A wing for an aircraft is disclosed including a main wing, a leading edge high lift assembly having a leading edge high lift body, and a connection assembly movably connecting the leading edge high lift body to the main wing, wherein the connection assembly includes a drive system that is mounted to the main wing and connected to the leading edge high lift body for driving the leading edge high lift body between the retracted position and the extended position. The drive system includes a first drive unit and a second drive unit, the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section coupled to a first connection element and including a first output wheel. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section coupled to a second connection element and including a second output wheel.

A wing for an aircraft is disclosed including a main wing, a leading edge high lift assembly having a leading edge high lift body, and a connection assembly movably connecting the leading edge high lift body to the main wing, wherein the connection assembly includes a drive system that is mounted to the main wing and connected to the leading edge high lift body for driving the leading edge high lift body between the retracted position and the extended position. The drive system includes a first drive unit and a second drive unit, the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section coupled to a first connection element and including a first output wheel. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section coupled to a second connection element and including a second output wheel.

A wireless autopilot system includes a mounting plate for securement onto a flight control surface of an aircraft, an airfoil, and a flight control device. The flight control device is connected to the mounting plate, and an elongated bracket functions as an anti-flutter counterbalance. A servomotor is connected to the airfoil by the elongated bracket, and a controller having a wireless transceiver for communicating with an application on an externally located processor enabled device is located within the main body. Changes in the position of the servomotor during flight are instructed by the application, and result in a change to the orientation of the aircraft.

A flexible pillar for a variable geometry flight control surface including upper skin and lower skins includes an elongate shape elastic element having an and at least a first end and a second end. The flexible pillar can be disposed between the upper skin and the lower skin so the elastic element can be fixed to the upper skin at the first end of the flexible pillar and fixed to the lower skin at the second end of the flexible pillar. The flexible pillar has a rigidity along the longitudinal axis of the flexible pillar that is greater than a rigidity of the flexible pillar in shear along a transverse axis of the flexible pillar, the flexible pillar making it possible to obtain a support having a longitudinal direction and able to transmit forces between its ends without, or with little, deformation longitudinally and to be easily deformed in a transverse direction.

A flexible pillar for a variable geometry flight control surface including upper skin and lower skins includes an elongate shape elastic element having an and at least a first end and a second end. The flexible pillar can be disposed between the upper skin and the lower skin so the elastic element can be fixed to the upper skin at the first end of the flexible pillar and fixed to the lower skin at the second end of the flexible pillar. The flexible pillar has a rigidity along the longitudinal axis of the flexible pillar that is greater than a rigidity of the flexible pillar in shear along a transverse axis of the flexible pillar, the flexible pillar making it possible to obtain a support having a longitudinal direction and able to transmit forces between its ends without, or with little, deformation longitudinally and to be easily deformed in a transverse direction.

A jam detection system for a flap of a wing of an aircraft includes a linkage coupled to the flap and a support of the wing, and a sensor configured to detect a position of at least a portion of the linkage. The sensor is further configured to compare the position of the least a portion of the linkage to a jam threshold to determine if a jam condition exists. The linkage can also be coupled to a carriage moveably coupled to the support.

A joint structure includes a bent portion, a first member configured to be connected rotatably to a mating member, a second member configured to be connected rotatably to an actuator for driving the mating member, and a core shaft. The core shaft has a first connecting portion and a second connecting portion. The core shaft is connected to the first member at the first connecting portion and connected to the second member at the second connecting portion. The joint structure further includes a covering member covering the first connecting portion and the second connecting portion. The bent portion is provided at a position different from the first connecting portion.

A wingless vertical take-off and landing (VTOL) vehicle has a main body including airfoil sections on either side of a central module in which a load may be carried. Articulated forward thrust systems are mounted on a leading edge of the main body and lateral members are located on either side of the main body and form winglets. At least one rear vertical-thrust system may also be provided and, in one embodiment, is mounted in an aperture aft of the central module. The forward thrust systems transition between a vertical flight configuration and a horizontal flight configuration. The lateral members are configured as both vortex-damping members and also to channel backwash from the forward thrust systems over the airfoil formed by the main body.

A wingless vertical take-off and landing (VTOL) vehicle has a main body including airfoil sections on either side of a central module in which a load may be carried. Articulated forward thrust systems are mounted on a leading edge of the main body and lateral members are located on either side of the main body and form winglets. At least one rear vertical-thrust system may also be provided and, in one embodiment, is mounted in an aperture aft of the central module. The forward thrust systems transition between a vertical flight configuration and a horizontal flight configuration. The lateral members are configured as both vortex-damping members and also to channel backwash from the forward thrust systems over the airfoil formed by the main body.

An apparatus for supporting a wing flap of an aircraft includes a support fitting configured to be coupled to a wing of the aircraft. The apparatus also includes a first link, pivotably coupled to the support fitting and configured to be pivotably coupled to the wing flap, and a second link, separably coupled to the support fitting and configured to be pivotably coupled to the wing flap.