A proportional braking system is provided for use with a movable surface which is movable relative to a housing. The proportional braking system includes a variable displacement brake which is configured for displacement toward or away from braking engagement with the movable surface in proportion to an input command and a brake driver which is receptive of data reflective of movements of the movable surface relative to the housing and which issues the input command to the variable displacement brake in accordance with the data.

Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a middle track connected to an aerodynamic surface and configured to move along a plurality of intermediate tracks, wherein one or more inner surfaces of the middle track are configured to interface with one or more outer surfaces of the plurality of intermediate tracks; a plurality of outer tracks, each including a flange and configured to interface with one or more inner surfaces of the plurality of intermediate tracks; and an actuator configured to control a position of the middle track and a position of the plurality of intermediate tracks via a plurality of linkages.

Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a middle track connected to an aerodynamic surface and configured to move along a plurality of intermediate tracks, wherein one or more inner surfaces of the middle track are configured to interface with one or more outer surfaces of the plurality of intermediate tracks; a plurality of outer tracks, each including a flange and configured to interface with one or more inner surfaces of the plurality of intermediate tracks; and an actuator configured to control a position of the middle track and a position of the plurality of intermediate tracks via a plurality of linkages.

A vortex generator arrangement comprising a section that defines an opening to a corresponding cavity, an aircraft airflow modification device disposed within the cavity, and at least one fluidic muscle actuator arrangement coupled to the airflow modification device.

A vortex generator arrangement comprising a section that defines an opening to a corresponding cavity, an aircraft airflow modification device disposed within the cavity, and at least one fluidic muscle actuator arrangement coupled to the airflow modification device.

A flap actuating system for use in an aircraft comprises a carriage for supporting and guiding a flap which is engageable with and translationally movable along at least one linear bearing rail. A linear actuator of the flap actuating system has a linearly actuatable coupling element coupled to the carriage and a drive element configured to linearly actuate the coupling element in a direction substantially parallel to a movement direction of the carriage along the linear bearing rail. The drive element is arranged substantially parallel to the movement direction of the carriage along the linear bearing rail.

A flap actuating system for use in an aircraft comprises a carriage for supporting and guiding a flap which is engageable with and translationally movable along at least one linear bearing rail. A linear actuator of the flap actuating system has a linearly actuatable coupling element coupled to the carriage and a drive element configured to linearly actuate the coupling element in a direction substantially parallel to a movement direction of the carriage along the linear bearing rail. The drive element is arranged substantially parallel to the movement direction of the carriage along the linear bearing rail.

Various techniques are provided for a winged drone platform. In one example, a drone can be provided. The drone can include a drone body, a plurality of wings, a plurality of tiling propeller assemblies, and a drone controller. The wings can be coupled to the drone body and configured to generate lift when the drone travels in a first travel direction. The tilting propeller assemblies can each be supported by one of the wings, can include a propeller and a propeller powerplant connected to the propeller, and can be configured to move between at least a first position and a second position. The drone controller can provide instructions to the tilting propeller assemblies to move between at least the first position and the second position. Additional systems and related methods are also provided.

A wing leading-edge device is disclosed having a slat body having a front side with a forward skin and a back side with a rearward skin, and at least a drive arrangement having at least one lug and a slat track, wherein the back side extends between an upper spanwise edge of the forward skin and a lower spanwise edge of the forward skin. The back side is defined by a continuously curved profile contour for receiving a fixed leading edge, and the at least one lug is at least partially arranged between the back side and the front side. The slat track is coupled with the first lug. The connection points to the slat body are shifted far forward to improve the load introduction and reduce moments acting on the drive mechanism.

A linear actuator, for controlling movement of a control surface of an aircraft, includes a screw, a primary load path and secondary nut engaged with the screw, and an engagement member. The engagement member moves from an ambush position, maintained by the primary load path or the secondary nut, to an engaged position, restricting relative movement between the primary load path and the secondary nut. The restricted relative movement may occur in response to free relative axial movement of the primary load path and the secondary nut caused by a failure of the primary load path of the linear actuator. A sensor of the linear actuator is configured to sense the failure of the primary load path and the free relative axial movement of the primary load path and the secondary nut.