ACTUATOR ARRANGEMENT FOR A FIXED ENTRY ELEMENT OF AN AIRCRAFT FLYING ARRANGEMENT AND AIRCRAFT WITH THIS ACTUATOR DEVICE

Description

[0001] The invention relates to an actuator arrangement for a fixed leading edge member of an aircraft. Furthermore, the invention relates to a wing assembly and an aircraft equipped with such an actuator arrangement.

[0002] Most known slat actuation architectures have a static geared rotary actuator (GRA) that drives the slat via a pinon. For some applications, like e.g. droop nose or for space allocation (e.g. short curved track principle) lever bearing assemblies are preferred.

[0003] US 4 979 700 A discloses a typical GRA for a leading edge of an aircraft.

[0004] EP 3 378 762 A1 discloses a wing for an aircraft, comprising a main wing, a slat, and a connection assembly for movably connecting the slat to the main wing. The connection assembly comprises a drive unit provided at the main wing and connected to the slat for initiating movement of the slat. The drive unit comprises a plurality of drive stations spaced apart from one another in the wing span direction.

[0005] WO 2010 / 119 280 A1 discloses a panel device for modifying airflow about a wing of an aircraft. The panel device comprises a plurality of independently operable panel sub-sections. The panel sub-section is coupled to the trailing edge of the wing by a linkage mechanism. The linkage mechanism comprises an actuator coupled to a trapezoidal frame by a mechanical linkage. The actuator is fixed to the wing at the trailing edge. Activation of the actuator is operable to raise and lower the relative position of the panel sub-section with respect to the wing.

[0006] US 3 128 966 A discloses a high-lift system for aircraft wings. The leading edge device comprises a worm and linkage system in which pivoted scissors are pivoted at one of their ends. The scissors connect to a lower flap door and a fixed bracket respectively. At their other ends the scissors connect to a nut-and-bracket device driven by a turning screw. The turning screw results in translation of the nut-and-bracket device, angular displacements of the scissors, and motion of the lower flap door about its pivotal axis.

[0007] US 3 617 018 A discloses a flap connected to a wing by a geared hinge. Extension or retraction of the flap is accomplished by an actuating and drive mechanism arranged on the flap. Upon command of an associated remotely positioned control means the actuating mechanism will via the drive mechanism drive the geared hinge connection for moving the flap into a predetermined position in reference to the wing surface.

[0008] It is the object of the invention to improve an actuator arrangement for high-lift devices.

[0009] The invention provides a wing assembly for an aircraft, the wing assembly comprising a fixed leading edge member, a high-lift device movably attached to the fixed leading edge member, and an actuator arrangement, the actuator arrangement comprising: a fixed leading edge lever attached to the fixed leading edge member at a mounting point, a high-lift device lever attached to the high-lift device, and an actuator assembly that is configured for driving the fixed leading edge lever and the high-lift device lever relative to each other, so as to allow movement of the high-lift device between a fully retracted position and a fully extended position, wherein the fixed leading edge member has an inner cavity that is defined at least in part by an outer skin and a rib, wherein the actuator arrangement is configured for extending and retracting the high-lift device, the actuator assembly including at least one geared rotary actuator, wherein the actuator assembly is configured such that the geared rotary actuator is movable during extending and retracting of the high-lift device between a fully retracted position, in which the geared rotary actuator is predominantly accommodated within the inner cavity, and a fully extended position, in which the geared rotary actuator is predominantly positioned outside the inner cavity. The geared rotary actuator is rotatable about a rotational axis that is defined by the mounting point of the fixed leading edge lever.

[0010] Preferably, the geared rotary actuator is movable along a circular arc section in a forward direction during extending of the high-lift device and / or in an aft direction during retracting of the high-lift device.

[0011] Preferably, the geared rotary actuator, when in the fully retracted position, is wholly accommodated within the inner cavity.

[0012] Preferably, the geared rotary actuator, when in the fully extended position, is wholly positioned outside the inner cavity.

[0013] Preferably, the geared rotary actuator assembly includes at least two geared rotary actuators and two geared rotary actuators each are grouped together into a respective geared rotary actuator group for driving one high-lift device.

[0014] Preferably, the geared rotary actuator arrangement further comprises a drive unit providing mechanical power for driving the geared rotary actuator assembly Preferably, the geared rotary actuator assembly includes a spanwise drive train having at least one spanwise straight drive shaft, which mechanically couples two adjacent geared rotary actuators.

