There is disclosed an aircraft wing rib comprising a structural rib section to which a wing skin can be attached; and a suction conduit to which, in use, a negative pressure can be applied so as to cause air to be drawn through suction holes provided in the outer surface of the wing skin. There is a
There is disclosed an aircraft wing rib comprising a structural rib section to which a wing skin can be attached; and a suction conduit to which, in use, a negative pressure can be applied so as to cause air to be drawn through suction holes provided in the outer surface of the wing skin. There is also disclosed an aircraft wing including such a wing rib.
대표청구항▼
1. An aircraft wing rib, comprising: a structural rib section to which a wing skin can be attached; anda suction conduit configured such that, in use, an application of a negative pressure causes air to be drawn through suction holes provided in an outer surface of the wing skin,wherein the suction
1. An aircraft wing rib, comprising: a structural rib section to which a wing skin can be attached; anda suction conduit configured such that, in use, an application of a negative pressure causes air to be drawn through suction holes provided in an outer surface of the wing skin,wherein the suction conduit comprises an open channel configured to be closed by the attachment of the wing skin to the structural rib section, andwherein the structural rib section comprises two laterally spaced wing skin flanges configured to attach the wing skin to the structural rib section, andwherein the open channel is located between the two laterally spaced wing skin flanges. 2. The wing rib according to claim 1, wherein the suction conduit has a port arranged to be fluidically coupled to a source of negative pressure. 3. The wing rib according to claim 1, wherein the open channel is defined by the structural rib section. 4. The wing rib according to claim 1, wherein the suction conduit further comprises a duct in fluid communication with the open channel and arranged to be fluidically coupled to a source of negative pressure. 5. The wing rib according to claim 4, wherein the duct extends in a direction substantially parallel to a width direction of the wing rib. 6. The wing rib according to claim 4, wherein the duct comprises two duct couplings, one on either side of the structural rib section, to which a corresponding coupling of a suction pipe can be connected. 7. The wing rib according to claim 1, wherein the wing rib is at least one of: an integrally formed component; and is manufactured by an additive manufacturing process. 8. An aircraft wing comprising: at least one wing spar;a plurality of wing ribs, attached to the at least one wing spar; each wing rib comprising:a structural rib section; anda suction conduit; anda wing skin attached to the structural rib sections of the wing ribs, the wing skin having a plurality of suction holes in an outer surface thereof and wherein each suction hole is in fluid communication with a suction conduit of at least one wing rib,wherein the suction conduit comprises an open channel closed by the attachment of the wing skin to the structural rib section,wherein the structural rib section comprises two laterally spaced wing skin flanges attaching the wing skin to the structural rib section, andwherein the open channel is located between the two laterally spaced wing skin flanges. 9. The aircraft wing according to claim 8, wherein the suction conduits of the wing ribs are in fluid communication with one another. 10. The aircraft wing according to claim 9, wherein the suction conduits of each adjacent pair of wing ribs are fluidically coupled together with a suction pipe section located between adjacent wing ribs. 11. The aircraft wing according to claim 10, wherein the suction conduit of each wing rib comprises a duct which extends through the structural rib section. 12. The aircraft wing according to claim 11, wherein the suction pipe sections and the ducts form a continuous suction channel which can be fluidically coupled to a source of negative pressure. 13. The aircraft wing according to claim 12, wherein the end of each duct is provided with a duct coupling, and wherein the end of each suction pipe section is provided with a coupling which is coupled to a respective duct coupling. 14. The aircraft wing according to claim 8, wherein the wing skin comprises an outer layer and an inner layer defining at least one suction chamber therebetween, wherein the suction holes are provided in the outer layer, and wherein the inner layer comprises a plurality of metering holes, each opening into a suction conduit. 15. The aircraft wing according to claim 14, wherein the wing skin defines a plurality of separated suction chambers, each suction chamber extending in a spanwise direction. 16. The aircraft wing according to claim 15, wherein each suction chamber is provided with a plurality of metering holes in the inner layer, each metering hole opening into a separate suction conduit. 17. The aircraft wing according to claim 15, wherein a plurality of suction holes open into each suction chamber. 18. An aircraft wing comprising: at least one wing spar;a plurality of wing ribs attached to the at least one wing spar, each of the plurality of wing ribs including: a structural rib section; anda suction conduit comprising an open channel and a duct extending though the structural rib section in a direction substantially parallel to a width direction of the wing rib;wherein the ducts of adjacent wing ribs are coupled together with a suction pipe section so as to form a continuous suction channel; anda wing skin attached to the wing ribs so as to close the open channels, the wing skin having a plurality of suction holes in an outer surface thereof, each suction hole being in fluid communication with the open channel of at least one wing rib,wherein the structural rib section comprises two laterally spaced wing skin flanges attaching the wing skin to the structural rib section, andwherein the open channel is located between the two laterally spaced wing skin flanges. 19. An airfoil on an aircraft comprising: a leading edge section including a wing skin forming a leading edge of the airfoil and extending aft of the leading edge from both sides of the airfoil, wherein the leading edge extends in a spanwise direction of the airfoil;a spar housed within the wing skin, oriented in the spanwise direction, aft of the leading edge and spanning between opposing sections of the wing skin;a wing rib spanning between the opposing sections of the wing skin, attached to and extending forward of the spar, wherein the wing rib includes an outer surface attached to the wing skin along both of the opposing sections of the wing skin from the leading edge towards the spar;a pair of laterally spaced wing skin flanges forming at least a portion of the outer surface of each of the wing ribs;a channel between the pair of laterally spaced wing skin flanges and in the outer surface of the wing rib; the channel is closed by the attachment of the outer surface to the wing skin, wherein the channel is configured to form a reduced pressure air region to allow a portion of air flowing across an outer surface of the wing skin to enter the channel; anda duct in fluid communication with the channel and housed within the wing skin,wherein the wing skin is porous and pores in the wing skin are in fluid communication with the channel. 20. The airfoil of claim 19, wherein the airfoil is a wing of the aircraft. 21. The airfoil of claim 19, wherein the duct extends through the wing rib. 22. The airfoil of claim 19, wherein the wing rib includes a body section which is a plate extending perpendicular to the spar and the wing skin. 23. The airfoil of claim 22, wherein the wing rib includes a flange at a rear edge of the body section, wherein the flange is attached to the spar. 24. The airfoil of claim 19, wherein the wing skin includes an outer layer including the pores, an inner layer which closes the channel, and a suction air chamber sandwiched between the inner and outer layers.
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이 특허에 인용된 특허 (8)
Johnstone Edmund H. (82 Salzburg Blvd. Apt. G Columbus IN 47201), Aircraft wing vortex deflector.
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