公开(公告)号：US20190329881A1

公开(公告)日：2019-10-31

申请号：US16394195

申请日：2019-04-25

申请人： AIRBUS HELICOPTERS

发明人： Jacques GAFFIERO ,  Christophe SERR ,  Jean-Romain BIHEL

IPC分类号： B64C29/00 ,  B64C27/08 ,  B64C27/52

摘要： A rotorcraft comprising a fuselage, a single main rotor, and a first propeller and a second propeller. The rotorcraft has an adjustment system configured, at least during a stage of hovering flight, to position the first propeller in a first low speed configuration in order to exert a first thrust including a first horizontal component and a first vertical component, the adjustment system being configured, at least during the stage of hovering flight, to position the second propeller in a second low speed configuration so as to exert a second thrust comprising a second horizontal component and a second vertical component.

公开(公告)号：US20190178266A1

公开(公告)日：2019-06-13

申请号：US15834550

申请日：2017-12-07

申请人： AIRBUS HELICOPTERS

发明人： Clement COIEC ,  Jean-Romain BIHEL ,  Arnaud GROLL

IPC分类号： F15B20/00 ,  B64C27/605 ,  F15B7/08 ,  F15B13/02 ,  F15B21/00

摘要： A servo-control. The servo-control comprises at least one body as well as a power shaft and a control piston arranged in each body, the at least one body and the power shaft respectively forming two power members. One of the power members bears at least on end-stop member and the power member without an end-stop member bears a passivation actuator. The passivation actuator comprises a passivation shaft which bears an end-stop and a passivation piston, the passivation piston being arranged to be mobile in longitudinal translation in an enclosure, an elastic system being arranged between the passivation piston and the enclosure.

公开(公告)号：US20190300163A1

公开(公告)日：2019-10-03

申请号：US16369546

申请日：2019-03-29

申请人： AIRBUS HELICOPTERS

发明人： Jean-Romain BIHEL ,  Damien SEQUERA ,  Jean-Pierre JALAGUIER

IPC分类号： B64C27/00

摘要： A hydro-elastic damper comprising at least one elastic assembly comprising an elastic member between two strength members. The elastic assembly including a compression chamber. The hydro-elastic damper includes a damping assembly provided with an expansion chamber that is defined in a transverse direction by an end wall and by a piston. The compression chamber is hydraulically connected to the expansion chamber by three hydraulic connections comprising respectively: a duct; at least one first passage with an overpressure valve; and at least one second passage with a check valve.

公开(公告)号：US20150176612A1

公开(公告)日：2015-06-25

申请号：US14277422

申请日：2014-05-14

申请人： AIRBUS HELICOPTERS

发明人： Jean-Romain BIHEL ,  Pascal LEGUAY ,  Thibaut MARGER

IPC分类号： F15B13/01 ,  B64C13/40 ,  F15B11/02

CPC分类号： F15B13/01 ,  B64C13/40 ,  B64C27/605 ,  B64C27/64 ,  F15B11/02 ,  F15B13/0402 ,  F15B20/008 ,  F15B2211/8636 ,  F15B2211/8752 ,  F15B2211/8757 ,  F16K11/07 ,  F16K11/0704 ,  F16K11/0708

摘要： A hydraulic valve (3, 3′) of a servo-control for feathering the blades (1) of a rotorcraft rotor. The hydraulic valve (3, 3′) comprises a main valve member (5) and an emergency valve member (6) blocked relative to a valve cylinder (4) of the hydraulic valve (3, 3′) by means of a pin (23) in sliding thrust engagement in a cavity (24) of the emergency valve member (6). Relative movement between the emergency valve member (6) and the valve cylinder (4) initiating sliding movement of the pin (23) inside the cavity (24) and causing mover means (27) for moving the pin (23) to be put into operation, thereby releasing the emergency valve member (6) to move freely.

