Drive mechanism for combined flap-aileron surface
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-009/06
B64C-009/18
출원번호
US-0431759
(1982-09-30)
발명자
/ 주소
Robinson, Curtiss W.
출원인 / 주소
The Boeing Company
대리인 / 주소
Barnard, Delbert J.
인용정보
피인용 횟수 :
8인용 특허 :
2
초록▼
A flap (22) carries a guide roller (24) at each of its ends. Each guide roller (24) travels within a fore and aft track (28) positioned immediately endwise outwardly of its end of the flap (22). The flap (22) is extended and retracted by means including a reaction link (36) and a two-way linear actu
A flap (22) carries a guide roller (24) at each of its ends. Each guide roller (24) travels within a fore and aft track (28) positioned immediately endwise outwardly of its end of the flap (22). The flap (22) is extended and retracted by means including a reaction link (36) and a two-way linear actuator (38). The actuator (38) and the reaction link (36) are pivotally connected at their forward ends to the outer end of a bell crank arm (34), for pivotal movement about a common axis (40). At its rearward end the actuator (38) is pivotally attached to the flap at a location (44) offset above the roller (24). The reaction link (36) is pivotally attached at its rearward end to the flap (22) at a location (42) offset below the roller (24). Rotation of the bell crank arm (34) alone will result in the flap (22) being translated rearwardly and rotated downwardly, i.e. Fowler flap movement. Extension or retraction of the actuator (38) will cause a rotation of the flap (22) about the axes (26) of the rollers (24).
대표청구항▼
1. In an aircraft: a slotted wing comprising a main wing structure having upper, lower and forward edge skin surfaces and a rear recess, and a combination flap-aileron having upper and lower skin surfaces, a forward edge, and a hinge axis, said wing skin surfaces establishing a wing skin envelope
1. In an aircraft: a slotted wing comprising a main wing structure having upper, lower and forward edge skin surfaces and a rear recess, and a combination flap-aileron having upper and lower skin surfaces, a forward edge, and a hinge axis, said wing skin surfaces establishing a wing skin envelope; fixed position track means carried by the main wing structure totally within the wing envelope, mounting said flap-aileron for fore and aft movement relative to the main wing structure, between a forward position in which the forward edge of the flap-aileron is received within the recess and a rearward position in which said forward edge is spaced rearwardly of the recess; and positioning means for said flap-aileron operable for driving the flap-aileron fore and aft along said fixed position track means, and for holding the flap-aileron in position at any location at or between the forward and rearward positions of the flap-aileron, and for rotating the flap-aileron about said hinge axis at any position of the flap-aileron along said track means, and for holding the flap-aileron in a selected rotational position within a range of rotational positions, wherein fore and aft movement of the flap-aileron along said fixed position track means and rotation of the flap-aileron about said hinge axis are each independent of the other. 2. In an aircraft: a forward wing structure; a rear edge flap having opposite ends; a pair of fore and aft extending fixed tracks, one positioned immediately outwardly of each end of the flap, said tracks being carried by the forward wing structure; guide means carried by each end of the flap, mounting its end of the flap for movement along the track means; and flap positioning means comprising a torque tube supported within the main wing structure forwardly of said track means, a bell crank arm having a first end connected to the torque tube and a second end spaced radially outwardly from the torque tube, a reaction link pivotally connected at a first end to the second end of the bell crank arm and pivotally connected at a second end to the flap at a location offset below the pivot axis, and a two-way linear actuator having a first end which is pivotally connected to the second end of the bell crank arm, on a common axis with said reactive link, and a second end which is pivotally connected to the flap at a location offset above the pivot axis. 3. The structure of claim 2, wherein the two-way linear actuator is a double-acting hydraulic cylinder. 4. The structure of claim 3, wherein the flap has a forward neutral position and when it is in such position, the guide means occupy relatively forward positions on the fixed tracks, the bell crank arm extends at a slope downwardly and forwardly from the torque tube, and the hydraulic cylinder is centered. 5. The structure of claim 3, wherein the flap has an extended position in which it is spaced rearwardly from the main wing structure and is also rotated slightly downwardly from its attitude when in the forward neutral position, the guide means are positioned relatively forwardly on the fixed tracks, the bell crank arm and the hydraulic cylinder are substantially aligned, and the hydraulic cylinder is centered. 