals between signals are indicative of circumferential distances between position markers. A controller measures longitudinal position of the feedback ring based on the intervals and is configured to produce a warning signal if the longitudinal position is outside a first threshold range.

公开(公告)号：US09873518B2

公开(公告)日：2018-01-23

申请号：US14799845

申请日：2015-07-15

申请人： AIRBUS HELICOPTERS

发明人： Matthieu Sautreuil ,  Gilles Bezes

IPC分类号： B64D35/02 ,  B64D27/24 ,  B64D27/10 ,  B64D31/14 ,  B64D35/08 ,  B64D27/02

CPC分类号： B64D35/02 ,  B64D27/10 ,  B64D27/24 ,  B64D31/14 ,  B64D35/08 ,  B64D2027/026 ,  B64D2221/00 ,  Y02T50/64 ,  Y10S903/904

摘要： An electrical architecture for an aircraft having a main electrical machine connected to a fuel burning engine and a secondary electrical machine connected to a power transmission assembly. A high-voltage electrical master box is connected by a first line and by a second line to a multifunction converter, the high-voltage electrical master box connecting the first line to the secondary electrical machine, and the second line to at least the main electrical machine and the secondary electrical machine. The multifunction converter includes a supervisor connected to an avionics system and to a control system controlling the engine, and to a controller of the high-voltage electrical master box.

公开(公告)号：US20170327230A1

公开(公告)日：2017-11-16

申请号：US15432549

申请日：2017-02-14

申请人： Hood Technology Corporation

发明人： Andreas H. von Flotow ,  Corydon C. Roeseler ,  Daniel Pepin Reiss

IPC分类号： B64D5/00 ,  B64C27/08 ,  B64C39/02 ,  B64F1/02

CPC分类号： B64C27/48 ,  B64C25/08 ,  B64C27/001 ,  B64C27/08 ,  B64C27/26 ,  B64C27/32 ,  B64C39/024 ,  B64C2027/003 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/146 ,  B64C2201/182 ,  B64C2201/201 ,  B64D1/00 ,  B64D1/02 ,  B64D1/12 ,  B64D3/00 ,  B64D5/00 ,  B64D35/02 ,  B64F1/02 ,  B65D25/10 ,  B65D85/68 ,  B65D2585/687

摘要： The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.

公开(公告)号：US20170327211A1

公开(公告)日：2017-11-16

申请号：US15431172

申请日：2017-02-13

申请人： Hood Technology Corporation

发明人： Corydon C. Roeseler ,  Caleb Andrew Woodruff ,  Daniel Pepin Reiss

IPC分类号： B64C27/26 ,  B64D35/02 ,  B64C27/48

CPC分类号： B64C27/48 ,  B64C25/08 ,  B64C27/001 ,  B64C27/08 ,  B64C27/26 ,  B64C27/32 ,  B64C39/024 ,  B64C2027/003 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/146 ,  B64C2201/182 ,  B64C2201/201 ,  B64D1/00 ,  B64D1/02 ,  B64D1/12 ,  B64D3/00 ,  B64D5/00 ,  B64D35/02 ,  B64F1/02 ,  B65D25/10 ,  B65D85/68 ,  B65D2585/687

摘要： The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.

公开(公告)号：US20170082066A1

公开(公告)日：2017-03-23

申请号：US15273183

申请日：2016-09-22

申请人： Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

发明人： Michael J. Armstrong ,  Igor Vaisman

IPC分类号： F02K5/00

CPC分类号： F02K5/00 ,  B64D35/02 ,  B64D35/04 ,  F01K23/10 ,  F01K25/103 ,  F02C1/105 ,  F02C6/18 ,  F02C6/206 ,  F02K3/06 ,  F02K3/077 ,  F02K3/12 ,  F05D2210/12 ,  F05D2210/13 ,  F05D2240/40 ,  F05D2250/311 ,  F05D2260/213 ,  Y02T50/675

摘要： A power and propulsion system includes an air compressor, a combustor positioned to receive compressed air from the air compressor as a core stream, and a closed-loop system having carbon dioxide as a working fluid that receives heat from the combustor and rejects heat to a cooling stream. The closed-loop system configured to provide power to a fan that provides the cooling stream, and to one or more distributed propulsors that provide thrust to an aircraft.

