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1. 发明公开

EP3584154A1 AIRCRAFT WING WITH DEPLOYABLE FLAP 有权
公开(公告)号：EP3584154A1
公开(公告)日：2019-12-25
申请号：EP19180621.5
申请日：2019-06-17
申请人： Bombardier Inc.
发明人： ILIESCU, Vlad
IPC分类号： B64C9/02 , B64C9/16
摘要： An aircraft wing (5) includes a groove (20) extending along a length between a forward extremity (22A) and an aft extremity (22B). A forward segment (24A) of the groove (20) extends upwardly to the forward extremity (22A). The forward extremity (22A) is a highest point of the groove. A flap carriage (32) is mounted to the groove (20) and displaceable therealong. A flap (10) is pivotably attached to the flap carriage (32) to define a flap pivot axis (35A) about which the flap (10) is rotatable. The flap (10) is displaceable with the flap carriage (32). An actuator (40) has an arm (44) being extendable between an extended position and a retracted position to displace the flap carriage (32) along the groove (20). The flap carriage (32) in the retracted position being disposed in the forward segment (24A) of the groove (20) and the flap (10) being rotated about the flap pivot axis (35A) to position the flap trailing edge (11B) in negative flap deployment.

2. 发明公开

EP2925603A1 FAILURE DETECTION MECHANISM FOR SELECTOR LEVER 有权转让
标题翻译： FEHLERERKENNUNGSMECHANISMUSFÜRWÄHLHEBEL
公开(公告)号：EP2925603A1
公开(公告)日：2015-10-07
申请号：EP12805493.9
申请日：2012-11-27
申请人： Bombardier Inc. , Learjet Inc.
发明人： ILIESCU, Vlad , SALIB, Menas
IPC分类号： B64C13/10 , B64D31/04
CPC分类号： B64C13/10 , B64D31/04 , G05G5/03 , Y10T74/20612
摘要： A selector lever includes a housing (16) with front and rear ends and a lever (12) with a shaft (22) pivotally disposed on a cross-shaft (20). The shaft defines a shaft axis. The lever has a top that is disposed outside of the housing. A movable shaft (24) moves substantially axially along the shaft axis. A pin (40), having first and second protrusions (50,52), is disposed adjacent to a bottom end (38) of the movable shaft. A first detent plate (44) is disposed on a first side of the movable shaft and includes at least a first slot (42) that receives the first protrusion. A second detent plate (44) is disposed on a second side of the moveable shaft and includes at least a second slot therein receiving the second protrusion. A first failure detection slot (74) is associated with the first slot, permitting movement of the first protrusion (50) therein in the absence of the second protrusion (52).
摘要翻译：选档杆包括具有前端和后端的壳体和具有枢转地布置在横向轴上的轴的杆。轴定义轴轴。杠杆具有设置在壳体外部的顶部。可动轴沿轴线基本轴向移动。具有第一和第二突起的销被设置成与可动轴的底端相邻。第一制动板设置在可动轴的第一侧上，并且至少包括容纳第一突起的第一槽。第二制动板设置在可动轴的第二侧上，并且在其中至少包括第二槽，其中容纳第二突起。第一故障检测槽与第一槽相关联，允许在不存在第二突起的情况下第一突起在其中移动。

3. 发明公开

EP3347274A1 APPARATUS AND METHODS FOR DISTRIBUTING ELECTRIC POWER ON AN AIRCRAFT DURING A LIMITED POWER AVAILABILITY CONDITION 有权
公开(公告)号：EP3347274A1
公开(公告)日：2018-07-18
申请号：EP16766637.9
申请日：2016-09-08
申请人： Bombardier Inc. , Short Brothers Plc
发明人： NFONGUEM, Gustave , ILIESCU, Vlad
IPC分类号： B64D41/00
摘要： Methods and apparatus for distributing electric power from a power source of an aircraft to a plurality of electrical loads of the aircraft during a limited power availability condition are disclosed. An exemplary method comprises: distributing electric power from the power source of the aircraft to the plurality of electrical loads; receiving one or more signals indicative of a demand for electric power by one or more of the plurality of electrical loads; and adjusting the power distribution to the plurality of electrical loads based on the demand for electric power by the one or more plurality of electrical loads. The power distribution is also adjusted to maintain an overall power consumption of the plurality of electrical loads at or below a threshold.

