[특허]High lift longitudinal axis control system

Libby,John

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High lift longitudinal axis control system

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-009/16 B64C-009/00
미국특허분류(USC)	244/216; 244/198; 244/201
출원번호	US-0047194 (2005-01-31)
등록번호	US-7367532 (2008-05-06)
발명자 / 주소	Libby,John
출원인 / 주소	Libby,John
대리인 / 주소	Ryan Kromholz & Manion, S.C.
인용정보	피인용 횟수 : 6 인용 특허 : 9

초록

A bipartite, full span airplane flap system having an inboard flap portion and an outboard flap portion, wherein the outboard flap portion includes an integrated aileron mounted on its substantially equivalent spanwise length.

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I claim: 1. An airplane wing having a trailing part and a flap comprising: a full span flap having positions including an extreme retracted position and an extreme extended position, said full span flap having two parts, an inboard flap portion and an outboard flap portion; said inboard flap portion comprising an inboard flap portion leading part and an inboard flap portion trailing part; said outboard flap portion comprising an outboard flap portion leading part and an outboard flap portion trailing part having a fixed distance therebetween; a linkage with a fore portion and aft portion extending from wing support structure to the leading part of the flap, a linkage extending from wing support structure to an actuation point located such that the actuation point remains in a constant position with respect to the leading part of the flap when the flap translates between a first and a second position to create a functional slot between a bottom surface of the leading part of the flap and a bottom surface of the wing trailing part to draw a portion of higher pressure air from the bottom surface of the wing through the slot to distribute the higher pressure air over a top surface of the flap; means for imparting relative movement between the leading and trailing parts of the flap through movement of the actuation point with respect to the leading part of the flap once the flap translates further toward the second position, wherein the means for imparting relative movement between the leading and trailing parts of the flap through the actuation point includes means for converting movement of the actuation point into a rearward movement of a control linkage; said outboard flap portion further including an independently operable, integrated aileron portion, said aileron portion having an aileron portion leading part and an aileron portion trailing part; said aileron portion leading part being pivotally attached to said outboard flap portion trailing part such that said aileron portion leading part is mounted adjacent said outboard flap portion trailing part and said aileron portion extending along said outboard flap portion substantially spanwise length; and said outboard flap portion trailing part and all of said integrated aileron portion being located aft of said wing trailing part when said full span flap is in an extreme retracted position. 2. An airfoil having a trailing edge and a full span, bipartite flap, said bipartite flap having positions including an extreme retracted position and an extreme extended position, said bipartite flap adapted to translate between a first and a second position to create a functional slot between a bottom surface of a leading part of said bipartite flap and a bottom surface of the airfoil trailing edge to draw a portion of higher pressure air from the bottom surface of the airfoil through the slot to distribute the higher pressure air over a top surface of the bipartite flap; said bipartite flap including an inboard flap portion and an outboard flap portion; said inboard flap portion including an inboard flap portion leading edge and an inboard flap portion trailing edge; said outboard flap portion including an outboard flap portion leading edge and an outboard flap portion trailing edge; said outboard flap portion including a flap member and an aileron member, said flap member having a flap member leading edge and a flap member trailing edge having a fixed distance therebetween, said aileron member having an aileron member lead edge and an aileron member trailing edge; said aileron member being pivotally mounted such that said aileron member leading edge is located adjacent said flap member trailing edge; said flap member trailing edge of said outboard flap portion and all of said aileron member being located aft of said airfoil trailing edge when said bipartite flap is in an extreme retracted position; means for imparting relative movement between the leading and trailing edge of each of said inboard flap portion and said outboard flap portion; said means for imparting relative movement comprises at least a first linkage member and a second linkage member, each of said first linkage member and said second linkage member being disposed for reciprocating push pull movement transversely relative to a substantially spanwise axis of said airfoil, each respective first linkage member and said second linkage member having a first end and a second end, said first end of said first linkage member being pivotally attached to said inboard flap leading edge and said first end of said second linkage member being pivotally attached to said flap member leading edge for reciprocal movement of said flap member leading edge and said inboard flap leading edge relative to said spanwise axis; and a pivotally operable bell crank lever including a pair of normally disposed, bifurcated arms, the second end of at least one of said first linkage member and said second linkage member being pivotally attached to one of said arms; said bellcrank member including another arm pivotally attached to an operating rod, said operating rod being arranged for reciprocating axial movement for pivotal operation of said bellcrank and consequent reciprocating axial movement of said linkage member. 