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1.发明申请公开(公告)号：US20200023938A1
公开(公告)日：2020-01-23
申请号：US16193309
申请日：2018-11-16
Applicant: Airbus Operations GmbH , Airbus Operations S.A.S. , Airbus Operations Ltd.
Inventor： Saskia DEGE , Svenja JEGMINAT , Frank NIENABER , Jean GUILHAMET , Aeron Charles JONES
Abstract: A method to control folding of a wing tip section about a fixed base wing section by a control system that automatically determines whether: (i) a command signal is received to fold the wing tip section, (ii) a first condition indicating signal indicates that the aircraft is on the ground; (iii) the current speed of the aircraft is no greater than a preset maximum speed, and (iv) the aircraft is not at gate in an airport.
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Patent Agency Ranking
公开(公告)号：US20190152580A1
公开(公告)日：2019-05-23
申请号：US16193524
申请日：2018-11-16
Applicant: Airbus Operations GmbH , Airbus Operations S.A.S.
Inventor： Saskia DEGE , Svenja JEGMINAT , Yann NICOLAS
IPC: B64C3/56 , F15B21/0427 , H05B3/26
Abstract: An actuating system for pivoting a wing tip section (13) about a fixed wing base section (11), and including a heating arrangement (33) positioned and adapted to be operable to heat at least one portion of an actuating arrangement (23) that pivots the wing tip section 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.
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3.发明申请公开(公告)号：US20190152624A1
公开(公告)日：2019-05-23
申请号：US16193054
申请日：2018-11-16
Applicant: Airbus Operations GmbH
Inventor： Saskia DEGE , Svenja JEGMINAT
Abstract: A method for testing an arresting unit (15) for locking a foldable wing tip portion (11) to a wing (5) that includes a fixed wing (9), a foldable wing tip portion (11), 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). The method includes: 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.
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4.发明申请HIGH LIFT SYSTEM FOR AN AIRCRAFT, AIRCRAFT HAVING A WING AND A HIGH LIFT SYSTEM AND METHOD FOR MOVING A HIGH LIFT SURFACE RELATIVE TO THE WING OF AN AIRCRAFT 有权用于飞机的高升力系统，具有升降机的飞机和高升力系统以及相对于飞机机翼移动高升力表面的方法公开(公告)号：US20150360769A1
公开(公告)日：2015-12-17
申请号：US14719864
申请日：2015-05-22
Applicant: Airbus Operations GmbH
Inventor： Saskia DEGE
CPC classification number: B64C13/28 , B64C9/02 , B64C13/42 , B64D2045/001
Abstract: A high lift system for an aircraft, comprises a drive unit, a high lift surface, at least one primary drive station, each primary drive station having a shaft connection couplable with the drive unit and a primary lever couplable with the high lift surface. The high lift system further comprises at least one secondary unit, each secondary unit having a secondary lever couplable with the high lift surface. Each one of the at least one primary drive station is adapted for moving the respective primary lever on driving the shaft connection, and each one of the at least one secondary unit comprises a selectively activatable brake, such that the secondary lever follows the motion of the one of the at least one high lift surface when the brake is deactivated.
Abstract translation: 用于飞行器的高升程系统包括驱动单元，高升程表面，至少一个主驱动站，每个主驱动站具有可与驱动单元耦合的轴连接，以及可与高起升面联接的主杆。 高升降系统还包括至少一个次级单元，每个次级单元具有可与高升程表面联接的次级杆。 所述至少一个主驱动站中的每一个适于在驱动所述轴连接件时移动相应的主杠杆，并且所述至少一个次单元中的每一个包括可选择性激活的制动器，使得所述副杠杆跟随所述主杆 当制动器停用时，至少一个高升程表面中的一个。
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公开(公告)号：US20190152579A1
公开(公告)日：2019-05-23
申请号：US16193107
申请日：2018-11-16
Applicant: Airbus Operations GmbH
Inventor： Saskia DEGE , Svenja JEGMINAT
IPC: B64C3/56
Abstract: A method for operating a wing (5) including 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. The method includes 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), and locking the arresting unit (15) upon detection of the stall condition.
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公开(公告)号：US20190152578A1
公开(公告)日：2019-05-23
申请号：US16193239
申请日：2018-11-16
Applicant: Airbus Operations GmbH
Inventor： Saskia DEGE , Svenja JEGMINAT , Jörg WYREMBEK
Abstract: A method to detect a failure of a sensor or system in an aircraft, wherein the aircraft includes a wing including a fixed wing and a wing tip device pivotably mounted to the fixed wing, a sensor system, and a control unit including a system behavior model which models a target vale of an operation parameter of the wing, wherein the method includes: detecting a value of an operation parameter by the sensor system; comparing the detected value of the operation parameter to a corresponding target value of the operation parameter obtained from the system behavior model, and declaring a sensor failure or a system failure in response to determining a predefined deviation of the detected value from the corresponding target value of the operation parameter, detecting a sensor failure or a system failure.
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