Wing leading edge slat

• US 4,399,970 A
• Filed: 11/13/1980
• Issued: 08/23/1983
• Est. Priority Date: 11/13/1980
• Status: Expired due to Term

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Evans, Arthur
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US06/206,590
• Time in Patent Office: 1,013 Days
• Field of Search: 244/210, 244/213, 244/214, 244/216, 244/218, 244/215, 244/75 R
• US Class Current: 244/214
• CPC Class Codes: B64C 9/24 by single flap
• CPC Class Codes: Y02T 50/30 Wing lift efficiency

Abstract

A wing leading edge slat actuation and positioning system, wherein a slat panel is connected to one end of an extensible track member which is supported and guided at its other end, by rollers mounted to fixed structure in the leading edge section of the wing. The actuation and positioning system comprises a unified drive and a programming mechanism which is connected to the slat panel and functions to combine an aerodynamic slot opening or closure operation with a slat extension drive mechanism. The unified drive and programming mechanism comprises a contoured camtrack somewhat in the shape of an S-camtrack and having a roller follower which is connected to a link and drive arm; and this combination allows synchronization of slat actuation with programming control of slat angle-of-deflection and aerodynamic slot opening or closure.

Claims

1. A mechanism for extending and positioning a pair of spanwise adjacent high-lift devices relative to an airfoil, comprising:

a pair of carrier tracks extending chordwise of said airfoil for supporting each of said high-lift devices;

said carrier tracks being supportably guided toward one end by rollers mounted to said airfoil and pivotally connected at the other end to said high-lift devices for support thereof;

a structural rib member extending chordwise of said airfoil and being positioned between said pair of spanwise adjacent high-lift devices;

a pair of chordwise integrated linkage mechanisms spaced apart spanwise and arranged on either side of said rib member for operative connection to each of said high-lift devices;

a camtrack cut transversely through said rib member and formed structurally integral therewith;

a roller follower having its rotational axis aligned transversely to said chordwise extending rib member and extending through said camtrack for pivotal connection at its ends to each of said chordwise integrated linkage mechanisms, thereby providing a direct interconnection between said adjacent high-lift devices for synchronization of extension actuation with position programming control of angle-of-deflection of said high-lift device relative to the airfoil.

2. The mechanism for extending and positioning a pair of spanwise adjacent high-lift devices relative to an airfoil as set forth in claim 1, wherein:

said camtrack and said pair of chordwise integrated linkage mechanisms, in combination, extending said pair of high lift devices, from a retracted stowed position whereat they form the leading edge nose structure of said airfoil, to a first forward and downward extended operation position whereat a continuous upper surface contour is formed between said high-lift devices and the relatively fixed leading edge portion of said airfoil, and to a second further extended operating position whereat an aerodynamic slot is formed between said high-lift devices and the relatively fixed leading edge portion of said airfoil.

3. A mechanism for extending and positioning a pair of spanwise adjacent high-lift devices relative to an airfoil, comprising:

a pair of carrier tracks extending chordwise in said airfoil and being pivotally connected at their one end to said high-lift devices;

cylindrical rollers axially mounted to said airfoil for rolling support of the other end portion of said carrier tracks;

a structural rib member extending chordwise of said airfoil and being located between said pair of spanwise adjacent high-lift devices;

a camtrack cut transversely through said rib member and formed structurally integral therewith;

a pair of chordwise integrated linkage mechanisms spaced apart spanwise and arranged on each side of said rib member for operative connection to each of said high-lift devices;

each of said chordwise integrated linkage mechanisms comprising, a drive arm mounted to said airfoil for rotation in a chordwise plane, a drive link pivotally connected at one end to the swinging end of said drive arm, and a drive beam extending chordwise and being pivotally connected at one end to the other end of said drive link and being fixedly secured at its other end to one of said high-lift devices;

a roller cam follower having its rotational axis aligned transversely to said chordwise extending rib member and extending through said camtrack for connection at its ends to the pivotal connection between said drive beam and said drive link of each of said chordwise integrated linkage mechanisms, for producing a force vector component to each of said linkage mechanisms along the arcuate track of said camtrack, and thereby providing a direct interconnection between said adjacent high-lift devices for synchronization of extension actuation with position programming control of angle-of-deflection of said high-lift devices relative to said airfoil.

4. The mechanism for extending and positioning a pair of spanwise adjacent high-lift devices relative to an airfoil as set forth in claim 3, wherein:

said camtrack and said pair of chordwise integrated linkage mechanisms, in combination, extending said pair of highlift devices, from a retracted stowed position whereat said pair of high-lift devices form the leading edge nose structure of said airfoil, to a first forward and downward extended operating position whereat a continuous upper surface contour is formed between said high-lift devices and the relatively fixed leading edge portion of said airfoil, and to a second further extended operating position whereat an aerodynamic slot is formed between said high-lift devices and the relatively fixed leading edge portion of said airfoil.

6. The mechanism for extending and positioning a pair of spanwise adjacent high-lift devices relative to an airfoil as set forth in claim 3, wherein:

said camtrack and said pair of chordwise integrated linkage mechanisms, in combination, extending said pair of high lift devices, from a retracted stowed position whereat said pair of high-lift devices form the leading edge nose structure of said airfoil, to a first forward and downward extended operating position whereat a continuous upper surface contour is formed between said high-lift devices and the relatively fixed leading edge portion of said airfoil, and to a second further extended operating position whereat an aerodynamic slot is formed between said high-lift devices and the relatively fixed leading edge portion of said airfoil.

