An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.

An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.

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.

Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a plurality of outer tracks, wherein each outer track of the plurality of outer tracks include: an inner roller channel; and an outer roller channel positioned above the inner roller channel; an aerodynamic surface connected to a carrier, wherein the carrier includes: a plurality of rollers configured to move within inner roller channels of the plurality of outer tracks; and a carrier rack; a plurality of fixed rollers mounted to a plurality of longitudinal structural elements in an aerodynamic structure, wherein the plurality of fixed rollers are disposed within outer roller channels of the plurality of outer tracks; and a plurality of fixed racks, wherein each fixed rack of the plurality of fixed racks is mounted to a longitudinal structural element of the plurality of longitudinal structural elements.

The invention relates to an aircraft control column, the control column comprising a first shaft and a control lever configured to rotate the first shaft about a first axis through a first angular range [α1; α3] via a mechanical joint having a primary reduction ratio, the control column comprising a braking device configured to brake the first shaft via a first transmission device having a secondary reduction ratio, the secondary reduction ratio being maximum for an angular position, the secondary reduction ratio increasing over the range [α1; α4] and then decreasing over the range [α4; α3] so as to obtain an overall reduction ratio that has a limited amplitude of variation over the first angular range [α1; α3].

The invention relates to an aircraft control column, the control column comprising a first shaft and a control lever configured to rotate the first shaft about a first axis through a first angular range [α1; α3] via a mechanical joint having a primary reduction ratio, the control column comprising a braking device configured to brake the first shaft via a first transmission device having a secondary reduction ratio, the secondary reduction ratio being maximum for an angular position, the secondary reduction ratio increasing over the range [α1; α4] and then decreasing over the range [α4; α3] so as to obtain an overall reduction ratio that has a limited amplitude of variation over the first angular range [α1; α3].

Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

A foldable wing with foldable trailing edge flap, that includes a main wing and a foldable trailing edge flap. The main wing includes a wing supporting skeleton and a plurality of skin supporting ribs. The foldable trailing edge flap includes a plurality of crank-shaped flap supporting ribs, a flexible flap skin, a connecting shaft, and a return spring. The plurality of crank-shaped flap supporting ribs are hinged with lower surfaces of corresponding plurality of skin supporting ribs through the connecting shaft to form a foldable trailing edge flap supporting skeleton that relies on the plurality of skin supporting ribs. The return spring makes an upper surface of a long side of each crank-shaped flap supporting rib attach closely to a lower surface of each skin supporting rib. The flexible flap skin is attached to an upper surface of the foldable trailing edge flap supporting skeleton.