摘要翻译： 用于使旋翼飞机转子的叶片（1）羽化的伺服控制器的液压阀（3,3'）。 液压阀（3,3'）包括主阀构件（5）和相对于液压阀（3,3'）的气缸（4）通过销钉（3）封闭的紧急阀构件（6） 23）在紧急阀构件（6）的空腔（24）中滑动推力接合。 紧急阀构件（6）和阀缸（4）之间的相对运动引起销（23）在空腔（24）内部的滑动运动，并使得用于移动销（23）的移动装置（27）被放入 从而释放紧急阀构件（6）以自由移动。

公开(公告)号：US20180148167A1

公开(公告)日：2018-05-31

申请号：US15826851

申请日：2017-11-30

申请人： AIRBUS HELICOPTERS

发明人： Jean-Romain BIHEL ,  Zouhair SASSI

IPC分类号： B64C27/56 ,  B64C13/14 ,  B64C27/82

CPC分类号： B64C27/56 ,  B64C11/30 ,  B64C13/0421 ,  B64C13/044 ,  B64C13/14 ,  B64C27/82 ,  B64C2027/8227 ,  B64D31/04

摘要： A control member that is operable by a pilot to vary thrust from a thrust system of an aircraft. The control member comprises a stick and a movable assembly including a grip. The grip is linked to the stick via a helical link, rotation of the grip about the stick giving rise to movement in translation of the grip together with the movable assembly along the stick, the grip being movable in translation in both a first direction in translation and in a second direction in translation that is opposite to the first direction in translation.

公开(公告)号：US20160195113A1

公开(公告)日：2016-07-07

申请号：US14989105

申请日：2016-01-06

申请人： AIRBUS HELICOPTERS

发明人： Jean-Romain BIHEL ,  Thibaut MARGER ,  Christophe PUJOL ,  Alexandre PANTAINE

IPC分类号： F15B11/10 ,  B64C27/12

CPC分类号： F15B11/10 ,  B64C13/42 ,  B64C27/12 ,  F15B9/10 ,  F15B18/00 ,  F15B2211/321 ,  F15B2211/8633 ,  F15B2211/8752

摘要： A servo-control having at least one movable cylinder that includes a hydraulic directional control valve. The hydraulic valve includes a control shaft that is rotatable about a longitudinal axis, the control shaft being connected to a distributor slide. The servo-control including a stationary abutment member secured to a cylinder and an input lever situated outside the cylinder. The input lever is connected to the control shaft and includes a stop portion arranged in the abutment member. The servo-control includes movement means for moving the input lever longitudinally, a first abutment surface of the abutment member limiting a travel amplitude of the stop portion when the input lever is in a first position.

摘要翻译： 具有至少一个包括液压方向控制阀的可动气缸的伺服控制器。 液压阀包括可绕纵向轴线旋转的控制轴，控制轴连接到分配器滑块。 伺服控制器包括固定到气缸的静止的抵接构件和位于气缸外部的输入杆。 输入杆连接到控制轴，并且包括设置在抵接构件中的止动部。 伺服控制器包括用于纵向地移动输入杆的移动装置，当输入杆处于第一位置时，邻接构件的第一邻接表面限制止动部分的行进幅度。

公开(公告)号：US20170144747A1

公开(公告)日：2017-05-25

申请号：US15352924

申请日：2016-11-16

申请人： AIRBUS HELICOPTERS

发明人： Jean-Romain BIHEL ,  Arnaud GROLL ,  Romuald BIEST ,  Zouhair SASSI

IPC分类号： B64C13/12 ,  B64C11/36 ,  B64C29/00 ,  B64C13/28 ,  B64C27/26

摘要： An adaptive flight control system for controlling the pitch of blades of a propulsive propeller of a hybrid helicopter as a function of the return value of the pitch. The adaptive flight control system comprises control means supplying the pitch control order, a piloting member controlling variation of the pitch, and piloting means applying a control gain in order to transform the control order into a setpoint, and transmitting the setpoint to the piloting member. The piloting means include information return means applying a return gain that is variable to the return value of the variation of the pitch to the piloting means, also modifying the control gain as a function of the return value.

