초록 ▼

A replaceable tip portion (20) for a helicopter rotor blade (14) is selectively swept, tapered and anhedral. The tip portion is formed of an upper and lower composite tip skin layer (35), each tip skin layer having bonded thereto a honeycomb core (38). The density of the core varies from a leading e

A replaceable tip portion (20) for a helicopter rotor blade (14) is selectively swept, tapered and anhedral. The tip portion is formed of an upper and lower composite tip skin layer (35), each tip skin layer having bonded thereto a honeycomb core (38). The density of the core varies from a leading edge of the tip to a trailing edge of the tip from a high density to a lower density. A channel (recess) (40) is formed in the honeycomb for receiving a rotor spar tip end (30), and the tip portion is removably attached (60) to the rotor spar and the remainder of the rotor blade. The honeycomb core is attached to the upper and lower tip skin layers in halves, and is machined along the rotor blade chord plane (70) prior to assembly of the halves on the rotor spar, the machined core providing tight tolerance control in the construction of the blade tip portion. A composite tip cap (50) is fixed to the extreme tip end of the removable anhedral tip portion, the mating surface of the tip cap which is joined to the removable tip is machined to provide a precise joint.

대표청구항 ▼

1. A rotary wing aircraft blade, comprising: a root portion adapted to be connected to a helicopter rotor hub for rotation therewith about an axis of rotation; a central portion of aerodynamic shape connected to and extending outwardly from said root portion; a structural spar extending along t

1. A rotary wing aircraft blade, comprising: a root portion adapted to be connected to a helicopter rotor hub for rotation therewith about an axis of rotation; a central portion of aerodynamic shape connected to and extending outwardly from said root portion; a structural spar extending along the blade longitudinal axis from said root portion to a spar tip end; a blade skin covering said spar and a blade structural core for defining said central portion aerodynamic shape; an upper tip skin layer; a lower tip skin layer; a replaceable tip structural core disposed between said upper and lower tip skin layers in a replaceable tip portion of said blade; a recess formed in said replaceable tip structural core for receiving said spar tip end; and fastening means for securely fastening said spar tip end within said recess, thereby fastening said replaceable tip portion to said blade. 2. A rotary wing aircraft blade according to claim 1 further comprising adhesive disposed between said spar tip end and said recess for fastening said replaceable tip portion to said blade. 3. A rotary wing aircraft blade according to claim 1 wherein a flap of said upper and lower tip skin layers extends radially inward from said tip portion beyond the structural core disposed therebetween, said flaps being adhesively attached to said blade central portion. 4. A rotary wing aircraft blade according to claim 1 wherein the density of said replaceable tip structural core varies from a leading edge of said tip portion to a trailing edge of said tip portion from a high density to a lower density. 5. A rotary wing aircraft blade according to claim 1 wherein said tip portion is selectively swept, tapered and anhedral. 6. A rotary wing aircraft blade according to claim 1 further comprising a composite tip cap fixed to an extreme tip end of said tip portion. 7. A replaceable tip portion for a rotary wing aircraft blade, the blade having a root portion adapted to be connected to a helicopter rotor hub for rotation therewith about an axis of rotation, a central portion of aerodynamic shape connected to and extending outwardly from said root portion, a structural spar extending along the blade longitudinal axis from said root portion to a spar tip end, and a blade skin covering said spar and a blade structural core for defining said central portion aerodynamic shape, the replaceable tip portion comprising: an upper tip skin layer; a lower tip skin layer; a replaceable tip structural core disposed between said upper and lower tip skin layers; a recess formed in said replaceable tip structural core for receiving said spar tip end; and fastening means for securely fastening said spar tip end within said recess, thereby fastening said replaceable tip portion to said blade. 8. A replaceable tip portion according to claim 7 further comprising adhesive disposed between said spar tip end and said recess for fastening said tip portion to said blade. 9. A replaceable tip portion according to claim 7 wherein a flap of said upper and lower tip skin layers extends radially inward from the tip portion beyond the structural core disposed therebetween, said flaps being adhesively attached to said blade central portion. 10. A replaceable tip portion according to claim 7 wherein the density of said replaceable tip structural core varies from a leading edge of said tip portion to a trailing edge of said tip portion from a high density to a lower density. 11. A replaceable tip portion according to claim 7 wherein said tip portion is selectively swept, tapered and anhedral. 12. A replaceable tip portion according to claim 8 further comprising a composite tip cap fixed to an extreme tip end of said tip portion. 13. A method for manufacturing a replaceable tip portion for a rotary wing aircraft blade, comprising the steps of: providing an upper tip skin mold and a lower tip skin mold, each mold having a lay-up surface for forming a tip skin surface; laying-up a plurality of ply layers in each mold, each ply layer comprising composite fibers in a matrix of binder; curing said ply layers to form an upper tip skin and a lower tip skin; attaching structural core material to said upper tip skin and to said lower tip skin thereby forming an upper tip portion and a lower tip portion; forming a recess in said structural core material having an inside diameter which corresponds to the shape of a rotor spar tip end; and machining said core material along a rotor blade chord plane; said machined core providing tight tolerance control in the assembly of said upper and lower tip portions as said replaceable tip portion. 14. The method according to claim 13 wherein said lay-up surfaces substantially provide the desired final exterior shape of said tip portion. 15. The method according to claim 14 wherein said upper and lower tip portions are selectively swept, tapered and anhedral. 16. The method according to claim 13 further comprising the step of debulking said ply layers prior to curing said upper and lower tip skin.