초록 ▼

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 movabl

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.

대표청구항 ▼

1. A leading edge flap and boundary layer control system for an aircraft wing having a substantially sharp leading edge, said system comprising: said wing having a spanwise slot having front and rear guide walls, said slot located a discrete distance from said leading edge extending from the lowe

1. A leading edge flap and boundary layer control system for an aircraft wing having a substantially sharp leading edge, said system comprising: said wing having a spanwise slot having front and rear guide walls, said slot located a discrete distance from said leading edge extending from the lower aerodynamic surface to the upper aerodynamic surface of said wing; a guide member rotatably mounted to said wing movable from a retracted position to an extended position, said guide member having a first aerodynamic surface defining and acting as a first portion of said lower aerodynamic surface when said guide member is in said retracted position and a second aerodynamic surface adapted to act as an entrance guide for said front guide wall of said slot when said guide member is in said extended position; a flap segment rotatably mounted to said guide member movable from a retracted position to an extended position in conjunction with said movement of said guide member, said flap member having a first aerodynamic surface forming a second portion of said lower aerodynamic surface of said wing when said flap segment is in said retracted position, said flap segment having a second aerodynamic surface adapted to form an aerodynamic extension of said leading edge and cooperating with said second aerodynamic surface of said guide member to form a smooth transition inlet to said slot when in said extended position; first actuation means adapted to move said guide member and said flap segment from said retracted positions to said extended positions; a door member rotatably mounted to said wing adapted to rotate from an extended position to a retracted position, said door member having an upper surface adapted to form a portion of said upper aerodynamic surface of said wing when in said extended position, and to form a portion of said rear wall of said slot when in said retracted position; and second actuation means coupled to said wing and to said door member adapted to move said door member from said extended position to said retracted position. 2. The system as set forth in claim 1 wherein said first acuation means comprises: a first hydraulic actuator rotatably mounted at its first end to said wing and at its second end to said guide member; and a second hydraulic actuator rotatably mounted at its first end to said guide member and it is second end to said flap segment. 3. The system as set forth in claim 2 wherein said second actuation means comprises a third hydraulic actuator rotatably mounted at its first end to said wing and at its second end to said door member. 4. The system as set forth in claim 3 wherein said flap segment serves as a cover for the bottom of said slot when in said retracted position. 5. The system as set forth in claim 4 wherein said first aerodynamic surface of said flap segment covers said slot and said second aerodynamic surface is stored within said slot when said flap segment is in said retracted position. 6. A leading edge flap and boundary layer control system for an aircraft wing having a substantially sharp edge, said system comprising: said wing having a spanwise slot said slot having front and rear guide walls, said slot located a discrete distance from said leading edge extending from the lower aerodynamic surface to the upper aerodynamic surface of said wing; a guide member rotatably mounted to said wing movable from a retracted position stored within said slot to an extended position, said guide member having a first aerodynamic surface defining and acting as a first portion of said lower aerodynamic surface when said guide member is in said retracted position and a second aerodynamic surface adapted to act as an entrance guide for said front guide wall of said slot when said guide member is in said extended position; a flap segment rotatably mounted to said guide member movable from a retracted position to an extended position in conjunction with said movement of said guide member, said flap member having a first aerodynamic surface forming a second portion of said lower aerodynamic surface of said wing covering said slot when said flap segment is in said retracted position, said flap segment having a second aerodynamic surface adapted to be stored within said slot when said flap segment is in said retracted position and to form an aerodynamic extension of said leading edge and cooperating with said second aerodynamic surface of said guide member to form a smooth transition inlet to said slot when in said extended position; first actuation means adapted to move said guide member and said flap segment from said retracted positions to said extended positions; a door member rotatably mounted to said wing adapted to rotate from an extended position to a retracted position, said door member having an upper surface adapted to form a portion of said upper aerodynamic surface of said wing when in said extended position, and to form a portion of said rear wall of said slot when in said retracted position; and second actuation means coupled to said wing and to said door member adapted to move said door member from said extended position to said retracted position.