公开(公告)号：EP3374262A1

公开(公告)日：2018-09-19

申请号：EP16864758.4

申请日：2016-10-25

申请人： Sikorsky Aircraft Corporation

发明人： THOMAS, Justin ,  KOPANSKI, Krzysztof ,  SCOTT, Mark, W.

IPC分类号： B64C27/72 ,  B64C27/46 ,  B64C27/473 ,  B64C27/54 ,  B64C27/59 ,  B64C27/64

CPC分类号： B64C27/72 ,  B64C27/473 ,  B64C27/54 ,  B64C27/64 ,  B64C2027/7272 ,  Y02T50/34

摘要： A closeout structure for a rotor blade includes a first fluid channel for supplying a first pressure to a first port of a trailing edge (TE) device, a second fluid channel for supplying a second pressure to a second port of the TE de vice, and a trough disposed between the first fluid channel and the second fluid channel. The closeout structure forms a double-W shape.

公开(公告)号：EP3028943A1

公开(公告)日：2016-06-08

申请号：EP15197659.4

申请日：2015-12-02

申请人： Bell Helicopter Textron Inc.

发明人： SCHANK, Troy

IPC分类号： B64C27/72

CPC分类号： B64C27/64 ,  B64C27/57 ,  B64C27/72 ,  B64C2027/7211 ,  B64C2027/7216 ,  Y02T50/34

摘要： One example of a rotorcraft blade control system includes a mechanical linkage (117a,b) to connect to a rotorcraft blade (104) including a feather axis (150) and a pneumatic muscle (107a,b) connected to the mechanical linkage (117a,b). The system also includes a movement member connected to the mechanical linkage (117a,b), the pneumatic muscle (107a,b) and the movement member to move the mechanical linkage (117a,b) to control movement of the rotorcraft blade (104) on the feather axis (150). The pneumatic muscle (107a,b) can be a first pneumatic muscle and the movement member can be a second pneumatic muscle or a bias spring.

公开(公告)号：EP3403923A1

公开(公告)日：2018-11-21

申请号：EP18173037.5

申请日：2018-05-17

申请人： Pratt & Whitney Canada Corp.

发明人： PEDRAMI, Reza ,  JARVO, James

IPC分类号： B64C11/38 ,  B64C27/64 ,  B64C11/40

CPC分类号： B64C11/385 ,  B64C11/40 ,  B64C27/64 ,  B64D27/10

摘要： A system (100) and method (500) for controlling an aircraft propeller (30) are provided. In anticipation of a condition in which a parameter related to an angle of a plurality of blades of the propeller (30) reaches a value beyond a predetermined threshold, a first control signal is output comprising instructions to actuate a feather valve (102) operatively coupled to an actuator (103) configured to adjust the angle in response to hydraulic pressure, thereby causing the feather valve (102) to provide the hydraulic pressure to the actuator (103) and the angle to be adjusted for bringing the parameter towards the threshold. When the parameter reaches the predetermined threshold, a second control signal is output comprising instructions to hold the feather valve (102) at a position in which the hydraulic pressure is withheld from the actuator (103), thereby causing the angle to remain unchanged.

公开(公告)号：EP2543589B1

公开(公告)日：2018-09-05

申请号：EP11290312.5

申请日：2011-07-06

申请人： Airbus Helicopters ,  AIRBUS HELICOPTERS DEUTSCHLAND GmbH

发明人： Grohmann, Boris ,  Chaduc, Bruno ,  Tempier, Christophe

IPC分类号： B64C13/50 ,  B64C27/64 ,  B64C27/68

CPC分类号： B64C27/625 ,  B64C13/503 ,  B64C27/64 ,  B64C27/68 ,  Y02T50/44

摘要： The present invention relates to primary flight controls (10) for main and/or tail rotors (4) of helicopters with an electro-mechanical interface between any of Fly-By-Wire and/or of Fly-by-light controls and hydraulic servo actuators (8) for control force amplification towards said main and/or tail rotor controls (4). For each of the main and/or tail rotor controls (4) there is provided but one of the hydraulic servo actuators (8), connected by one mechanical linkage (7) to one electro motor (5), said one hydraulic servo actuator (8) being of the type having the one mechanical linkage (7) connected to its input (29) and its output (30) and the one electro motor (5) being of the direct drive type, the position of said electro motor (5) having a reference to said one mechanical linkage (7) and the torque delivered by said electro motor (5) to the hydraulic servo actuator (8) being related to the power consumption of said electro motor (5).

公开(公告)号：EP3028943B1

公开(公告)日：2017-04-12

申请号：EP15197659.4

申请日：2015-12-02

申请人： Bell Helicopter Textron Inc.

发明人： SCHANK, Troy

IPC分类号： B64C27/57 ,  B64C27/64 ,  B64C27/72

CPC分类号： B64C27/64 ,  B64C27/57 ,  B64C27/72 ,  B64C2027/7211 ,  B64C2027/7216 ,  Y02T50/34

摘要： One example of a rotorcraft blade control system includes a mechanical linkage (117a,b) to connect to a rotorcraft blade (104) including a feather axis (150) and a pneumatic muscle (107a,b) connected to the mechanical linkage (117a,b). The system also includes a movement member connected to the mechanical linkage (117a,b), the pneumatic muscle (107a,b) and the movement member to move the mechanical linkage (117a,b) to control movement of the rotorcraft blade (104) on the feather axis (150). The pneumatic muscle (107a,b) can be a first pneumatic muscle and the movement member can be a second pneumatic muscle or a bias spring.

