Example actuator assemblies to deploy aircraft leading edge flaps and seals for aircraft leading edge flaps are described herein. An example apparatus includes an aircraft flap that is movable between a stowed position and a deployed position. The flap includes a top panel. A notch is formed in the top panel and extends into a side of the top panel near a trailing edge of the flap. The example apparatus also includes a seal coupled to the flap. The seal is movable to cover the notch when the flap is in the deployed position.

A spoiling apparatus for triggering a turbulent transition by autonomous disturbance and spoilers. The spoilers are mounted in multiple grooves in the circumferential direction of a navigating body, when a flow autonomously undergoes a turbulent transition, the spoilers remain in the grooves, the surface of the navigating body is free of protrusion, thus causing no additional flow resistance. A rated critical Reynolds number is set, in a case of a reduced flow speed and reduced density, the flow is a laminar flow, at which time the pressure applied to the spoilers by the flow is reduced, and the spoilers are ejected under the effect of compression springs. When ejected, the spoilers disturb the flowing of the bottom layer of the flow, and trigger the laminar flow into a turbulent flow. By setting the rebounding force of the compression springs, the spoiling apparatus is turned on automatically when a disturbance-triggered turbulent transition is required and is turned off when not required, thus implementing the autonomous control of turbulent transitions.

The present application relates to a stopping device, a moving mechanism and an aircraft. The moving mechanism is connected to a stationary structure of the aircraft so as to allow the moving mechanism to move relative to the stationary structure. The stopping device includes a first stopper provided at the moving mechanism and a second stopper provided at the stationary structure, and is configured such that when a drive connection structure of the moving mechanism fails, the first stopper is adapted to abut against the second stopper to limit the moving range of the moving mechanism. At least one of the first stopper and the second stopper includes a buffer region made by modifying its meso-structure and thus has a reduced density to thereby be adapted to reduce a dynamic load generated when the first stopper collides with the second stopper.

Underwing-mounted trailing edge flaps for wings of aircraft are disclosed. A flap pivotally coupled to the wing is movable between a stowed position located along a lower surface of the wing and a deployed position located rearward of a trailing edge of the wing. The flap includes a first edge, a second edge located opposite the first edge, a first surface extending between the first edge and the second edge, and a second surface located opposite the first surface and extending between the first edge and the second edge. The first edge is located rearward of the second edge when the flap is in the stowed position, and forward of the second edge when the flap is in the deployed position. A bullnose pivotally coupled to the flap at a location along the first edge pivots relative to the flap as the flap moves between the stowed and deployed positions.

Underwing-mounted trailing edge flaps for wings of aircraft are disclosed. A flap pivotally coupled to the wing is movable between a stowed position located along a lower surface of the wing and a deployed position located rearward of a trailing edge of the wing. The flap includes a first edge, a second edge located opposite the first edge, a first surface extending between the first edge and the second edge, and a second surface located opposite the first surface and extending between the first edge and the second edge. The first edge is located rearward of the second edge when the flap is in the stowed position, and forward of the second edge when the flap is in the deployed position. A bullnose pivotally coupled to the flap at a location along the first edge pivots relative to the flap as the flap moves between the stowed and deployed positions.

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 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 gurney flap arrangement includes: an airfoil 2 with a trailing edge 6 and an opening 14 in a surface 8 of the airfoil 2; a gurney flap 1 having a first position in which at least a portion of the gurney flap 1 extends through the opening 14 and projects outwardly from the airfoil surface 8, and a second position in which the gurney flap 1 does not project from the airfoil surface 8 or projects outwardly from the airfoil surface 8 to a lesser extent; and a gurney flap actuator 3 for moving the gurney flap 1 between at least the first position and the second position.

A gurney flap arrangement includes: an airfoil 2 with a trailing edge 6 and an opening 14 in a surface 8 of the airfoil 2; a gurney flap 1 having a first position in which at least a portion of the gurney flap 1 extends through the opening 14 and projects outwardly from the airfoil surface 8, and a second position in which the gurney flap 1 does not project from the airfoil surface 8 or projects outwardly from the airfoil surface 8 to a lesser extent; and a gurney flap actuator 3 for moving the gurney flap 1 between at least the first position and the second position.

A lifting surface of an aircraft, comprising a leading edge and a notch located in the leading edge. The notch comprises two walls adapted to be parallel to the direction of the incident flow to the lifting surface and a third wall adapted to face the incident flow to the lifting surface when it is in flight. The lifting surface also comprises a retractable cover element, the notch and the retractable cover element being configured such that when the retractable cover element does not cover the notch, the notch is exposed to the incident flow generating a vortex which increases the lift force of the lifting surface, delaying stall.