[0015] Preferably, the geared rotary actuator assembly includes a first geared rotary actuator and a second geared rotary actuator, wherein the first geared rotary actuator is mechanically coupled to the drive unit.

[0016] Preferably, the first geared rotary actuator is mechanically coupled to the drive unit via a pivotable drive shaft.

[0017] Preferably, the second geared rotary actuator is mechanically coupled to the first geared rotary actuator via a spanwise straight drive shaft.

[0018] Preferably, the drive unit is arranged spanwise between adjacent geared rotary actuators associated with one high-lift device

[0019] Preferably, the drive unit is arranged on the same axis as the geared rotary actuator in a spanwise direction.

[0020] Preferably, the drive unit is arranged aft of the geared rotary actuator.

[0021] Preferably, the drive unit is arranged below the geared rotary actuator.

[0022] Preferably, the drive unit is arranged aft and below of the geared rotary actuator.

[0023] Preferably, the drive unit is arranged adjacent to the geared rotary actuator in a spanwise direction or chordwise direction.

[0024] Preferably, the drive unit is configured to be arranged predominantly, in particular entirely, within an upper half of the inner cavity in the fully retracted position.

[0025] Preferably, the drive unit is configured to be arranged partially, in particular predominantly, within a lower half of the inner cavity in the fully extended position.

[0026] Preferably, the drive unit is configured to be arranged within the inner cavity, when in the fully retracted position, in the fully extended position and when moving between said positions.

[0027] Preferably, the drive unit is configured to be arranged predominantly, in particular entirely, within a lower half of the inner cavity in the fully retracted position.

[0028] Preferably, the drive unit is configured to be arranged partially outside inner cavity in the fully extended position.

[0029] Preferably, the drive unit is configured to be arranged to protrude downward through a cut-out of the fixed leading edge member.

[0030] Preferably, the drive unit is attached to the actuator assembly, so as to be simultaneously movable.

[0031] Preferably, the drive unit has at least one motor for driving the geared rotary actuator.

[0032] Preferably, the drive unit has at least one electric motor for driving the geared rotary actuator.

[0033] Preferably, the drive unit has at least one hydraulic motor for driving the geared rotary actuator.

[0034] Preferably, one or each motor is mechanically coupled to two adjacent geared rotary actuators associated with one high-lift device, in particular via a spanwise straight drive shaft.

[0035] Preferably, one or each motor is arranged aft of and adjacent to the geared rotary actuator when viewed in a top view.

[0036] Preferably, one or each motor is arranged aft of and below the geared rotary actuator and adjacent to the geared rotary actuator when viewed in a top view.

[0037] Preferably, one or each motor is arranged on the same axis as the geared rotary actuator in a spanwise direction.

[0038] There is also provided an aircraft comprising wing assembly according to the invention.

[0039] The invention allows for a GRA to be integrated into the lever architecture. The stroke of the GRA may be maximized using the preferred configurations, thereby increasing efficiency. This may be achieved due to a reduction of the required forces by increasing travel, thus reducing actuation momentum. As a result gear sizes within the GRA and the overall size of the GRA may be reduced. Consequently, weight and space efficiency are improved.

[0040] Embodiments of the invention are described in more detail with reference to the accompanying schematic drawings: Fig. 1depicts an embodiment of an aircraft; Fig. 2depicts an embodiment of an actuator arrangement; Fig. 3depicts a cross-section of the actuator arrangement of Fig. 2 in the fully retracted and extended positions; Fig. 4depicts a cross-section of the actuator arrangement of Fig. 2 in the fully retracted position; Fig. 5depicts a cross-section of the actuator arrangement of Fig. 2 in the fully extended position; Fig. 6depicts a cross-section of another embodiment of an actuator arrangement in the fully retracted and extended positions; Fig. 7depicts a top view of the actuator arrangement of Fig. 6 in the fully retracted (upper) and extended positions (lower); Fig. 8depicts a cross-section of another embodiment of an actuator arrangement in the fully retracted and extended positions; Fig. 9depicts a top view of the actuator arrangement of Fig. 8 in the fully retracted position; Fig. 10depicts a variant of the actuator arrangement of Fig 8; Fig. 11depicts a cross-section of another embodiment of an actuator arrangement in the fully retracted and extended positions; Fig. 12depicts a variant of the actuator arrangement of Fig. 11; and Fig. 13depicts a top view of the actuator arrangement of Fig. 12 in the fully retracted position.