6. The structure of claim 2, wherein positioning means is operable for rotating the flap-aileron downwardly by extension of the linear actuator. 7. The structure of claim 2, wherein the positioning means is operable for rotating the flap-aileron upwardly by retraction of the linear actuator. 8. In an aircraft: a slotted wing comprising a main wing structure having upper, lower and forward edge skin surfaces and a rear recess, and a combination flap-aileron having upper and lower skin surfaces, a forward edge, and a hinge axis, said wing skin surfaces establishing a wing skin envelope; track means carried by the main wing structure, mounting said flap-aileron for fore and aft movement relative to the main wing structure, between a forward position in which the forward edge of the flap-aileron is received within the recess and a rearward position in which said forward edge is spaced rearwardly of the recess; and positioning means operable for (a) drivingly moving the flap-aileron fore and aft along said track means, and for holding the flap-aileron in a selected position along said track means, and (b) rotating the flap-aileron about said hinge axis, and for holding the flap-aileron in a selected rotational position, said movement of the flap-aileron along said track means being independent of rotation of the flap-aileron about said hinge axis, the flap-aileron being rotatable at any position of the flap-aileron fore and aft along said track means, and further, the flap-aileron being movable along said track means for any rotational position of the flap-aileron within a selected range of rotational positions, wherein the track means and the positioning means are located totally within the wing envelope, and wherein the flap-aileron comprises opposite ends and the track means comprises a pair of fixed tracks, one positioned immediately outwardly of each end of the flap-aileron, and guide means carried by each end of the flap-aileron, mounting its end of the flap-aileron for movement along the track means. 9. The structure of claim 8, wherein each fixed track has spaced apart upper and lower rails, and wherein the guide means carried by the ends of the flap-aileron are positioned between the rails. 10. The structure of claim 9, wherein the guide means have axes coinciding with the hinge axis and they mount the flap-aileron for rotation about the hinge axis. 11. The structure of claim 10, wherein the guide means are rollers. 12. The structure of claim 11, wherein the positioning means comprises a torque tube, a bell crank having a first end connected to the torque tube and a second end spaced radially outwardly from the torque tube, a reaction link pivotally connected at a first end to the second end of the bell crank and pivotally connected at a second end to the flap-aileron at a location offset below the pivot axis, and a two-way linear actuator having a first end which is pivotally connected to the second end of the bell crank, on a common axis with said reaction link, and a second end which is pivotally connected to the flap-aileron at a location offset above the pivot axis. 13. The structure of claim 12, wherein the two-way linear actuator is a double-acting hydraulic cylinder. 14. The structure of claim 10, wherein the positioning means comprises a torque tube, a bell crank having a first end connected to the torque tube and a second end spaced radially outwardly from the torque tube, a reaction link pivotally connected at one end to the second end of the bell crank and pivotally connected at a second end to the flap-aileron at a location offset below the pivot axis, and a two-way linear actuator having a first end which is pivotally connected to the second end of the bell crank, on a common axis with said reaction link, and a second end which is pivotally connected to the flap-aileron at a location offset above the pivot axis. 15. The structure of claim 14, wherein the two-way linear actuator is a double-acting hydraulic cylinder. 16. The structure of claim 15, wherein the hydraulic cylinder is centered when the flap-aileron is in its forward position. 17. The structure of claim 16, wherein the track means and the positioning means function to both translate and rotate the flap-aileron downwardly upon bell crank rotation in a direction moving the flap-aileron from its forward position to its rearward position. 18. The structure of claim 17, wherein the track means and the positioning means are operable for rotating the flap-aileron downwardly by extension of the hydraulic cylinder. 19. The structure of claim 17, wherein the track means and the positioning means are operable for rotating the flap-aileron upwardly by retraction of the hydraulic cylinder. 