公开(公告)号：US09541142B2

公开(公告)日：2017-01-10

申请号：US14482603

申请日：2014-09-10

申请人： Bell Helicopter Textron Inc.

发明人： Pasquale Spina ,  Carlos A Fenny ,  Jean-Sebastian Plante ,  Patrick Chouinard ,  Jean-Philippe Lucking Bigué ,  Yves St-Amant

IPC分类号： F16D37/00 ,  B64C27/56 ,  B64C27/64 ,  B64C27/68 ,  B64C27/12 ,  B64C27/78 ,  B64D35/02 ,  F16D37/02 ,  B64C13/28 ,  B64C27/605 ,  B64C27/08 ,  B64D35/04 ,  F16H25/20

CPC分类号： F16D37/008 ,  B64C13/28 ,  B64C27/08 ,  B64C27/12 ,  B64C27/56 ,  B64C27/605 ,  B64C27/64 ,  B64C27/68 ,  B64C27/78 ,  B64D31/14 ,  B64D35/02 ,  B64D35/04 ,  F16D27/14 ,  F16D37/02 ,  F16D2037/001 ,  F16D2037/007 ,  F16H25/20 ,  F16H2025/2059 ,  Y02T50/44 ,  Y10T74/18704

摘要： In some embodiments, a redundant control system includes first and second control systems, having first and second clutches, and a shared clutch system. The shared clutch system may include a shared shaft configured to receive mechanical energy from a shared power source, a first shared clutch corresponding to the first clutch and configured to receive mechanical energy from the shared shaft, and a second shared clutch corresponding to the second clutch and configured to receive mechanical energy from the shared shaft. A first linkage provides mechanical communication between an output of the first clutch, an output of the first shared clutch, and a first output device in mechanical communication with the rotor system. A second linkage provides mechanical communication between an output of the second clutch, an output of the second shared clutch, and a second output device in mechanical communication with the rotor system.

摘要翻译： 在一些实施例中，冗余控制系统包括具有第一和第二离合器以及共享离合器系统的第一和第二控制系统。 共享离合器系统可以包括被配置为从共享电源接收机械能的共享轴，对应于第一离合器并被配置为从共享轴接收机械能的第一共享离合器和对应于第二离合器的第二共享离合器 并且构造成从共享轴接收机械能。 第一联动装置提供第一离合器的输出，第一共享离合器的输出和与转子系统机械连通的第一输出装置之间的机械连通。 第二联动装置提供第二离合器的输出，第二共享离合器的输出和与转子系统机械连通的第二输出装置之间的机械连通。

公开(公告)号：US20160340051A1

公开(公告)日：2016-11-24

申请号：US15136074

申请日：2016-04-22

申请人： ROLLS-ROYCE PLC

发明人： Huw L. EDWARDS ,  Alexander C. SMITH ,  Judith M. APSLEY ,  Charalampos MANOLOPOULOS

IPC分类号： B64D27/02 ,  B64D35/02 ,  B64C11/30

CPC分类号： B64D27/02 ,  B64D27/24 ,  B64D35/02 ,  B64D2027/026 ,  B64D2221/00 ,  Y02T50/44 ,  Y02T50/64

摘要： An electrical network for an aircraft. The aircraft includes at least one variable pitch propulsor. The electrical network includes a wound field synchronous AC electrical generator having a wound rotor driven by an internal combustion engine. The network further includes a voltage regulator configured to regulate output voltage of the electrical generator by regulating rotor winding magnetic field strength, and a synchronous AC drive motor coupled to a respective variable pitch propulsor and provided with power from the output of the electrical generator.

摘要翻译： 飞机电气网络。 飞行器包括至少一个可变俯仰推进器。 电网包括具有由内燃机驱动的绕线转子的绕线场同步交流发电机。 网络还包括电压调节器，其被配置为通过调节转子绕组磁场强度来调节发电机的输出电压，以及耦合到相应的可变间距推进器并且从发电机的输出端提供电力的同步AC驱动电动机。