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公开(公告)号：US10738803B2
公开(公告)日：2020-08-11
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
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.
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公开(公告)号：US10737775B2
公开(公告)日：2020-08-11
申请号：US15826851
申请日：2017-11-30
申请人： AIRBUS HELICOPTERS
发明人： Jean-Romain Bihel , Zouhair Sassi
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.
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公开(公告)号：US11142307B2
公开(公告)日：2021-10-12
申请号：US15728750
申请日：2017-10-10
申请人： AIRBUS HELICOPTERS
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.
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公开(公告)号：US09732769B2
公开(公告)日：2017-08-15
申请号：US14989105
申请日：2016-01-06
申请人： AIRBUS HELICOPTERS
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.
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公开(公告)号：US11518503B2
公开(公告)日：2022-12-06
申请号：US16425178
申请日：2019-05-29
申请人： AIRBUS HELICOPTERS
IPC分类号： B64C27/00 , B64C27/06 , F16F13/00 , F16F15/023
摘要： A hydroelastic damper comprising at least a first resilient assembly that is provided with a first inner strength member engaged at least in part in a first outer strength member, a first resilient member providing resilient return for the first outer strength member and the first inner strength member towards a rest position (POSREP). The hydroelastic damper comprises at least one hydraulic assembly provided with a first hydraulic chamber and a second hydraulic chamber in communication with each other via a connection provided in a first wall of the hydraulic assembly. A first floating piston is movable at least in translation along the longitudinal axis relative to the first inner strength member and to the first outer strength member, the first hydraulic chamber being defined at least by the first floating piston and the first wall in order to protect the first resilient member.
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公开(公告)号：US10518870B2
公开(公告)日：2019-12-31
申请号：US15727826
申请日：2017-10-09
申请人： AIRBUS HELICOPTERS
IPC分类号： B64C13/04 , B64D31/04 , B64C13/50 , B64C13/28 , B64C27/26 , B64C27/56 , B64C11/30 , B64C13/42 , B64C27/82
摘要： An electric control device having manipulation means. The electric control device has a first measurement system and a second measurement system respectively taking a first measurement and a second measurement of the current position of the manipulation means. A processor unit compares the first and second measurements in order to generate a control signal as a function of said current position, said processor unit considering that the manipulation means are in a neutral position when the first and second measurements do not correspond to the same position for the manipulation means.
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7.发明授权公开(公告)号：US10507905B2
公开(公告)日：2019-12-17
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： B64C13/00 , B64C27/02 , B64C13/28 , B64C13/04 , B64D31/04 , B64C11/36 , B64C13/12 , B64C27/26 , B64C27/28 , G05D1/08
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.
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公开(公告)号：US11161601B2
公开(公告)日：2021-11-02
申请号：US16369546
申请日：2019-03-29
申请人： AIRBUS HELICOPTERS
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.
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9.发明授权Aircraft hydraulic system comprising at least one servo-control, and an associated rotor and aircraft 有权飞机液压系统包括至少一个伺服控制器，以及相关联的转子和飞机公开(公告)号：US09428262B2
公开(公告)日：2016-08-30
申请号：US14686001
申请日：2015-04-14
申请人： AIRBUS HELICOPTERS
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。
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公开(公告)号：US09950783B2
公开(公告)日：2018-04-24
申请号：US15257172
申请日：2016-09-06
申请人： AIRBUS HELICOPTERS
发明人： Jean-Romain Bihel
摘要： A ball-bearing control cable comprising an outer sheath surrounding a central blade. The outer sheath comprises a central portion extending between two endpieces. Each endpiece comprises a tubular central body that surrounds the central blade, each central body extending from a proximal abutment secured to the central portion towards a free distal abutment, each abutment of an endpiece projecting from the central body of the endpiece, each endpiece including a resilient system interposed around the central body of the endpiece between an abutment of the endpiece and a ring, the resilient system of one endpiece being arranged between the distal abutment and the ring of the endpiece, and the resilient system of the other endpiece being arranged between the proximal abutment and the ring of the other endpiece.
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