[0041] Referring to Fig. 1, an embodiment of an aircraft 10 is depicted. In a known manner, the aircraft 10 comprises a fuselage 12, a vertical tail plane 14 and a horizontal tail plane 16. Furthermore, the aircraft 10 comprises a wing assembly 18, which comprises at least one high-lift device 20, such as a slat 22.

[0042] Referring now to Figs. 2 to 5, an actuator arrangement 24 is configured to move the high-lift device 20 between a fully retracted position (Fig. 4) and a fully extended position (Fig. 5).

[0043] As depicted more closely in Fig. 2, the high-lift device 20 is movably attached to a fixed leading edge member 26 (Fig. 3) using a plurality of rails 28, which are supported by roller bearings 30. The rails 28 are attached to the high-lift device 20 via a lever assembly 32.

[0044] In the present embodiment, the actuator arrangement 24 comprises two fixed leading edge levers 34. The fixed leading edge lever 34 is mechanically coupled to the fixed leading edge member 26.

[0045] Furthermore, the actuator arrangement 24 comprises a high-lift device lever 36. The high-lift device lever 36 is coupled to the high-lift device 20.

[0046] Furthermore, the actuator arrangement 24 comprises an actuator assembly 38. The actuator assembly 38 is configured for driving the fixed leading edge lever 34 and the high-lift device lever 36 relative to each other, so as to extend and retract the high-lift device 20.

[0047] The actuator assembly 38 comprises at least one actuator 40. The actuator 40 is preferably a geared rotary actuator 42.

[0048] The fixed leading edge member 26 comprises in manner known per se an outer skin 44 and a plurality of ribs 46, which support the outer skin 44. Adjacent ribs 46 and the outer skin 44 define an inner cavity 48 of the fixed leading edge member 26.

[0049] Furthermore, the outer skin 44 comprises so-called D-nose cut-outs 50, which allow extending and retracting the high-lift device 20 via the actuator arrangement 24 and the rails 28.

[0050] In this embodiment, the actuator 40 is arranged predominately inside the inner cavity 48, when in the fully retracted position (Fig. 4). Furthermore, the actuator 40 is arranged predominately in an upper half of the inner cavity 48, when in the fully retracted position.

[0051] In order to extend the high-lift device 20 the actuator arrangement 24 is operated. In doing so, the actuator 40 moves the fixed leading edge lever 34 relative to the high-lift device lever 36.

[0052] As indicated in Figs. 4 and 5, the fixed leading edge lever 34 and the high-lift device lever 36 stretch in the forward aft direction. In other words the angle between the fixed leading edge lever 34 and the high-lift device lever 36 is acute at the beginning and increases to be more than 90 degrees in the extended position (Fig. 5). During the movement of the high-lift device 20, the actuator 40 itself follows the movement along a circular arc section 52 until the actuator 40 is arranged entirely outside the inner cavity 48, when in the fully extended position. Thus, the actuator 40 rotates about a rotational axis 53. The rotational axis 53 is defined by the mounting point of the fixed leading edge lever 34.

[0053] It should be noted that in the following further embodiments are only described in so far as they differ from the embodiment described above.

[0054] Referring to Figs. 6 and 7 the actuator arrangement 24 comprises a plurality of actuators 40. Each actuator 40 has an input shaft 54 and an output shaft 56.

[0055] Furthermore, the actuator arrangement 24 comprises a drive unit 58. The drive unit 58 may be hydraulic or electric in nature.

[0056] The actuator arrangement 24 comprises a drive train formed by a plurality of straight drive shafts 62, which are aligned substantially along the spanwise direction.

[0057] The drive unit 58 may be fixed in place and be connected to a first actuator 64 using an initial drive shaft 66 and universal joints 68. Splines 70 may be used to transfer the torque.

[0058] Furthermore, the actuator assembly 38 comprises a second actuator 72 which is associated with the same high-lift device 20 as the first actuator 64. The first actuator 64 and the second actuator 72 thereby form an actuator group 74, which is associated with the same high-lift device 20.

