Patent ID: 12208896

DETAILED DESCRIPTION

FIG.1shows an exemplary aircraft1according to an embodiment of the present invention. The aircraft1comprises a wing3including a main wing5mounted to a fuselage7, and a trailing edge high lift assembly9including a flap11movably mounted to the main wing5.

FIGS.2and3illustrate two embodiments of the wing3of the aircraft1shown inFIG.1. The wing3according to both first and second embodiments as shown inFIGS.2and3comprises a main wing5and a trailing edge high lift assembly9. The trailing edge high lift assembly9is movably arranged at a trailing edge of the main wing5and comprises a flap11and a connection assembly13. The connection assembly13movably mounts the flap11to the main wing5, such that the flap11is movable between a retracted position with a reduced chord length and curvature of the wing3, and at least one extended position with an extended chord length and curvature of the wing3. The flap11is mounted to the main wing5in a manner rotatable about a flap rotation axis19, wherein the flap rotation axis19is located outside the flap profile spaced apart from the flap11by a flap lever arm20. The flap lever arm20is mounted to the main wing5via a rib21that projects downwards from the lower side of the main wing5and that is mounted to the lever arm20rotatably via the flap rotation axis19. The flap11comprises a leading edge part23including the leading edge25of the flap11, and a trailing edge part27including the trailing edge29of the flap11and mounted to the leading edge part23in a manner pivotable about a pivot axis31extending in a span direction33.

The connection assembly13comprises an actuator unit35for moving the flap11relative to the main wing5between the retracted position and the at least one extended position, and for moving the trailing edge part27relative to the leading edge part23. Specifically, the actuator unit35is configured for moving the trailing edge part27relative to the leading edge part23in a way independent from moving the flap11relative to the main wing5between the retracted position and the at least one extended position. Additionally or alternatively, the actuator unit35is configured for moving the flap11relative to the main wing5between the retracted position and the at least one extended position in a way independent from moving the trailing edge part27relative to the leading edge part23. Specifically, the actuator unit35is configured for driving the trailing edge part27relative to the leading edge part23and the flap11relative to the main wing5in a way independently from one another.

In the embodiments shown inFIGS.2and3, the actuator unit35comprises a motor37, a first output39and a second output41. The motor37in the present embodiment is an electric motor but might also be e.g. a hydraulic motor or a pneumatic motor. The motor37is configured for driving both the first output39and the second output41in a manner independent from one another. The first output39is formed as a first output shaft49rotatable about a first shaft axis43. The second output41is formed as a second output shaft53rotatable about a second shaft axis45. A first rotating arm47is fixedly mounted to the first output shaft49by its one end in a way extending transverse to the first shaft axis43. A second rotating arm51is fixedly mounted to the second output shaft53by its one end in a way extending transverse to the second shaft axis45. The first rotating arm47is coupled by its opposite end to the trailing edge part27of the flap11via a first linkage55comprising a first link57. The first link57is rotatably mounted to the first rotating arm47and in a spaced position is rotatably mounted to a lever59mounted to a lower side of the trailing edge part27.

In the embodiment shown inFIG.2, the actuator unit35is fixedly mounted to a rib21of the main wing5extending downwards from a lower side of the main wing5. The second rotating arm51is coupled by its opposite end to a flap lever arm20fixedly mounted to the leading edge part23of the flap11and extending downwards from the lower side of the leading edge part23, via a second linkage63comprising a second link65. The second link65is rotatably mounted to the second rotating arm51and is rotatably mounted to the flap lever arm20mounted to the lower side of the leading edge part23.

In the alternative embodiment shown inFIG.3, the actuator unit35is fixedly mounted to a flap lever arm20extending downwards from a lower side of the leading edge part23of the flap11. The second rotating arm51is coupled to a rib21extending downwards from a lower side of the main wing5via a second linkage63comprising a second link65. The second link65is rotatably mounted to the second rotating arm51and is rotatably mounted to a rib21mounted to the lower side of the main wing5.

InFIGS.4to6three alternative embodiments of the actuator unit35of the wings3shown inFIGS.2and3are shown having three different arrangements of the first and second output shafts49,53. In the embodiment shown inFIG.4, the first output shaft49and the second output shaft53are arranged in a manner extending away from the motor37on opposite sides of the motor37. In the embodiment shown inFIG.5, the first output shaft49and the second output shaft53are arranged in a manner extending away from the motor37on one common side of the motor37in a coaxial way. In the embodiment shown inFIG.6, the first output shaft49and the second output shaft53are arranged in a manner extending away from the motor37on one common side of the motor37in a way parallelly spaced from one another.

As shown inFIGS.7and8, the first output shaft49and the second output shaft53of the wings3shown inFIGS.2and3are coupled to the motor37via a differential gear unit67configured to control how the rotational power provided by the motor37is distributed between the first and second output shafts49,53. The differential gear unit67comprises a differential gear69coupled to the motor37, a first selection brake71coupled between the differential gear69and the first output shaft49, and a second selection brake73coupled between the differential gear69and the second output shaft53. The differential gear unit67further comprises a first gear unit75in the form of a reduction gear unit coupled between the first selection brake71and the first output shaft49and a second reduction gear unit77in the form of a reduction gear unit coupled between the second selection brake73and the second output shaft53. By selective application of the first and second selection brakes71,73it can be controlled which of the first and second output shafts49,53is provided with rotational power from the motor37. Specifically, the actuator unit35can be selectively operated in a first operation mode and in a second operation mode. In the first operation mode shown inFIG.7, the first selection brake71is engaged and the second selection brake73is released, so that the second output shaft53is driven by the motor37and the first output shaft49is still. In the second operation mode shown inFIG.8, the second selection brake73is engaged and the first selection brake71is released, so that the first output shaft49is driven by the motor37and the second output shaft53is still.

By the trailing edge high lift assembly9according to the invention, only one actuator unit35is required to move both the flap11relative to the main wing5and the trailing edge part27relative to the leading edge part23of the flap11in an independent manner, thereby largely reducing complexity, weight and costs of the wing3.

In summary, the wing (3) includes a main wing (5) and a trailing edge high lift assembly (9) movably arranged at a trailing edge of the main wing (5), the trailing edge high lift assembly (9) comprising a flap (11) and a connection assembly (13) movably mounting the flap (11) to the main wing (5), wherein the connection assembly (13) comprises an actuator unit (35) for moving the flap (11) between a retracted position and at least one extended position, wherein the flap (11) comprises a leading edge part (23) and a trailing edge part (27) mounted to the leading edge part (23) in a manner pivotable about a pivot axis (31). The object to provide a wing having a simplified trailing edge high lift assembly that allows to reduce weight and costs of the wing, is achieved in that the actuator unit (35) is configured for moving the trailing edge part (27) relative to the leading edge part (23) in a way independent from moving the flap (11) between the retracted position and the at least one extended position, and/or in that the actuator unit (35) is configured for moving the flap (11) between the retracted position and the at least one extended position in a way independent from moving the trailing edge part (27) relative to the leading edge part (23)

While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both, unless the this application states otherwise. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.