Abstract: A linear actuator (100) comprising a stroke axis (102), an actuator rod (104) extending along the stroke axis. The actuator rod comprises: an actuator rod outer surface (110), and a first screw thread (108) on a portion of the actuator rod outer surface; a sleeve (118) positioned around, and coaxial with, the actuator rod. The sleeve comprises: a sleeve inner surface (122), a sleeve outer surface (130), a second screw thread (120) on a portion of the sleeve inner surface, the second screw thread configured to engage with the first screw thread, and a third screw thread (128) on a portion of the sleeve outer surface. A screw nut (136) is provided configured to engage with the third screw thread. At least one motor (142a, 142b) configured to drive the screw nut. In use, the at least one motor applies a torque to the sleeve via the screw nut.

Abstract: A linear actuator (100) comprising a stroke axis (102), an actuator rod (104) extending along the stroke axis. The actuator rod comprises: an actuator rod outer surface (110), and a first screw thread (108) on a portion of the actuator rod outer surface; a sleeve (118) positioned around, and coaxial with, the actuator rod. The sleeve comprises: a sleeve inner surface (122), a sleeve outer surface (130), a second screw thread (120) on a portion of the sleeve inner surface, the second screw thread configured to engage with the first screw thread, and a third screw thread (128) on a portion of the sleeve outer surface. A screw nut (136) is provided configured to engage with the third screw thread. At least one motor (142a, 142b) configured to drive the screw nut. In use, the at least one motor applies a torque to the sleeve via the screw nut.

Abstract: An aircraft control surface skew and/or loss detection system including an aircraft wing structure having a fixed part and at least two control surface elements wherein the at least two control surface elements are configured to be moveable relative to the fixed part. The detection system also includes a cable operably connected to each of the at least two control surface elements such that a tensile force is applied to the cable upon skew and/or loss of one of the control surface elements. The detections system has a sensor assembly including a first part and a second part, wherein one of the first and second parts has a sensor and wherein the cable is coupled to the second part such that skew and/or loss of one of the control surface elements causes movement of the second part relative to the first part.

Abstract: A system for an aircraft wing including a power drive unit (101), a first actuator (104C) for actuating a first aerodynamic device (103), a second actuator (104A) for actuating a second aerodynamic device (102), a first drive path (109B) configured to operate between the power drive unit (101) and the first actuator (104C), a second drive path (109A) operably connecting the power drive unit (101) and the second actuator (104A), the first drive path (109B) including a lost motion device (108A), the lost motion device (108A) being configured to selectively operably connect the power drive unit (101) to the first actuator (104C) and selectively operably disconnect the power drive unit (101) from the first actuator (104C).

Abstract: A skew detection system for an aircraft flight control surface, the flight control surface being moveable relative to fixed structure of the aircraft by operation of a first gear rack driven by a first gear pinion and by operation of a second gear rack driven by a second gear pinion, the skew detection system including a first sensor arrangement and a second sensor arrangement, the first gear rack having a first set of teeth defining a plurality of first targets, the second gear rack having a second set of teeth defining a plurality of second targets, the plurality of first targets being configured to move relative to the first sensor arrangement and the plurality of second targets being configured to move relative to the second sensor arrangement, the skew detection system including a monitoring device to monitor the output from the first and second sensors and determine whether a skew condition has arisen in the flight control surface.

Abstract: An aircraft control surface skew and/or loss detection system including an aircraft wing structure having a fixed part and at least two control surface elements wherein the at least two control surface elements are configured to be moveable relative to the fixed part. The detection system also includes a cable operably connected to each of the at least two control surface elements such that a tensile force is applied to the cable upon skew and/or loss of one of the control surface elements. The detections system has a sensor assembly including a first part and a second part, wherein one of the first and second parts has a sensor and wherein the cable is coupled to the second part such that skew and/or loss of one of the control surface elements causes movement of the second part relative to the first part.

Abstract: A system for an aircraft wing including a power drive unit (101), a first actuator (104C) for actuating a first aerodynamic device (103), a second actuator (104A) for actuating a second aerodynamic device (102), a first drive path (109B) configured to operate between the power drive unit (101) and the first actuator (104C), a second drive path (109A) operably connecting the power drive unit (101) and the second actuator (104A), the first drive path (109B) including a lost motion device (108A), the lost motion device (108A) being configured to selectively operably connect the power drive unit (101) to the first actuator (104C) and selectively operably disconnect the power drive unit (101) from the first actuator (104C).

Abstract: A control surface element skew and/or loss detection system (100) is provided which combines a cable (168, 178) system linked to movement transducers (120) via mechanical links (114, 116) connecting the fixed wing structure (102) to the control surface elements (106, 112).

Abstract: A control surface element skew and/or loss detection system (100) is provided which combines a cable (168, 178) system linked to movement transducers (120) via mechanical links (114, 116) connecting the fixed wing structure (102) to the control surface elements (106, 112).

Abstract: Systems and methods for providing differential motion to wing high lift devices are disclosed. A system in accordance with one embodiment of the invention includes a wing having a leading edge, a trailing edge, a first deployable lift device with a first spanwise location, and a second deployable lift device with a second spanwise location different than the first. The wing system can further include a drive system having a drive link operatively coupleable to both the first and second deployable lift devices, and a control system operatively coupled to the drive system. The control system can have a first configuration for which the drive link is operatively coupled to the first and second deployable lift devices, and activation of at least a portion of the drive link moves the first and second deployable lift devices together.