摘要翻译： 旋翼飞机叶片控制系统的一个例子包括连接到旋翼飞机叶片（104）的机械联动装置（117a，b），所述旋翼飞机叶片包括羽毛轴线（150）和连接到机械连杆机构（117a， b）。 该系统还包括连接到机械联动装置（117a，b）的运动构件，气动肌肉（107a，b）和移动构件，用于移动机械联动装置（117a，b）以控制旋翼飞轮叶片（104）的运动， 在羽轴（150）上。 气动肌肉（107a，b）可以是第一气动肌肉，运动部件可以是第二气动肌肉或偏压弹簧。

公开(公告)号：EP2806173B1

公开(公告)日：2017-03-01

申请号：EP14169043.8

申请日：2014-05-20

申请人： Hamilton Sundstrand Corporation

发明人： WAKEFIELD, David L. ,  NOREM, Dean A.

IPC分类号： F15B13/04

CPC分类号： F16K11/02 ,  B64C11/38 ,  B64C13/40 ,  B64C27/64 ,  F15B13/01 ,  F15B20/004 ,  Y10T137/0324 ,  Y10T137/86582

公开(公告)号：EP3069990B1

公开(公告)日：2017-01-11

申请号：EP15400013.7

申请日：2015-03-20

申请人： AIRBUS HELICOPTERS DEUTSCHLAND GmbH

发明人： Grohmann, Boris ,  Rohr, Thomas ,  Klaubert, Jens

IPC分类号： B64C13/46

CPC分类号： B64C13/46 ,  B64C13/08 ,  B64C13/22 ,  B64C27/04 ,  B64C27/605 ,  B64C27/64 ,  Y02T50/44

公开(公告)号：EP3063063A1

公开(公告)日：2016-09-07

申请号：EP14796985.1

申请日：2014-10-31

申请人： LORD Corporation

发明人： JOLLY, Mark R. ,  HALILOVIC, Haris ,  MILLER, Lane

IPC分类号： B64C27/08 ,  B64C27/51

CPC分类号： B64C27/001 ,  B64C27/51 ,  B64C27/605 ,  B64C27/615 ,  B64C27/64 ,  B64C2027/003 ,  B64C2027/7266 ,  Y02T50/34

摘要： Vibration control systems, devices, and methods are provided for a rotary wing aircraft having a rotor including a plurality of blades (20) each attached to a hub (10) at its root end and capable of pitching with respect to the hub (10). The systems, devices, and methods include a blade pitch adjuster (100) that is passively adjustable in response to aerodynamic loading on the plurality of blades (20) to adjust a pitch of one of the plurality of blades (20) with respect to the hub (10) based on a frequency of the aerodynamic loading. The blade pitch adjusters (100) can be configured to exhibit relatively high stiffness at the rotor rotating frequency and tailored dynamics at frequencies higher than the rotor rotating frequency such that hub loads at one or more higher harmonics are reduced.

公开(公告)号：EP2821343B1

公开(公告)日：2015-09-30

申请号：EP13195175.8

申请日：2013-11-29

申请人： Bell Helicopter Textron Inc.

发明人： McCollough, James M. ,  Fenny, Carlos A.

IPC分类号： B64C27/82 ,  B64C27/78 ,  B64C27/54

CPC分类号： B64C27/78 ,  B64C27/54 ,  B64C27/64 ,  B64C27/82

摘要： According to some embodiments, a rotorcraft (100) includes a secondary rotor control system (400b) located proximate to the empennage (150) of the rotorcraft (100). The secondary rotor control system (400b) includes at least one hydraulic pump (410b) and at least one hydraulic actuator (430). The at least one hydraulic pump is located proximate to the empennage (150). The at least one hydraulic actuator (430) is located proximate to the empennage (150) and configured to adjust at least one operating characteristic of the at least one secondary rotor blade (120').

公开(公告)号：EP2812245A2

公开(公告)日：2014-12-17

申请号：EP13790956.0

申请日：2013-02-09

申请人： Merlin Technology Inc.

发明人： ALBION, Nicolas ,  FEIFEL, Marc ,  MARVIN, Mark ,  MERCER, John

IPC分类号： B64C27/04 ,  G05D1/00

CPC分类号： B64C27/57 ,  B64C13/18 ,  B64C13/42 ,  B64C27/56 ,  B64C27/59 ,  B64C27/64 ,  B64C27/68 ,  G05D1/0077 ,  G05D1/0816 ,  G05D1/0858 ,  G05D1/102 ,  Y02T50/44

摘要： An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for corotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override.

摘要翻译： 直升机自动驾驶系统包括用于直升机飞行的姿态保持的内循环，包括施加到内循环的给定水平的冗余。 外部环路被配置为提供关于直升机的飞行的导航功能，其包括与内部循环不同的冗余级别。 致动器在联动装置上提供制动力，用于在停电期间稳定直升机的飞行。 致动器是机电的并且接收电驱动信号以提供直升机的自动飞行控制，而不需要直升机中的液压辅助系统。 自动驾驶仪可以在液压辅助系统的故障模式下操作直升机。 使用相关的传感器输入描述多个飞行模式，包括基于速率和真实姿态模式。