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EP-4470912-B1 - AERODYNAMIC SYSTEM FOR AN AIRCRAFT

EP4470912B1EP 4470912 B1EP4470912 B1EP 4470912B1EP-4470912-B1

Inventors

  • Hencke, Marc

Dates

Publication Date
20260506
Application Date
20230531

Claims (10)

  1. An aerodynamic system (1) for an aircraft (100), comprising: a support structure (10); an aerodynamic component (20) which is movably coupled to the support structure via a first coupling unit (31) and a second coupling unit (32); wherein the first coupling unit (31) and the second coupling (32) unit are configured to move the aerodynamic component (20) relative to the support structure (10) between a first position and a second position; wherein the first coupling unit (31) and the second coupling unit (32) are configured to transfer a load from the aerodynamic component (20) to the support structure (10) during an operation of the aircraft (100); at least one auxiliary coupling unit (40) coupled between the aerodynamic component (20) and the support structure (10); wherein the at least one auxiliary coupling unit (40) is configured to switch from a decoupling state (41) to a coupling state (42); wherein, in the decoupling state (41), a load transfer from the aerodynamic component (20) via the at least one auxiliary coupling unit (40) to the support structure (10) is prevented; wherein, in the coupling state (42), a load transfer from the aerodynamic component (20) via the at least one auxiliary coupling unit (40) to the support structure (10) is enabled; wherein the at least one auxiliary coupling unit (40) comprises an actuator (43) which is configured to actively move the aerodynamic component (20) relative to the support structure (10) when the at least one auxiliary coupling unit (40) is in the coupling state (42).
  2. The aerodynamic system (1) of claim 1, wherein the at least one auxiliary coupling unit (40) is configured to switch from the decoupling state (41) to the coupling state (42) based on a decoupling event at one of the first coupling unit (31) or the second coupling unit (32).
  3. The aerodynamic system (1) according to any one of the preceding claims, wherein the decoupling state (41) of the at least one auxiliary coupling unit (40) is defined by a decoupling of the aerodynamic component (20) from the support structure (10) via the at least one auxiliary coupling unit (40) in such a way that the at least one auxiliary coupling unit provides at least one more degree of freedom than the first coupling unit (31) or second coupling unit (32).
  4. The aerodynamic system (1) according to any one of the preceding claims, wherein each of the first coupling unit (31) and the second coupling unit (32) comprises an actuator (33, 34) which is configured to actively move the aerodynamic component (20) relative to the support structure (10).
  5. The aerodynamic system (1) according to claim 4, comprising: a drive shaft (11) which is arranged at the support structure (10); wherein the actuator (33) of the first coupling unit (31), the actuator (34) of the second coupling unit (32) and the actuator (43) of the at least one auxiliary coupling unit (40) are driven by the drive shaft (11).
  6. The aerodynamic system (1) according to any one of the preceding claims, wherein the at least one auxiliary coupling unit (40) comprises a mechanical linkage (44) coupled between the aerodynamic component (20) and the support structure (10); wherein the mechanical linkage (44) is configured to initiate a switch from the decoupling state (41) to the coupling state (42) of the at least one auxiliary coupling unit (40) by an engaging movement (45) inside the mechanical linkage (44).
  7. The aerodynamic system (1) according to any one of the preceding claims, wherein the at least one auxiliary coupling unit (40) comprises two longitudinal connector elements (46, 47); wherein the longitudinal connector elements (46, 47) are connected to each other in a connection region (48); wherein, in the decoupling state (41) of the at least one auxiliary coupling unit (40), the connector elements (46, 47) are separated by a gap (45) in the connection region (48) such that a load transfer (51, 52) in a longitudinal direction of at least one of the connector elements (46, 47) is prevented.
  8. The aerodynamic system (1) according to claim 7, wherein the at least one auxiliary coupling unit (40) comprises a damper element arranged in the connection region (48) between the two connector elements (46, 47).
  9. The aerodynamic system (1) according to any one of the preceding claims, wherein at least one of the first coupling unit (31) or the second coupling unit (32) comprises a sensor; and/or wherein the at least one auxiliary coupling unit (40) comprises a sensor.
  10. Aircraft comprising (100) an aerodynamic system (1) according to any one of the preceding claims, wherein the aerodynamic component (20) is a trailing-edge flap (11), a leading-edge slat (12), an aileron, a rudder or an elevator.

Description

Field of the invention The invention generally relates to movable aerodynamic structures. In particular, the invention relates to an aerodynamic system for an aircraft as well as to an aircraft comprising such an aerodynamic system. Technical Background Movables like flap components for aircraft are usually exposed to strong aerodynamic loads during operation of the aircraft. For example, flap components are attached at a trailing edge region of an aircraft wing and provide specified cruise and high-lift configurations, wherein the flap components are adapted to be retracted and deployed depending on the current flight condition. The movables, e.g., the flaps, are usually coupled to a base structure via actuators which enable a movement of the movables relative to the base structure. These actuators are also designed to transfer the loads from the movable to the base structure during each operating condition of the movable. US 2012/0012696 A1 and WO 2012/009087 A1 describe an aircraft flap actuator assembly which includes at least one fixed support, at least one track having a curvilinear track surface connected to the fixed support, at least one flap support adapted to traverse the curvilinear track surface, a trailing edge flap connected to the at least one flap support and a flap actuator engaging the at least one flap support. US 2015/360769 A1 describes a high lift system for an aircraft, comprising 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. US 2022/227484 A1 describes an actuation system, for example an actuation system for an aircraft control surface. The actuation system includes a rotary driver and three or more actuator modules, and each actuator module may be connected to the rotary driver such that the three or more actuator modules are configured to drive rotation of the rotary driver in combination. GB 2 449 172 A describes a drive system for the flaps/slats of an aircraft wing comprising drive shafts which are connected to the flaps, and comprising one or more servo motor units connected to the drive shafts, wherein the drive shafts can be selectively coupled with one another. WO 2008/001336 A1 describes an adjusting device for adjusting a high-lift flap and an airfoil wing provided with the same. DE 10 2012 005423 A1 describes an aircraft having a control unit which controls an aileron function of the aircraft. The control unit is provided with several drive units to adjust the landing flaps of the aircraft such that the aileron function of the aircraft is controlled by the operation of drive units during flight mode by the displacement of the flaps. Summary of the invention It may be seen as an object of the invention to improve the fail-safe characteristics of an aerodynamic system. The present invention claims an aerodynamic system according to claim 1. Preferred embodiments are claimed in the dependent claims. The inventive aerodynamic system may provide a mechanism which couples the auxiliary coupling unit as soon as one of the first or the second coupling unit experiences a decoupling event in which the coupling functionality, e.g. the load transfer capability, of the one of the first or the second coupling unit is disabled for any reason. In particular, if one of the first or the second coupling unit experiences such a decoupling event, the aerodynamic component gets partially or fully decoupled from the support structure. Such a decoupling event may also be called a GRA (geared rotary actuator) freewheel or disconnect condition. Therefore, upon the decoupling event of the first or the second coupling unit, a load transfer via the first or second coupling unit which experienced the decoupling event may be restricted or even inhibited. Accordingly, any actuator that usually drives the aerodynamic component via the first or the second coupling unit cannot anymore contribute to driving the aerodynamic component after experiencing the decoupling event. In other words, upon such a decoupling event of one of the first or the second coupling unit, one load path gets disabled. The inventive aerodynamic system may then provide a second or an additional load path via the auxiliary coupling unit, wherein the load path via the auxiliary coupling unit may be passively established. In particular, if one of the first or the second coupli