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1. 发明授权

US08602352B2 Method for operating a landing gear assembly with a breaker strut 有权
标题翻译：用于操作具有断路器支柱的起落架组件的方法
公开(公告)号：US08602352B2
公开(公告)日：2013-12-10
申请号：US13376160
申请日：2010-06-03
申请人： Nicolas Keller , Albert De Pindray , Edouard Campbell , Dominique Ducos , Sebastien Dubois
发明人： Nicolas Keller , Albert De Pindray , Edouard Campbell , Dominique Ducos , Sebastien Dubois
IPC分类号： B64C25/10 , B64C25/20
CPC分类号： B64C25/14 , B64C25/20 , B64C25/24 , B64C25/26
摘要： A method of operating an aircraft landing gear between a deployed position and a retracted position. The landing gear comprises a leg hinged to the aircraft, the leg being stabilized in the deployed position by a folding strut comprising two hinged-together links, the strut being held in an aligned position by a stabilizer member comprising two hinged-together links themselves held in alignment by a locking member. The method comprises the steps of arranging the strut (2; 102) and the stabilizer member (4; 104) in such a manner that at least one of the links (4a; 104a) of the stabilizer member moves continuously during a movement of the leg from the deployed position to the retracted position, and of attaching an operating actuator (10; 110) to the link in order to cause the link to pivot against the locking member and to exert thereon a force tending to move the leg.
摘要翻译：一种在展开位置和缩回位置之间操作飞机起落架的方法。起落架包括铰接到飞行器的腿部，腿部由包括两个铰接在一起的连杆的折叠支柱稳定在展开位置，该支柱由稳定器构件保持在对准位置，稳定器构件包括两个铰接在一起的链节，通过锁定构件对齐。该方法包括以下步骤：将支柱（2; 102）和稳定器构件（4; 104）布置成使得稳定器构件的至少一个连杆（4a; 104a）在移动过程中连续地移动从展开位置到缩回位置，并且将操作致动器（10; 110）连接到连杆上，以便使连杆枢转抵靠锁定件并在其上施加倾向于移动腿部的力。

2. 发明申请

US20120080559A1 METHOD FOR OPERATING A LANDING GEAR ASSEMBLY WITH A BREAKER STRUT 有权
标题翻译：一种用断路器操作起落架齿轮组件的方法
公开(公告)号：US20120080559A1
公开(公告)日：2012-04-05
申请号：US13376160
申请日：2010-06-03
申请人： Nicolas Keller , Albert De Pindray , Edouard Campbell , Dominique Ducos , Sebastien Dubois
发明人： Nicolas Keller , Albert De Pindray , Edouard Campbell , Dominique Ducos , Sebastien Dubois
IPC分类号： B64C25/26
CPC分类号： B64C25/14 , B64C25/20 , B64C25/24 , B64C25/26
摘要： A method of operating an aircraft landing gear between a deployed position and a retracted position. The landing gear comprises a leg hinged to the aircraft, the leg being stabilized in the deployed position by a folding strut comprising two hinged-together links, the strut being held in an aligned position by a stabilizer member comprising two hinged-together links themselves held in alignment by a locking member. The method comprises the steps of arranging the strut (2; 102) and the stabilizer member (4; 104) in such a manner that at least one of the links (4a; 104a) of the stabilizer member moves continuously during a movement of the leg from the deployed position to the retracted position, and of attaching an operating actuator (10; 110) to the link in order to cause the link to pivot against the locking member and to exert thereon a force tending to move the leg.
摘要翻译：一种在展开位置和缩回位置之间操作飞机起落架的方法。起落架包括铰接到飞行器的腿部，腿部由包括两个铰接在一起的连杆的折叠支柱稳定在展开位置，该支柱由稳定器构件保持在对准位置，稳定器构件包括两个铰接在一起的链节，通过锁定构件对齐。该方法包括以下步骤：将支柱（2; 102）和稳定器构件（4; 104）布置成使得稳定器构件的至少一个连杆（4a; 104a）在移动过程中连续地移动从展开位置到缩回位置，并且将操作致动器（10; 110）连接到连杆上，以便使连杆枢转抵靠锁定件并在其上施加倾向于移动腿部的力。

3. 发明授权

US09056672B2 Hydraulically regulated electromagnetic actuator, and landing gear fitted with such an actuator for controlling same 有权
标题翻译：液压调节电磁执行器和装有这样一个致动器的起落架用于控制它
公开(公告)号：US09056672B2
公开(公告)日：2015-06-16
申请号：US13640809
申请日：2011-04-15
申请人： Nicolas Keller , Edouard Campbell , Sébastien Dubois , Albert De Pindray
发明人： Nicolas Keller , Edouard Campbell , Sébastien Dubois , Albert De Pindray
IPC分类号： B64C25/26 , B64C25/24 , F16D57/06
CPC分类号： B64C25/26 , B64C25/24 , F16D57/06
摘要： An electromechanical actuator comprising an electric motor (11) for driving an output shaft (4) in rotation via a reduction gear (20) and passive regulation stage (30) allowing for control of the speed of rotation of the output shaft. A braking member is arranged between an output of the reduction gear and the output shaft to be driven, the braking member being arranged to ensure two different braking levels depending on the direction of rotation of the shaft. The braking member is of hydraulic type and comprises a paddle (33) for transferring fluid between two chambers (34, 35) under the effect of the rotation of the output shaft, transferred fluid passing through a selective drawing member (41) which, depending on the direction of rotation of the actuator, opposes two distinct resistances to the decantation of the fluid from one chamber to the other.
摘要翻译：一种机电致动器，包括用于通过减速齿轮（20）驱动输出轴（4）旋转的电动机（11）和允许输出轴的旋转速度的无源调节级（30）。制动部件设置在减速齿轮的输出端与被驱动的输出轴之间，制动部件被配置成根据轴的旋转方向确保两个不同的制动水平。制动构件是液压式的，包括用于在输出轴旋转的作用下在两个腔室（34,35）之间传送流体的桨叶（33），经过选择性拉拔构件（41）的传递的流体在致动器的旋转方向上，对流体从一个腔室到另一个腔室的倾析两个不同的阻力。