20. In an aircraft: a slotted wing comprising a main wing structure having upper, lower and forward edge skin surfaces and a rear recess, and a combination flap-aileron having opposite ends and a guide means carried by each of said ends, said flap-aileron further having upper and lower skin surfaces, a forward edge, and a hinge axis, said wing skin surfaces establishing a wing skin envelope; track means in the form of a pair of fixed tracks, one each of said pair being positioned immediately outwardly of each end of the flap-aileron, each of said fixed tracks having spaced apart upper and lower rails carried by the main wing structure, with the guide means carried by each end of the flap-ailerons being positioned between the rails for mounting each end of the flap-aileron for movement along the track means, for fore and aft movement relative to the main wing structure between a forward position in which the forward edge of the flap-aileron is received within the recess and a rearward position in which said forward edge is spaced rearwardly of the recess, and wherein said guide means have axes coinciding with the hinge axis such that they mount the flap-aileron for rotation about the hinge axis; and positioning means comprising a torque tube, a bell crank haing a first end connected to the torque tube and a second end spaced radially outwardly from the torque tube, a reaction link pivotally connected at one end to the second end of the bell crank and pivotally connected at a second end to the flap-aileron at a location offset below the pivot axis, and a two-way linear actuator having a first end which is pivotally connected to the second end of the bell crank, on a common axis with said reaction link, and a second end which is pivotally connected to the flap-aileron at a location offset above the pivot axis, said positioning means being operable for: (a) driving the flap-aileron fore and aft along said track, (b) rotating the flap-aileron about the hinge axis, and (c) holding the flap-aileron in a selected position, wherein the track means and the positioning means are located totally within the wing skin envelope. 21. The structure of claim 20, wherein the two-way linear actuator is a double-acting hydraulic cylinder. 22. The structure of claim 21, wherein the hydraulic cylinder is centered when the flap-aileron is in its forward position. 23. The structure of claim 22, wherein the track means and the positioning means function to both translate and rotate the flap-aileron downwardly upon bell crank rotation in a direction moving the flap-aileron from its forward position to its rearward position. 24. The structure of claim 23, wherein the track means and the positioning means are operable for rotating the flap-aileron downwardly by extension of the hydraulic cylinder. 25. The structure of claim 23, wherein the track means and the positioning means are operable for rotating the flap-aileron upwardly by retraction of the hydraulic cylinder. 26. In an aircraft: a slotted wing comprising a main wing structure having upper, lower and forward edge skin surfaces and a rear recess, and a combination flap-aileron having opposite ends and guide means in the form of a roller carried by each of said ends, said flap-aileron further having upper and lower skin surfaces, a forward edge, and a hinge axis, said wing skin surfaces establishing a wing skin envelope; track means in the form of a pair of fixed tracks, one each of said pair being positioned immediately outwardly of each end of the flap-aileron, each of said fixed tracks having spaced apart upper and lower rails carried by the main wing structure, with the roller carried by each end of the flap-aileron being positioned between the rails of that track which is positioned immediately outwardly of its end, for mounting its end for movement along the track, for fore and aft movement relative to the main wing structure between a forward position in which the forward edge of the flap-aileron is received within the recess and a rearward position in which said forward edge is spaced rearwardly of the recess, and wherein each roller has an axis coinciding with the hinge axis such that the rollers carried at the ends of the flap-aileron mount the flap-aileron for rotation about the hinge axis; and positioning means operable for (a) driving the flap-aileron fore and aft along said fixed tracks, (b) rotating the flap-aileron about the hinge axis, and (c) holding the flap-aileron in a selected position, said positioning means comprising: a torque tube, a bell crank having a first end connected to the torque tube and a second end spaced radially outwardly from the torque tube, a reaction link pivotally connected at a first end to the second end of the bell crank and pivotally connected at a second end to the flap-aileron at a location offset below the pivot axis, and a two-way linear actuator having a first end which is pivotally connected to the second end of the bell crank, on a common axis with said reaction link, and a second end which is pivotally connected to the flap-aileron at a location offset above the pivot axis, wherein the track means and the positioning means are located totally within the wing skin envelope. 27. The structure of claim 26, wherein the two-way linear actuator is a double-acting hydraulic cylinder.
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이 특허에 인용된 특허 (2)
Cole James B. (Mercer Island WA), Airplane wing trailing-edge flap-mounting mechanism.
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