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1. 发明公开

EP3486163A1 AN ACTUATING SYSTEM FOR ACTUATING A FOLDABLE WING TIP PORTION OF A WING FOR AN AIRCRAFT 有权
公开(公告)号：EP3486163A1
公开(公告)日：2019-05-22
申请号：EP18206086.3
申请日：2018-11-13
申请人： Airbus Operations GmbH , Airbus Operations S.A.S.
发明人： Dege, Saskia , Jegminat, Svenja , Nicolas, Yann
IPC分类号： B64C3/56 , B64C23/06
CPC分类号： B64C3/56 , B64C23/069 , F15B21/0427 , H05B3/26
摘要： The present invention relates to an actuating system for a wing arrangement (3) for an aircraft (1). The arrangement (3) includes a wing (9) comprising a base section (11) having a first end portion (11a) adapted to be secured to the fuselage (5) of an aircraft (1) and an opposite second end portion (11b), and a tip section (13) having a third end portion (13a) and an opposite fourth end portion (13b), wherein the third end portion (13a) is pivotably connected to the second end portion (11b) such that the tip section (13) is pivotable about a pivot axis (17) between a deployed position and a stowed position in which the spanwise length of the wing (9) is smaller than in the deployed position. The actuating system (21) comprises an actuating arrangement (23) which comprises an actuator (25), a first coupling part (29) and a second coupling part (31). The first coupling part (29) is adapted to be coupled to the base section (11), the second coupling part (31) is adapted to be coupled to the tip section (13) and the actuator (25) is operable to move the second coupling part (31) with respect to the first coupling part (29) between a first position and a second position, such that when the first coupling part (29) is coupled to the base section (11) and the second coupling part (31) is coupled to the tip section (13) the actuating arrangement (23) is operable to selectively move, by operating the actuator (25), the tip section (13) between the deployed position and the stowed position. In the first position of the second coupling part (31) the tip section (13) is in the deployed position, and in the second position of the second coupling part (31) the tip section (13) is in the stowed position. The actuating system (21) further comprises a heating arrangement (33) which is positioned and adapted to be operable to heat at least one portion of the actuating arrangement (23) such that at least for ambient temperatures below a predetermined temperature the required work to be effected by the actuator (25) when moving the second coupling part (31) between the first position and the second position is lower than without heating the at least one portion.

2. 发明公开

EP3486164A1 A METHOD AND A CONTROL UNIT FOR CONTROLLING ACTUATION OF A FOLDABLE WING TIP SECTION OF A WING OF AN AIRCRAFT 审中-公开
公开(公告)号：EP3486164A1
公开(公告)日：2019-05-22
申请号：EP18206089.7
申请日：2018-11-13
申请人： Airbus Operations GmbH , Airbus Operations S.A.S. , Airbus Operations Limited
发明人： Dege, Saskia , Jegminat, Svenja , Guilhamet, Jean , Nienaber, Frank , Jones, Aeron Charles
IPC分类号： B64C3/56
摘要： The invention relates to a method for controlling actuation of a foldable wing tip section of a wing of an aircraft. It comprises receiving (53) at a control unit (19) of an aircraft (1) a command signal (37). The aircraft (1) comprises a wing arrangement (3) which includes a wing (9) comprising a base section (11) having a first end portion (11a) adapted to be secured to the fuselage (5) of an aircraft (1) and an opposite second end portion (11b), and a tip section (13) having a third end portion (13a) and an opposite fourth end portion (13b), wherein the third end portion (13a) is pivotably connected to the second end portion (11b) such that the tip section (13) is pivotable about a pivot axis (17) between a deployed position and a stowed position in which the spanwise length of the wing (9) is smaller than in the deployed position, and an actuating system (21) which is coupled to the control unit (19) and which is operable to selectively move, under the control of the control unit (19), the tip section (13) between the deployed position and the stowed position. The command signal (37) is adapted to instruct the control unit (19) to control the actuating system (21) to move the tip section (13) from the deployed position into the stowed position or from the stowed position into the deployed position. The method further comprises receiving at the control unit (19) a first condition indicating signal (29a) indicative of whether or not the aircraft (1) is on the ground and determining by the control unit (19) based on the first condition indicating signal (29a) if a first condition is met that the aircraft (1) is on the ground, receiving at the control unit (19) a second condition indicating signal (29b) indicative of a current speed of the aircraft (1) and determining by the control unit (19) based on the second condition indicating signal (29b) if a second condition is met that the current speed of the aircraft (1) is below a predetermined maximum speed, and receiving at the control unit (19) a third condition indicating signal (29c) indicative of whether or not the aircraft (1) is at a gate (31) of an airport (33) and determining by the control unit (19) based on the third condition indicating signal (29c) if a third condition is met that the aircraft (1) is not at a gate (31) of an airport (33), and controlling the actuating system (21) to effect the movement of the tip section (13) instructed by the command signal (37) only if all of the first condition, the second condition and the third condition are met.