[0059] In this embodiment a connecting drive shaft 76 is mechanically coupled to the output shaft 56 of the first actuator 64 and to the input shaft 54 of the second actuator 72.

[0060] In the case of a plurality of high-lift devices 20, the output shaft 56 of the second actuator 72 is connected to a further actuator group 78 via a further drive shaft 80.

[0061] As can be seen from Fig. 7, this pattern is repeated until all high-lift devices 20 and their respective actuator group 74 are mechanically connected to the drive unit 58.

[0062] As can be seen from Fig. 6, the actuator 40 is arranged in its entirety within the inner cavity 48, when in the fully retracted position, whereas the actuator 40 predominately protrudes outside the inner cavity 48 at the bottom in the fully extended position. The actuator 40 thus extends through one of the D-nose cut-outs 50.

[0063] Referring now to Figs. 8 and 9, the drive unit 58 comprises an electric motor 82. As can be seen from Fig. 9 in particular, each electric motor 82 is arranged on the axis defined by the actuator 40. Here, each actuator 40 has its own electric motor 82.

[0064] As illustrated in Fig. 8, the movement of the actuator or the actuator arrangement 24 is substantially the same as the movement in the previous embodiment.

[0065] Referring to Fig. 10, a variant of the previous actuator arrangement 24 (Fig. 8) is depicted. In this variant, an actuator group 74 are driven by a single electric motor 82, which is connected to the respective actuators 40 using a drive shaft 62.

[0066] Referring now to Fig. 11, again each actuator 40 is driven by the drive unit 58 individually. As can be seen from Fig. 11, in the fully retracted position, the actuator 40 is arranged in its entirety within the inner cavity 48, as well as the drive unit 58.

[0067] In particular, the actuator 40 is arranged in an upper half of the inner cavity 48, whereas the drive unit 58 is arranged in a lower half of the inner cavity 48, when in the fully retracted position.

[0068] In the fully extended position, the actuator 40 is predominately protruding outside of the fixed leading edge member 26, whereas the drive unit 58 is still predominately accommodated within the inner cavity 48.

[0069] Similarly, in the variant depicted in Fig. 12, both the actuator 40 and the drive unit 58 are arranged in an upper half of the inner cavity 48 in the fully retracted position, whereas in the fully extended position, the actuator 40 protrudes outside the inner cavity 48 and the drive unit 58 is entirely accommodated within the inner cavity 48.

[0070] With the described configurations of the actuator arrangement 24 the actuators 40, such as geared rotary actuators 42, can be integrated more easily into the small space provided by fixed leading edge member 26 and the high-lift device 20.

[0071] In particular, the stroke of the actuator 40 may be maximized which allows an increase in efficiency due to a reduction of required forces for moving the high-lift device 20. Due to the lower requirements the overall size of actuators 40 may be reduced so that weight and space efficiency are improved. Furthermore, the size of the D-nose cut-out 50 may be reduced using a preferred actuator arrangement 24.

[0072] In order to improve space allocation, reduce weight and increase aerodynamic performance in high-lift devices (20), an actuator arrangement (24) for a fixed leading edge member (26) is proposed. The fixed leading edge member (26) has an inner cavity (48) defined by the outer skin (44) and ribs (46). The actuator arrangement (24) comprises at least one geared rotary actuator (42) which moves relative to the other parts along a circular arc section (52) during extending and retracting of the high-lift device (20) between a fully retracted position and a fully extended position. In the fully retracted position, the geared rotary actuator (42) is predominantly accommodated within the inner cavity (48) and in the extended position the geared rotary actuator (42) is predominantly positioned outside the inner cavity (48), preferably protruding through a D-nose cut-out (50).List of reference signs:

[0073] 10aircraft 12fuselage 14vertical tail plane 16horizontal tail plane 18wing assembly 20high-lift device 22slat 24actuator arrangement 26fixed leading edge member 28rail 30roller bearing 32lever assembly 34fixed leading edge member lever 36high-lift device lever 38actuator assembly 40actuator 42geared rotary actuator 44outer skin 46rib 48inner cavity 50D-nose cut-out 52circular arc section 53rotational axis 54input shaft 56output shaft 58drive unit 60drive train 62drive shaft 64first actuator 66initial drive shaft 68universal joint 70spline 72second actuator 74actuator group 76connecting shaft 78further actuator group 80further drive shaft 82electric motor