5. A mechanism for extending and positioning a pair of spanwise adjacent high-lift devices relative to the leading edge of an airfoil, comprising:

a pair of carrier tracks extending chordwise fore and aft in said airfoil and being pivotally connected at their fore end to said high-lift devices;

cylindrical rollers axially mounted to said airfoil for rolling support of the aft portion of said carrier tracks;

a structural rib member extending chordwise of said airfoil and being positioned between said pair of spanwise adjacent high-lift devices;

a camtrack cut transversely through said rib member and formed structurally integral therewith;

a pair of chordwise integrated linkage mechanisms spaced apart spanwise and arranged on either side of said rib member for operative connection to each of said high-lift devices;

each of said chordwise integrated linkage mechanisms comprising, a drive arm mounted to said airfoil for rotation in a chordwise plane, a drive link pivotally connected at one end to the swinging end of said drive arm, and a drive beam extending fore and aft chordwise and being pivotally connected at its aft end to the other end of said drive link and being fixedly secured at its fore end to one of said high-lift devices;

a roller cam follower having its rotational axis aligned transversely to said chordwise extending rib member and extending through said camtrack for connection at its ends to the pivotal connection between said drive beam and said drive link of each of said chordwise integrated linkage mechanisms, for producing a force vector component to each of said linkage mechanisms along an arcuate track of said camtrack, and thereby providing a direct interconnection between said adjacent high-lift devices for synchronization of extension actuation with position programming control of angle-of-deflection of said high-lift devices relative to the leading edge of said airfoil.

7. A mechanism for extending and positioning a high-lift device relative to an airfoil, comprising:

a carrier track extending chordwise in said airfoil and being pivotally connected at one end to said high-lift device;

means mounted to said airfoil for supportably guiding the other end portion of said carrier track for chordwise extension movement of said high-lift device relative to said airfoil;

a camtrack spaced spanwise from said carrier track and fixedly mounted chordwise in said airfoil;

a rotary actuator mounted in said airfoil;

a linkage mechanism being in a folded arrangement during a fully retracted position of said high-lift device relative to said airfoil and interconnecting said high-lift device with said camtrack and said rotary actuator;

said rotary actuator in combination with said linkage mechanism, said camtrack and said carrier track, effecting a simultaneously combined unfolding linkage extension movement of said high-life device on said carrier track from said airfoil, and a camtrack guided angle-of-incidence programming of said high-lift device relative to said airfoil; and

said camtrack producing a guided force vector component to said linkage mechanism during unfolding linkage extension movement of said high-lift device, for enabling said linkage mechanism to freely operate a complete extension cycle of said high-lift device without locking up.

8. The mechanism for extending and positioning a high-lift device relative to an airfoil as set forth in claim 7, wherein:

said rotary actuator, said camtrack and said linkage mechanism, in combination, extending said high-lift device, from a retracted stowed position whereat said high-lift device forms the leading edge nose structure of said airfoil, to a first forward and downward extended operating position whereat a continuous upper surface contour is formed between said high-lift device and the relatively fixed leading edge portion of said airfoil, and to a second further extended operating position whereat an aerodynamic slot is formed between said high-lift device and the relatively fixed leading edge portion of said airfoil.

9. A leading edge slat extension and position programming control mechanism for an airfoil, comprising:

a slat panel forming a leading edge nose structure of said airfoil and being extensible from a relatively fixed portion of said airfoil;

a carrier track extending chordwise fore and aft of said airfoil, and being pivotally connected at its fore end to said slat panel;

cylindrical rollers being axially mounted to said relatively fixed portion of said airfoil, for rolling contact support of the aft portion of said carrier track;

a rib member extending chordwise of said airfoil and being structurally integral with said relatively fixed portion of said airfoil;

a camtrack formed structurally integral with said rib member;

a chordwise integrated linkage mechanism being positioned adjacent to said rib member and comprising, a drive arm mounted to the relatively fixed portion of said airfoil for rotation in a chordwise plane, a drive link pivotally connected at one end to the swinging end of said drive arm, and a drive beam extending fore and aft chordwise and being pivotally connected at its aft end to the other end of said drive link and being fixedly secured at its fore end to said slat panel;

a cam follower engaged in said camtrack and connected to the pivotal connection between said drive beam and said drive link for producing a force vector component to said linkage mechanism along the arcuate track of said camtrack;

a rotary actuator mounted in said airfoil;

said chordwise integrated linkage mechanism being in a folded arrangement during a fully retracted position of said slat panel relative to said fixed portion of said airfoil, and interconnecting said slat panel with said camtrack and said rotary actuator;

said rotary actuator in combination with said linkage mechanism, said camtrack and said carrier track, effecting a simultaneously combined unfolding linkage extension movement of said slat panel on said carrier track from said fixed portion of said airfoil, and a camtrack guided angle-of-incidence programming of said slat panel relative to said fixed portion of said airfoil; and

said camtrack providing a guided force vector component to said linkage mechanism during unfolding linkage extension movement of said slat panel, for enabling said linkage mechanism to freely operate the complete extension cycle of said slat panel without locking up.

10. A leading edge slat extension and position programming control mechanism for an airfoil as set forth in claim 9, wherein:

said rotary actuator, said camtrack and said linkage mechanism, in combination, extending said slat panel, from a retracted stowed position whereat said slat panel forms the leading edge nose structure of said airfoil, to a first forward and downward extended operating position whereat a continuous upper surface contour is formed between said slat panel and the relatively fixed leading edge portion of said airfoil, and to a second further extended operating position whereat an aerodynamic slot is formed between said slat panel and the relatively fixed leading edge portion of said airfoil.