4. 发明申请

US20130092482A1 HYDRAULICALLY REGULATED ELECTROMAGNETIC ACTUATOR, AND LANDING GEAR FITTED WITH SUCH AN ACTUATOR FOR CONTROLLING SAME 有权
标题翻译：液压调节电磁致动器，以及配有这样一个执行器控制的接地齿轮
公开(公告)号：US20130092482A1
公开(公告)日：2013-04-18
申请号：US13640809
申请日：2011-04-15
申请人： Nicolas Keller , Edouard Campbell , Sébastien Dubois , Albert De Pindray
发明人： Nicolas Keller , Edouard Campbell , Sébastien Dubois , Albert De Pindray
IPC分类号： B64C25/26
CPC分类号： B64C25/26 , B64C25/24 , F16D57/06
摘要： The present invention relates to an electromechanical actuator comprising an electric motor (11) for driving an output shaft (4) in rotation via a reduction gear (20) and passive regulation means (30) allowing for control of the speed of rotation of the output shaft, and comprising a braking member (30), arranged between an output of the reduction gear and the output shaft to be driven, said braking member being arranged to ensure two different braking levels depending on the direction of rotation of the shaft, characterized in that the braking member is of hydraulic type and comprises fluid decantation means (33) between two chambers (34, 35) decanting under the effect of the rotation of the output shaft through a selective drawing member (41) which, depending on the direction of rotation of the actuator, opposes two distinct resistances to the decantation of the fluid from one chamber to the other.
摘要翻译：本发明涉及一种机电致动器，其包括用于通过减速齿轮（20）驱动输出轴（4）旋转的电动机（11）和被动调节装置（30），其允许控制输出的转速轴，并且包括布置在所述减速齿轮的输出端和待驱动的输出轴之间的制动构件（30），所述制动构件布置成根据所述轴的旋转方向确保两个不同的制动水平，其特征在于所述制动构件是液压型的，并且包括通过选择性拉拔构件（41）在输出轴的旋转作用下滗出的两个腔室（34,35）之间的流体倾析装置（33），所述选择性拉拔构件致动器的旋转对应于从一个室到另一个室的液体的倾析的两个不同的阻力。

5. 发明授权

US09511852B2 Device for coupling an actuator for controlling the landing gear of an aircraft 有权
标题翻译：用于联接用于控制飞行器的起落架的致动器的装置
公开(公告)号：US09511852B2
公开(公告)日：2016-12-06
申请号：US14238534
申请日：2012-09-07
申请人： Thierry Blanpain , Dominique Ducos , Edouard Campbell
发明人： Thierry Blanpain , Dominique Ducos , Edouard Campbell
IPC分类号： B64C25/20 , B64C25/26 , B64C25/62 , B64C25/58
CPC分类号： B64C25/20 , B64C25/26 , B64C25/58 , B64C25/62
摘要： A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure. The device comprises a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged, a pre-loading structure acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; and an abutment structure defining at least one working position for the lever when the actuator is activated.
摘要翻译：一种用于将用于操作飞行器起落架的致动器联接到飞机结构的装置。该装置包括杠杆，其具有用于铰接到飞行器的结构的第一端和致动器铰接的第二端，作用在杠杆上的预加载结构，以将其推向稳定的休止位置，该静止位置由没有任何力通过致动器的杠杆; 以及当所述致动器被致动时限定所述杠杆的至少一个工作位置的邻接结构。

6. 发明申请

US20140209738A1 DEVICE FOR COUPLING AN ACTUATOR FOR CONTROLLING THE LANDING GEAR OF AN AIRCRAFT 有权
标题翻译：用于联接执行机构以控制飞机的起落架的装置
公开(公告)号：US20140209738A1
公开(公告)日：2014-07-31
申请号：US14238534
申请日：2012-09-07
申请人： Thierry Blanpain , Dominique Ducos , Edouard Campbell
发明人： Thierry Blanpain , Dominique Ducos , Edouard Campbell
IPC分类号： B64C25/20
CPC分类号： B64C25/20 , B64C25/26 , B64C25/58 , B64C25/62
摘要： A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure. The device comprises a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged, a pre-loading structure acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; and an abutment structure defining at least one working position for the lever when the actuator is activated.
摘要翻译：一种用于将用于操作飞行器起落架的致动器联接到飞机结构的装置。该装置包括杠杆，其具有用于铰接到飞行器的结构的第一端和致动器铰接的第二端，作用在杠杆上的预加载结构，以将其推向稳定的休止位置，该静止位置由没有任何力通过致动器的杠杆; 以及当所述致动器被致动时限定所述杠杆的至少一个工作位置的邻接结构。

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