3. 发明授权

EP3486163B1 AN ACTUATING SYSTEM FOR ACTUATING A FOLDABLE WING TIP PORTION OF A WING FOR AN AIRCRAFT 有权
公开(公告)号：EP3486163B1
公开(公告)日：2020-02-26
申请号：EP18206086.3
申请日：2018-11-13
申请人： Airbus Operations GmbH , Airbus Operations S.A.S.
发明人： Dege, Saskia , Jegminat, Svenja , Nicolas, Yann
IPC分类号： B64C3/56 , B64C23/06

4. 发明公开

EP3486165A1 METHOD FOR OPERATING AN AIRCRAFT COMPRISING A WING WITH A FOLDABLE WING TIP PORTION 审中-公开
公开(公告)号：EP3486165A1
公开(公告)日：2019-05-22
申请号：EP18206434.5
申请日：2018-11-15
申请人： Airbus Operations GmbH
发明人： Dege, Saskia , Jegminat, Svenja , Wyrembek, Jörg
IPC分类号： B64C3/56 , B64D45/00
摘要： Disclosed is a method for operating an aircraft (1) comprising a wing (5) with a foldable wing tip portion (11), the method comprising the following steps:
- Providing an aircraft (1), the aircraft (1) comprising
a fuselage (3),
wings (5) mounted to the fuselage (3),
a sensor system (6), and
a control unit (7),
wherein the sensor system (6) is configured for detecting an operation parameter related to the operation of the foldable wing tip portion (11),
wherein the control unit (7) comprises a system behavior model with respect to the operation parameter, wherein the system behavior model provides a target value of the operation parameter,
- Detecting a value of the operation parameter by the sensor system (6),
- Comparing the detected value of the operation parameter to the corresponding target value of the operation parameter from the system behavior model,
- Upon a predefined deviation of the detected value from the corresponding target value of the operation parameter, detecting a sensor failure or a system failure

5. 发明公开

EP3486162A1 METHOD FOR OPERATING A WING FOR AN AIRCRAFT INCLUDING A FOLDABLE WING TIP PORTION 有权
公开(公告)号：EP3486162A1
公开(公告)日：2019-05-22
申请号：EP18204553.4
申请日：2018-11-06
申请人： Airbus Operations GmbH
发明人： Dege, Saskia , Jegminat, Svenja
IPC分类号： B64C3/56
摘要： Disclosed is a method for operating a wing (5) for an aircraft (1) including a foldable wing tip portion (11). The object, to improve and simplify locking of the arresting unit, is achieved by the following steps:
- Providing a wing (5) for an aircraft (1), the wing (5) comprising
a fixed wing (9),
a foldable wing tip portion (11) mounted to the fixed wing (9) pivotally between an extended position and a folded position,
an actuation unit (13) for actuating movement of the foldable wing tip portion (11), and
an arresting unit (15) for locking the foldable wing tip portion (11) in the extended position and/or in the folded position,

- Controlling the actuation unit (13) to move the foldable wing tip portion (11) either to the extended position or to the folded position until the foldable wing tip portion (11) or the actuation unit (13) contacts a stop element (28),
- Continuing actuation until the actuation unit (13) reaches a stall condition,
- Detecting the stall condition of the actuation unit (13),
- Locking the arresting unit (15) upon detection of the stall condition.

6. 发明授权

EP3492370B1 METHOD FOR TESTING OPERATION OF AN ARRESTING UNIT FOR LOCKING A FOLDABLE WING TIP PORTION IN AN EXTENDED POSITION 有权
公开(公告)号：EP3492370B1
公开(公告)日：2020-07-15
申请号：EP18202248.3
申请日：2018-10-24
申请人： Airbus Operations GmbH
发明人： Dege, Saskia , Jegminat, Svenja
IPC分类号： B64C3/56 , B64F5/60

