Device for providing assistance to the pilot of a rotorcraft...

Fluid reaction surfaces (i.e. – impellers) – With control means responsive to non-cyclic condition... – Responsive to condition of torque or thrust of device or...

Reexamination Certificate

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Details

C416S044000

Reexamination Certificate

active

11010444

ABSTRACT:
The present invention provides a device enabling the collective pitch of the blades of the main rotor of a single-engined rotorcraft to be reduced automatically in the event of an engine failure. The device comprises an actuator which increases the collective pitch of the blades above a predefined threshold, and which decreases the collective pitch below the predefined threshold. The actuator is arranged on a bell crank of the mixing unit of the rotorcraft.

REFERENCES:
patent: 2317342 (1943-04-01), Pullin
patent: 2941605 (1960-06-01), Sikorsky
patent: 3000445 (1961-09-01), Stuart, III
patent: 3071335 (1963-01-01), Carter, Jr.
patent: 3603697 (1971-09-01), Lane
patent: 3839923 (1974-10-01), Dean
patent: 4168045 (1979-09-01), Wright et al.
patent: 4277038 (1981-07-01), Yates et al.
patent: 4399968 (1983-08-01), Stock et al.
patent: 4528628 (1985-07-01), Fischer et al.
patent: 2601326 (1988-01-01), None

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