3. The airfoil of claim 2 further including control means for said means for imparting relative movement. 4. The airfoil of claim 3 wherein said control means for said means for imparting relative movement comprises: a reciprocally moveable linear actuator; and a prime mover for operating said linear actuator. 5. The airfoil of claim 2 wherein only said outboard flap portion of said full span, bipartite flap is partitioned spanwise to provide a flap member and an aileron member. 6. An airfoil having a trailing edge and a full span, bipartite flap, said bipartite flap having positions including an extreme retracted position and an extreme extended position, said bipartite flap adapted to translate between a first and a second position to create a functional slot between a bottom surface of a leading part of said bipartite flap and a bottom surface of the airfoil trailing edge to draw a portion of higher pressure air from the bottom surface of the airfoil through the slot to distribute the higher pressure air over a top surface of the bipartite flap; said bipartite flap including an inboard flap portion and an outboard flap portion; said inboard flap portion including an inboard flap portion leading edge and an inboard flap portion trailing edge; said outboard flap portion including an outboard flap portion leading edge and an outboard flap portion trailing edge; said outboard flap portion including a flap member and an aileron member, said flap member having a flap member leading edge and a flap member trailing edge having a fixed distance therebetween, said aileron member having an aileron member lead edge and an aileron member trailing edge; said aileron member being pivotally mounted such that said aileron member leading edge is located adjacent said flap member trailing edge; said flap member trailing edge of said outboard flap portion and all of said aileron member being located aft of said airfoil trailing edge when said bipartite flap is in an extreme retracted position; means for imparting relative movement between the leading and trailing edge of each of said inboard flap portion and said outboard flap portion; control means for said means for imparting relative movement, wherein said control means for said means for imparting relative movement comprises a reciprocally moveable linear actuator and a prime mover for operating said linear actuator; and said means for imparting relative movement includes a pulley-operated, endwise movable, cable having a first end and a second end, said cable being supported by a drive pulley and being attached at each of said first end and said second end to accurately spaced locations on said drive pulley, said cable being further moveably supported by spaced apart idler pulleys and being attached to said linear actuator for reciprocal movement therewith. 7. The airfoil of claim 6 wherein said drive pulley is further attached to a bellcrank lever. 8. An airplane wing comprising: a main airfoil, said main airfoil having a leading edge and a trailing edge; a full span flap structure, said full span flap structure including an inboard flap portion and an outboard flap portion; said inboard flap portion having an inboard flap leading edge and an inboard flap trailing edge; said inboard flap leading edge being movably located adjacent said trailing edge of said main airfoil; said outboard flap portion being partitioned spanwise to provide a flap member and an aileron member, said flap member having a flap member leading edge and a flap member trailing edge having a fixed distance therebetween; said flap member leading edge being movably located adjacent said trailing edge of said main airfoil, said aileron member being pivotally mounted adjacent to said flap member trailing edge; adjustable mounting means on said wing for said full span flap structure; control means for said adjustable mounting means to selectively move the respective axis of each of said outboard flap portion and said inboard flap portion in a generally aft and substantially downward direction to positions between and including an extreme retracted position in which said flap member trailing edge of said outboard flap portion and all of said aileron member are located aft of said airfoil trailing edge, and an extreme extended position of substantial aft displacement of the inboard flap structure and the outboard flap structure from the main airfoil in which said inboard flap leading edge and a substantially spanwise portion of said trailing edge of said main airfoil cooperate to form a first slot therebetween, and said flap member leading edge and a substantially spanwise portion of said trailing edge of said main airfoil cooperate to form a