Various flight control components can be operated through gearbox driven rotary actuators. In the event of a jam occurring the gearbox, the gearbox can be decoupled from a surrounding support housing to enable free-trailing or limited motion relative to the support housing. The motion may or may not be damped. Decoupling the gearbox enables the flight control component to move to a neutral or non-interfering position even when user control over the component has been lost.

A torque limiter (TL) is provided for torque transmission (TT) to downstream components. The TL includes an input shaft, an output shaft and a torsional spring which is preloadable by a preload torque whereupon the torsional spring is fittable about the output shaft with the output shaft fit about the input shaft. For input shaft rotation, first TT paths proceed from the input shaft to the output shaft through the torsional spring when downstream torque of the downstream components deceeds the preload torque and a second TT path proceeds from the input shaft to an external structure when the downstream torque exceeds the preload torque.

A torque limiter (TL) is provided for torque transmission (TT) to downstream components. The TL includes an input shaft, an output shaft and a torsional spring which is preloadable by a preload torque whereupon the torsional spring is fittable about the output shaft with the output shaft fit about the input shaft. For input shaft rotation, first TT paths proceed from the input shaft to the output shaft through the torsional spring when downstream torque of the downstream components deceeds the preload torque and a second TT path proceeds from the input shaft to an external structure when the downstream torque exceeds the preload torque.

A wing for an aircraft is disclosed having a main wing, a high lift body, and a connection assembly movably connecting the high lift body to the main wing, such that the high lift body can be moved between a retracted position and at least one extended position. The connection assembly includes a drive system having a first drive unit and a second drive unit, wherein the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section drivingly coupled to a first connection element. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section drivingly coupled to a second connection element. The first output section includes a first output wheel and the second output section includes a second output wheel.

An actuator system for actuating movement of a control surface of an aircraft wing includes a common input rail connectable to a means for providing movement to said input rail. The system also includes: a plurality of rotary geared actuators “RGAs”; a common output rail connectable to said control surface; wherein each of said plurality of RGAs is connected to said input rail by an individual input clutch and also connected to said output rail by an individual output clutch, and wherein the input clutch functions independently of the output clutch.

An actuator system for actuating movement of a control surface of an aircraft wing includes a common input rail connectable to a means for providing movement to said input rail. The system also includes: a plurality of rotary geared actuators “RGAs”; a common output rail connectable to said control surface; wherein each of said plurality of RGAs is connected to said input rail by an individual input clutch and also connected to said output rail by an individual output clutch, and wherein the input clutch functions independently of the output clutch.

A rotary geared actuator (RGA) for actuating movement of a first movable surface and a second movable surface. The RGA include an input shaft configured to receive torque in use, and an output shaft comprising means configured to communicate with and move both said first surface and said second surface in use. The actuator may be used in a leading edge high lift architecture for an aircraft wing, or may be used in other applications.

A rotary geared actuator (RGA) for actuating movement of a first movable surface and a second movable surface. The RGA include an input shaft configured to receive torque in use, and an output shaft comprising means configured to communicate with and move both said first surface and said second surface in use. The actuator may be used in a leading edge high lift architecture for an aircraft wing, or may be used in other applications.

Example flap actuation systems and related methods are disclosed herein. An example flap actuation system includes a first actuator, a second actuator, a first drive arm coupled to the first actuator and to a flap, a second drive arm coupled to the second actuator and to the flap, a first cam, and a first output shaft. The first cam is to couple to the first drive to enable the first actuator to actuate the flap via the first drive arm. The example flap actuation system includes a second cam and a second output shaft. The first cam is to be uncoupled from the first drive arm in response to a failure of the first actuator. The second actuator is to actuate the flap via the first drive arm and the second drive arm in response to the failure of the first actuator.

Example flap actuation systems and related methods are disclosed herein. An example flap actuation system includes a first actuator, a second actuator, a first drive arm coupled to the first actuator and to a flap, a second drive arm coupled to the second actuator and to the flap, a first cam, and a first output shaft. The first cam is to couple to the first drive to enable the first actuator to actuate the flap via the first drive arm. The example flap actuation system includes a second cam and a second output shaft. The first cam is to be uncoupled from the first drive arm in response to a failure of the first actuator. The second actuator is to actuate the flap via the first drive arm and the second drive arm in response to the failure of the first actuator.