公开(公告)号：US20150298796A1

公开(公告)日：2015-10-22

申请号：US14686001

申请日：2015-04-14

申请人： AIRBUS HELICOPTERS

发明人： Jean-Romain BIHEL ,  Clement COIC ,  Thibaut MARGER ,  Gerard COUDERC

IPC分类号： B64C13/42

CPC分类号： B64C13/42 ,  B64C27/64 ,  F15B15/1452 ,  F15B15/1461

摘要： A hydraulic system of an aircraft, the system comprising at least one servo-control, each servo-control comprising at least one cylinder together with a drive rod and a piston arranged in each cylinder. Between each cylinder of servo-control and the drive rod of that servo-control, at least one servo-control presents main sealing means with controlled leakage allowing a hydraulic fluid to leak out from the cylinder, the hydraulic system further comprising at least one enclosure, each cylinder of the servo-control being arranged inside the enclosure so that the fluid is collected in the enclosure.

摘要翻译： 一种飞行器的液压系统，该系统包括至少一个伺服控制器，每个伺服控制器包括至少一个气缸以及布置在每个气缸中的驱动杆和活塞。 在伺服控制的每个气缸和该伺服控制器的驱动杆之间，至少一个伺服控制器提供主要的密封装置，其具有受控的泄漏，允许液压流体从气缸中泄漏出来，液压系统还包括至少一个外壳 伺服控制器的每个气缸被布置在外壳内，使得流体被收集在外壳中。

公开(公告)号：US20150292527A1

公开(公告)日：2015-10-15

申请号：US14682327

申请日：2015-04-09

申请人： AIRBUS HELICOPTERS

发明人： Thibaut MARGER ,  Arnaud GROLL ,  Jean-Romain BIHEL ,  Clement COIC

IPC分类号： F15B13/02 ,  B64C27/58

CPC分类号： F15B13/026 ,  B64C27/58 ,  B64C27/64 ,  F15B11/22 ,  F15B18/00 ,  F15B2211/50572 ,  F15B2211/5152 ,  F15B2211/5154 ,  F15B2211/5155 ,  F15B2211/57 ,  F15B2211/8757

摘要： A pressure-balance valve for balancing the pressures of fluids admitted into the pressure-balance valve via respective second ducts. The pressure-balance valve has both a chamber for guiding movement in translation of a piston, and also fluid flow paths, each comprising a said second duct and a first duct for admitting a fluid coming from the same fluid source as the fluid flowing in its second duct. Each of the first ducts is provided with a shutter co-operating with a ramp arranged on the piston. Movement of the piston in translation as a result of a pressure difference between the fluids respectively admitted into the second ducts causes one of the shutters to slide along the corresponding ramp and consequently allows additional fluid to be delivered from a first duct to the second duct of the same fluid flow path.

摘要翻译： 一种压力平衡阀，用于通过相应的第二导管平衡进入压力平衡阀的流体的压力。 压力平衡阀具有用于引导活塞平移的运动的腔室以及流体流动路径，每个流体通道包括一个第二管道和第一管道，用于允许来自与其中流动的流体相同的流体源的流体 第二导管。 每个第一管道设置有与设置在活塞上的斜坡配合的闸板。 由于分别进入第二管道的流体之间的压力差导致活塞平移的运动导致一个快门沿着相应的斜坡滑动，并且因此允许另外的流体从第一管道输送到第二管道 相同的流体流动路径。

公开(公告)号：US20180105265A1

公开(公告)日：2018-04-19

申请号：US15728750

申请日：2017-10-10

申请人： AIRBUS HELICOPTERS

发明人： Stephane MAZET ,  Jean-Romain BIHEL ,  Mathias FOURNIER ,  Sylvain BERTHALON

IPC分类号： B64C27/51 ,  B64C27/48

CPC分类号： B64C27/51 ,  B64C27/001 ,  B64C27/35 ,  B64C27/48

摘要： A lead-lag damper arranged inside a blade of a rotor of a rotary wing aircraft. The lead-lag damper (comprises an inner strength member provided with a cage in which a ball-joint connection is arranged, an outer strength member for securing to the blade, and an elastomer material member arranged between the two strength members. The two strength members and the elastomer material member extending beyond the zone around the cage so that the relative movements between two strength members resulting from the movements of the blade are damped by deformations of the elastomer material member, at least a portion of the lead-lag damper being designed to occupy a portion of the inside of the blade that is conventionally filled with foam.