Blade pitch control disk device for a rotorcraft rotor

Details Blade pitch control disk device for a rotorcraft rotor Blade pitch control disk device for a rotorcraft rotor

2006-04-04

2006-04-04

Look, Edward K. (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Sustained ancillary movement of rotary working member

Responsive to fixed actuator

C416S13400R

Reexamination Certificate

active

07021897

ABSTRACT:
A cyclic swashplate device for controlling rotorcraft blade pitch is disclosed for application to rotorcraft swashplates, in particular, in helicopters. A cyclic swashplate device controls the rotorcraft blade pitch. The device (10′), with rotating (10′) and non-rotating (14′) cyclic swashplates is designed in such a way that at least one of the two disks includes a modular link fitting assembly (46, 42) ensuring the links with the disk (12′, 14′) and the pitch connecting rods (6) and/or at least one driving device or with the pilot control devices (17) and/or at least one retaining device. Interconnecting fittings are attached rigidly and separately to an annular device, such as one of the rings (31′, 30′) of a bearing (21′) on the corresponding disk (14′, 12′).

REFERENCES:
patent: 4630998 (1986-12-01), Leman
patent: 5785497 (1998-07-01), White et al.
patent: 6033182 (2000-03-01), Rampal
patent: 6152696 (2000-11-01), Rampal
patent: 6280141 (2001-08-01), Rampal et al.
patent: 36 03 400 (1987-05-01), None
patent: 36 20 794 (1987-12-01), None
INPI (French Patent Office) Preliminary Search Report, dated Aug. 14, 2003.

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