초록 ▼

A high-lift system for a wing of an aircraft is provided. The high-lift system includes movably held high-lift flaps, at least one drive unit, at least one transmission shaft connected to the drive unit, and several actuator devices, distributed on the transmission shaft and connected to the high-li

A high-lift system for a wing of an aircraft is provided. The high-lift system includes movably held high-lift flaps, at least one drive unit, at least one transmission shaft connected to the drive unit, and several actuator devices, distributed on the transmission shaft and connected to the high-lift flaps, for moving the high-lift flaps. The actuator devices each comprise a driven element and a torque limiting means. In one example, the driven elements of two adjacent actuator devices are interconnected in a non-rotational manner with the use of a separate torque transmitting means. If one actuator device is blocked, for example as a result of a defective tooth arrangement or some other defect, the torque to be produced by the intact actuator device increases and triggers its torque limiting means. This ensures synchronous operation and in the case of malfunction prevents damage to or detachment of a flap.

대표청구항 ▼

1. A high-lift system for a wing of an aircraft, comprising: movably held high-lift flaps;at least one drive unit;at least one transmission shaft connected to the drive unit; andseveral actuator devices, distributed on the transmission shaft and connected to the high-lift flaps, for moving the high-

1. A high-lift system for a wing of an aircraft, comprising: movably held high-lift flaps;at least one drive unit;at least one transmission shaft connected to the drive unit; andseveral actuator devices, distributed on the transmission shaft and connected to the high-lift flaps, for moving the high-lift flaps, wherein the actuator devices each include a driven element and a torque limiting means, and the driven elements of two adjacent actuator devices are interconnected in a non-rotational manner with the use of a separate torque transmitting means directly attached to the driven elements of the adjacent actuator devices of two adjacent flaps. 2. The high-lift system of claim 1, wherein the torque transmitting means is a torsion shaft. 3. The high-lift system of claim 2, wherein the torsion shaft is a hollow shaft through which the transmission shaft is fed. 4. The high-lift system of claim 2, wherein the torsion shaft is connected to a driven element on both ends by means of an offset gear arrangement each, wherein the torsion shaft extends at a distance from and parallel to the transmission shaft. 5. The high-lift system of claim 1, wherein high-lift flaps of a wing half are divided into two or more groups with different actuating speeds, and actuator devices of adjacent groups comprise different transmission ratios, and the torque transmitting means is arranged only between driven elements that form part of actuator devices of a common group. 6. The high-lift system of claim 5, wherein between actuator devices that are arranged adjacent to each other and that form part of two different groups of high-lift flaps a torsion shaft at a distance from and parallel to the transmission shaft at both ends of the torsion shaft is connected to the associated driven elements by means of an offset gear arrangement each. 7. The high-lift system of claim 6, wherein the offset gear arrangements of adjacent groups of high-lift flaps have different transmission ratios for taking into account different actuating speeds. 8. The high-lift system of claim 3, wherein a junction of the torsion shaft comprises play to compensate for differences in synchronous operation to a driven element at an end of the torsion shaft, which end is opposite the junction. 9. An aircraft, comprising: a high-lift system for a wing of the aircraft that includes:movably held high-lift flaps;at least one drive unit;at least one transmission shaft connected to the drive unit; andseveral actuator devices, distributed on the transmission shaft and connected to the high-lift flaps to move the high-lift flaps,wherein the actuator devices each include a driven element and a torque limiting means, and the driven elements of two adjacent actuator devices are interconnected in a non-rotational manner with a torsion shaft directly attached to driven elements of the adjacent actuator devices of two adjacent flaps. 10. The aircraft of claim 9, wherein the torsion shaft is a hollow shaft through which the transmission shaft is fed. 11. The aircraft of claim 9, wherein the torsion shaft is connected to a driven element on both ends by means of an offset gear arrangement each, wherein the torsion shaft extends at a distance from and parallel to the transmission shaft. 12. The aircraft of claim 9, wherein high-lift flaps of a wing half are divided into two or more groups with different actuating speeds, and actuator devices of adjacent groups comprise different transmission ratios, and the torsion shaft is arranged only between driven elements that form part of actuator devices of a common group. 13. The aircraft of claim 12, wherein between actuator devices that are arranged adjacent to each other and that form part of two different groups of high-lift flaps the torsion shaft at a distance from and parallel to the transmission shaft at both ends of the torsion shaft is connected to the associated driven elements by means of an offset gear arrangement each. 14. The aircraft of claim 13, wherein the offset gear arrangements of adjacent groups of high-lift flaps have different transmission ratios for taking into account different actuating speeds. 15. The aircraft of claim 10, wherein a junction of the torsion shaft comprises play to compensate for differences in synchronous operation to a driven element at an end of the torsion shaft, which end is opposite the junction.