4. 发明授权

EP2925603B1 FAILURE DETECTION MECHANISM FOR SELECTOR LEVER 有权转让
标题翻译：选择杆的故障检测机制
公开(公告)号：EP2925603B1
公开(公告)日：2017-09-13
申请号：EP12805493.9
申请日：2012-11-27
申请人： Bombardier Inc. , Learjet Inc.
发明人： ILIESCU, Vlad , SALIB, Menas
IPC分类号： B64C13/10 , B64D31/04
CPC分类号： B64C13/10 , B64D31/04 , G05G5/03 , Y10T74/20612

5. 发明授权

EP3347274B1 APPARATUS AND METHODS FOR DISTRIBUTING ELECTRIC POWER ON AN AIRCRAFT DURING A LIMITED POWER AVAILABILITY CONDITION 有权
公开(公告)号：EP3347274B1
公开(公告)日：2020-04-01
申请号：EP16766637.9
申请日：2016-09-08
申请人： Bombardier Inc. , Short Brothers Plc
发明人： NFONGUEM, Gustave , ILIESCU, Vlad
IPC分类号： B64D41/00

6. 发明公开

EP3317179A1 AIRCRAFT WITH DISTRIBUTED HYDRAULIC SYSTEM 有权
标题翻译：具有分布式液压系统的飞机
公开(公告)号：EP3317179A1
公开(公告)日：2018-05-09
申请号：EP16734040.5
申请日：2016-06-23
申请人： Bombardier Inc. , Short Brothers Plc
发明人： NFONGUEM, Gustave , ILIESCU, Vlad , ARDMAN, Avraham
IPC分类号： B64C13/50 , B64C13/42
CPC分类号： B64C13/42 , B64C5/10 , B64C9/00 , B64C13/503 , B64C13/504 , B64C2009/005 , Y02T50/44
摘要： An aircraft comprises an aircraft structure, a flight control surface attached to the aircraft structure, and a local hydraulic power pack disposed proximal to the flight control surface. The local hydraulic power pack is configured to provide pressurized hydraulic fluid for actuating the flight control surface. The local hydraulic power pack comprises a reservoir for the hydraulic fluid and two hydraulic pumps for pressurizing the hydraulic fluid.

7. 发明公开

EP3143306A1 ACTUATORS AND METHODS FOR AIRCRAFT FLIGHT CONTROL SURFACES 有权
标题翻译：阿拉伯联合酋长国VERFAHRENFÜRFLUGZEUGFLUGSTEUERUNGSOBERFLÄCHEN
公开(公告)号：EP3143306A1
公开(公告)日：2017-03-22
申请号：EP15723767.8
申请日：2015-05-13
申请人： Bombardier Inc. , Université de Sherbrooke , SHORT BROTHERS PLC
发明人： NFONGUEM, Gustave , CHOUINARD, Patrick , PLANTE, Jean - Sebastien , DENNINGER, Marc , ILIESCU, Vlad
IPC分类号： F16H25/20
CPC分类号： B64C13/28 , B64C13/42 , F16H25/20 , F16H25/205 , F16H25/2056 , F16H25/2454 , F16H2025/2071 , F16H2025/2081
摘要： Actuators and methods useful in the operation aircraft flight control surfaces are disclosed. Some of the actuators and methods disclosed may be useful in the operation flight control surfaces when a fault condition such as a jam associated with an actuator is detected. An exemplary electromechanical actuator disclosed comprises: a motor; a first screw configured for translation movement relative to a structure of the aircraft when driven by the motor; a second screw mounted in series with the first screw; and a fuse element coupling the first screw and the second screw together to permit translation movement of the second screw together with the first screw. The fuse element may permit at least partial disengagement of the second screw from the first screw to permit translation of the second screw relative to the first screw. The fuse element may also allow an active flutter damping of the flight control surface. The fuse element may comprise magneto-rheological fluid.
摘要翻译：公开了在操作飞行器飞行控制表面中有用的致动器和方法。当检测到诸如与致动器相关联的堵塞的故障状况时，所公开的一些致动器和方法在操作飞行控制表面中可能是有用的。公开的示例性机电致动器包括：电动机; 第一螺杆，其构造成当由所述电动机驱动时相对于所述飞机的结构进行平移运动; 与第一螺钉串联安装的第二螺钉; 以及将第一螺钉和第二螺钉联接在一起的熔丝元件，以允许第二螺钉与第一螺钉一起平移运动。保险丝元件可以允许第二螺钉至少部分地从第一螺钉脱离，以允许第二螺钉相对于第一螺钉的平移。保险丝元件还可以允许飞行控制表面的主动颤动阻尼。保险丝元件可以包括磁流变流体。

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