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High lift system, aircraft, and method for moving high lift surface relative to wing

An aircraft and wing technology, applied in the field of increased lift systems, to achieve the effects of reducing risk, reducing system complexity, and increasing safety

Active Publication Date: 2016-02-10
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Additionally, an additional system brake is required within the system

Method used

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  • High lift system, aircraft, and method for moving high lift surface relative to wing
  • High lift system, aircraft, and method for moving high lift surface relative to wing
  • High lift system, aircraft, and method for moving high lift surface relative to wing

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Embodiment Construction

[0034] Figure 1a to Figure 1f A part of a first exemplary embodiment of the high lift system 2 is shown schematically. Here, an increased lift surface 4 is shown, to which the first main drive station 6 , the second main drive station 8 , the first primary unit 10 and the second secondary unit 12 are coupled.

[0035] Each of the two main drive stations 6 and 8 includes a geared rotary actuator 14 coupled to a main rod 16 . The geared rotary actuator 14 includes a shaft connection 18 coupled to a transmission shaft 20 driven by a drive unit. The drive unit may be a central drive unit located at a clear distance with respect to the arrangement shown, or it may be a separate drive unit 22 indicated with dashed lines between the primary unit 10 and the second secondary unit 12 .

[0036] By driving the propeller shaft 20 , a torque is provided to the geared rotary actuator 14 which is translated into an extension or retraction movement of the main rod 16 . Thus, by driving the...

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PUM

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Abstract

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.

Description

[0001] Cross References to Related Applications [0002] This application claims priority to European Patent Application No. 14171960.9 filed on June 11, 2014, the entire disclosure of which is hereby incorporated by reference. technical field [0003] The invention relates to a high-lift system for an aircraft, an aircraft having a wing and such a high-lift system, and a method for moving a high-lift surface relative to a wing of an aircraft. Background technique [0004] The aircraft's high-lift system allows for the selective increase of the effective surface area and camber of a wing by deploying high-lift surfaces movably mounted on the wing. These high lift systems may include leading edge slats and trailing edge flaps. By deploying the high-lift surface, the lift coefficient of the aircraft can be greatly increased to allow low flight speeds especially during descent and landing. [0005] In common commercial aircraft, the trailing edge flap system usually includes ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C9/16B64C9/22
CPCB64C13/341B64C9/02B64C13/505B64D2045/001
Inventor 萨斯基亚·德吉
Owner AIRBUS OPERATIONS GMBH