| 摘要 |
The invention is a leading edge flap and boundary layer control system for an aircraft wing having a substantially sharp leading edge. The system comprises the wing 10 incorporating a spanwise slot 26 having front and rear guide walls 28, 30. A guide member 44 is rotatably mounted in the wind movable from a retracted position to an extended position. A flap segment 54 is rotatably mounted to the guide member 44 and is movable from a retracted position to an extended position in conjunction with the guide member 44. The flap segment incorporates an aerodynamic surface adapted to form an aerodynamic extension of the leading edge 16 of the wing 10 and, furthermore, cooperating with the guide member 44 to form a smooth transition inlet to the front guide wall 28 of the slot 26. Actuators 66, 72 are provided to actuate the guide member 44 and flap segment 54 from their retracted positions to their extended positions. A door member is rotatably mounted to the rear wall of the slot moveable from an extended position to a retracted position. An actuator 90 is provided to move the door member 62 to the retracted position where it forms a portion of the rear wall 30 of the slot 26. Thus, during normal flight conditions the sharp leading edge and smooth aerodynamic contour is maintained. For landing and takeoff purposes, the flap segment 54 and guide member 44 are extended and the door member 62 is retracted producing an aerodynamic extension of the leading edge and a smooth entrance to the slot is provided for energizing the boundary layer near the leading edge.
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