second slot therebetween, the second slot comprising a functional slot between a bottom surface of said flap member leading edge and a bottom surface of said trailing edge of said main airfoil to draw a portion of higher pressure air from the bottom surface of said main airfoil through the second slot to distribute the higher pressure air over a top surface of said flap member; said adjustable mounting means comprises at least a first linkage member and a second linkage member, each of said first linkage member and said second linkage member being disposed for reciprocating push pull movement transversely relative to a substantially spanwise axis of said wing, each respective first linkage member and said second linkage member having a first end and a second end, said first end of said first linkage member being pivotally attached to said inboard flap leading edge and said first end of said second linkage member being pivotally attached to said flap member leading edge for reciprocal movement of said flap member leading edge and said inboard flap leading edge relative to said spanwise axis; and a pivotally operable bell crank lever including a pair of normally disposed, bifurcated arms, the second end of at least one of said first linkage member and said second linkage member being pivotally attached to one of said arms; said bellcrank member including another arm pivotally attached to an operating rod, said operating rod being arranged for reciprocating axial movement for pivotal operation of said bellcrank and consequent reciprocating axial movement of said linkage member. 9. The airplane wing of claim 8 wherein said control means for said adjustable mounting means comprises: a reciprocally moveable linear actuator; and a prime mover for operating said linear actuator. 10. An airplane wing comprising: a main airfoil, said main airfoil having a leading edge and a trailing edge; a full span flap structure, said full span flap structure including an inboard flap portion and an outboard flap portion; said inboard flap portion having an inboard flap leading edge and an inboard flap trailing edge; said inboard flap leading edge being movably located adjacent said trailing edge of said main airfoil; said outboard flap portion being partitioned spanwise to provide a flap member and an aileron member, said flap member having a flap member leading edge and a flap member trailing edge having a fixed distance therebetween; said flap member leading edge being movably located adjacent said trailing edge of said main airfoil, said aileron member being pivotally mounted adjacent to said flap member trailing edge; adjustable mounting means on said wing for said full span flap structure; control means for said adjustable mounting means to selectively move the respective axis of each of said outboard flap portion and said inboard flap portion in a generally aft and substantially downward direction to positions between and including an extreme retracted position in which said flap member trailing edge of said outboard flap portion and all of said aileron member are located aft of said airfoil trailing edge, and an extreme extended position of substantial aft displacement of the inboard flap structure and the outboard flap structure from the main airfoil in which said inboard flap leading edge and a substantially spanwise portion of said trailing edge of said main airfoil cooperate to form a first slot therebetween, and said flap member leading edge and a substantially spanwise portion of said trailing edge of said main airfoil cooperate to form a second slot therebetween, the second slot comprising a functional slot between a bottom surface of said flap member leading edge and a bottom surface of said trailing edge of said main airfoil to draw a portion of higher pressure air from the bottom surface of said main airfoil through the second slot to distribute the higher pressure air over a top surface of said flap member; said control means for said adjustable mounting means comprises a reciprocally moveable linear actuator and a prime mover for operating said linear actuator; and said adjustable mounting means includes a pulley-operated, endwise movable, cable having a first end and a second end, said cable being supported by a drive pulley and being attached at each of said first end and said second end to arcuately spaced locations on said drive pulley, said cable being further moveably supported by spaced apart idler pulleys and being attached to said linear actuator for reciprocal movement therewith. 11. The airplane wing of claim 10 wherein said drive pulley is further attached to a bellcrank lever.

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이 특허를 인용한 특허 피인용횟수: 6

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특허 상세정보

High lift longitudinal axis control system

초록

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청구항
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이 특허에 인용된 특허 (9)

이 특허를 인용한 특허 피인용횟수: 6

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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특허 상세정보

High lift longitudinal axis control system

초록

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이 특허에 인용된 특허 (9)

이 특허를 인용한 특허 피인용횟수: 6

IPC 상위 출원인

상세정보조회

원문조회

IPC 상세정보(version : 201201)

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