Claims

1. A wing assembly (18) for an aircraft (10), the wing assembly (18) comprising a fixed leading edge member (26), a high-lift device (20) movably attached to the fixed leading edge member (26), and an actuator arrangement (24), the actuator arrangement (24) comprising: - a fixed leading edge lever (34) attached to the fixed leading edge member (26) at a mounting point (53), - a high-lift device lever (36) attached to the high-lift device (20), and - an actuator assembly (38) that is configured for driving the fixed leading edge lever (34) and the high-lift device lever (36) relative to each other, so as to allow movement of the high-lift device (20) between a fully retracted position and a fully extended position, wherein the fixed leading edge member (26) has an inner cavity (48) that is defined at least in part by an outer skin (44) and a rib (46), wherein the actuator arrangement (24) is configured for extending and retracting the high-lift device (20), the actuator assembly (38) including at least one geared rotary actuator (42), wherein the actuator assembly (38) is configured such that the geared rotary actuator (42) is movable during extending and retracting of the high-lift device (20) between a fully retracted position, in which the geared rotary actuator (42) is predominantly accommodated within the inner cavity (48), and a fully extended position, in which the geared rotary actuator (42) is predominantly positioned outside the inner cavity (48), wherein the geared rotary actuator (42) is rotatable about a rotational axis that is defined by the mounting point (53) of the fixed leading edge lever (34).

2. The wing assembly (18) according to any of the previous claims, wherein the geared rotary actuator (42) is movable along a circular arc section (52) in a forward direction during extending of the high-lift device (20) and / or in an aft direction during retracting of the high-lift device (20).

3. The wing assembly (18) according to any of the previous claims, wherein the geared rotary actuator (42), when in the fully retracted position, is wholly accommodated within the inner cavity (48).

4. The wing assembly (18) according to any of the previous claims, wherein the geared rotary actuator (42), when in the fully extended position, is wholly positioned outside the inner cavity (48).

5. The wing assembly (18) according to any of the previous claims, wherein the actuator assembly (38) includes at least two actuators and two actuators each are grouped together into a respective actuator group (74) for driving one high-lift device (20).

6. The wing assembly (18) according to any of the previous claims, further comprising a drive unit (58) providing mechanical power for driving the actuator assembly (38), wherein the actuator assembly (38) includes a spanwise drive train (60) having at least one spanwise straight drive shaft (62), which mechanically couples two adjacent actuators (40).

7. The wing assembly (18) according to claim 6, wherein the actuator assembly (38) includes a first actuator (64) and a second actuator (72), wherein the first actuator (64) is mechanically coupled to the drive unit (58).

8. The wing assembly (18) according to claim 7, wherein the first actuator (64) is mechanically coupled to the drive unit (58) via a pivotable drive shaft (62).

9. The wing assembly (18) according to claim 7 or 8, wherein the second actuator (72) is mechanically coupled to the first actuator (64) via a spanwise straight drive shaft (62).

10. The wing assembly (18) according to any of the previous claims, further comprising a or the drive unit (58) providing mechanical power for driving the actuator assembly (38), wherein the drive unit (58) is arranged spanwise between adjacent actuators (40) associated with one high-lift device (20).

11. The wing assembly (18) according to any of the previous claims, further comprising a or the drive unit (58) providing mechanical power for driving the actuator assembly (38), wherein the drive unit (58) is arranged on the same axis as the geared rotary actuator (42) in a spanwise direction.

12. The wing assembly (18) according to any of the previous claims, further comprising a or the drive unit (58) providing mechanical power for driving the actuator assembly (38), wherein the drive unit (58) is arranged aft of the geared rotary actuator (42).

13. The wing assembly (18) according to any of the previous claims, further comprising a or the drive unit (58) providing mechanical power for driving the actuator assembly (38), wherein the drive unit (58) is arranged adjacent to the geared rotary actuator (42) in a spanwise direction or chordwise direction.

14. The wing assembly (18) according to any of the previous claims, further comprising a or the drive unit (58) providing mechanical power for driving the actuator assembly (38), wherein the drive unit (58) is attached to the actuator assembly (38), so as to be simultaneously movable.

15. Aircraft (10) comprising a wing assembly (18) according to any of the preceding claims.