Helicopter rotor blade having a replaceable anhedral tip

Details Helicopter rotor blade having a replaceable anhedral tip Helicopter rotor blade having a replaceable anhedral tip

1992-12-22

1994-06-14

Look, Edward K.

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Formed with main spar

416228, 416229R, 416230, 298896, 2988971, 156 92, 156 98, 156344, 264257, B64C 1126

Patent

active

053204948

ABSTRACT:
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.

REFERENCES:
patent: 3105557 (1963-10-01), Wigal
patent: 3874820 (1975-04-01), Fenaughty
patent: 4324530 (1982-04-01), Fradenburgh et al.
patent: 4334828 (1982-06-01), Moffitt
patent: 4470862 (1984-09-01), More et al.
patent: 4648921 (1987-03-01), Nutter, Jr.
patent: 4784575 (1988-11-01), Nelson et al.
patent: 5042968 (1991-08-01), Fecto

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