7. 发明公开

EP3492370A1 METHOD FOR TESTING OPERATION OF AN ARRESTING UNIT FOR LOCKING A FOLDABLE WING TIP PORTION IN AN EXTENDED POSITION 有权
公开(公告)号：EP3492370A1
公开(公告)日：2019-06-05
申请号：EP18202248.3
申请日：2018-10-24
申请人： Airbus Operations GmbH
发明人： Dege, Saskia , Jegminat, Svenja
IPC分类号： B64C3/56 , B64F5/60
摘要： Disclosed is a method for testing operation of an arresting unit (15) for locking a foldable wing tip portion (11) of a wing (5) for an aircraft (1) in an extended position. The object, to increase safety of the aircraft during flight, is achieved by the following steps:
- Providing a wing (5) for an aircraft (1), the wing (5) comprising
a fixed wing (9),
a foldable wing tip portion (11) mounted to the fixed wing (9) pivotally between an extended position and a folded position,
an actuation unit (13) for actuating movement of the foldable wing tip portion (11), and
an arresting unit (15) for locking the foldable wing tip portion (11),

- Locking the foldable wing tip portion (11) in the extended position by the arresting unit (15),
- Controlling the actuation unit (13) to move the foldable wing tip portion (11) in the direction towards the folded position, such that the foldable wing tip portion (11) urges against the arresting unit (15) with a predefined test load,
- Detecting deformation of the arresting unit (15) during or after application of the test load, and
- Comparing the detected deformation to a predefined threshold deformation.

8. 发明授权

EP2955104B1 System and method for moving a high lift surface relative to the wing of an aircraft 有权
标题翻译：用于相对于飞机机翼移动高升力表面的系统和方法
公开(公告)号：EP2955104B1
公开(公告)日：2017-08-09
申请号：EP14171960.9
申请日：2014-06-11
申请人： Airbus Operations GmbH
发明人： Dege, Saskia
IPC分类号： B64C9/02 , B64C13/28 , B64C13/42 , B64C13/50 , B64D45/00 , B64C3/50
CPC分类号： B64C13/28 , B64C9/02 , B64C13/42 , B64D2045/001

9. 发明公开

EP2955104A1 System and method for moving a high lift surface relative to the wing of an aircraft 有权
标题翻译：系统和方法，用于相对于移动的高升力表面到飞机的机翼
公开(公告)号：EP2955104A1
公开(公告)日：2015-12-16
申请号：EP14171960.9
申请日：2014-06-11
申请人： Airbus Operations GmbH
发明人： Dege, Saskia
IPC分类号： B64C9/02 , B64C13/28 , B64C13/50 , B64D45/00 , B64C3/50
CPC分类号： B64C13/28 , B64C9/02 , B64C13/42 , B64D2045/001
摘要： A high lift system (2) for an aircraft, comprises a drive unit, a high lift surface, at least one primary drive station (6, 8), each primary drive station (6, 8) having a shaft connection (18) couplable with the drive unit (22) and a primary lever (16) couplable with the high lift surface (4). The high lift system further comprises at least one secondary unit, each secondary unit (10, 12) having a secondary lever (26) couplable with the high lift surface (4). Each one of the at least one primary drive station (6, 8) is adapted for moving the respective primary lever (16) on driving the shaft connection (18), and each one of the at least one secondary unit (10, 12) comprises a selectively activatable brake (24), such that the secondary lever (26) follows the motion of the one of the at least one high lift surface (4) when the brake (24) is deactivated and such that the secondary lever (16) arrests the motion of the one of the at least one high lift surface (4) when the brake (24) is activated. Thereby, a dual load path is providable, wherein the secondary units (10, 12) are usable for arresting the high lift surfaces (4) during normal operation of the aircraft.
摘要翻译：的高升力系统（2），用于在飞机上，包括驱动单元，高的升力面，至少一个主驱动器站（6,8），每个主驱动器站（6,8），其具有一个轴连接（18）可耦合与驱动单元（22）和主杆（16）联接以高升程表面（4）。高升力系统还包括至少一个次级单元，具有一个副杠杆（26），每个辅助单元（10，12）可耦合与高升力表面（4）。所述至少一个主驱动器站中的每一个（6,8）的angepasst用于在驱动所述轴连接（18）移动所述respectivement主杆（16），以及所述至少一个次级单元中的每一个（10,12）包括一个可选择性激活的制动器（24）检测所做的副杠杆（26）遵循所述至少一个高提升表面中的一个的运动（4）当所述制动器（24）被去激活并且这样做了辅杆（16 ）逮捕该至少一个高提升表面（一个4）当所述制动器（24）被激活的运动。由此，双载荷路径可提供的是，worin次级单元（10，12）是用于所述飞行器的正常手术期间阻止所述高提升表面（4）可用的。

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