Helicopter blade pitch control system

Details Helicopter blade pitch control system Helicopter blade pitch control system

1991-06-10

1993-02-23

Denion, Thomas E.

Fluid reaction surfaces (i.e., impellers)

Sustained ancillary movement of rotary working member

Responsive to fixed actuator

416114, 416149, 416159, 416162, B63H 300

Patent

active

051885123

ABSTRACT:
A helicopter blade pitch control system allows blade pitch to be controlled with regard to the degree of rotational position of the blade with respect to the direction of travel and also the degree of pitch. The invention provides an improved arrangement wherein speed paddles attach to rotor blades can change in pitch around the circle of rotation of the blade and also the amount of pitch change can be adjustably changed by the pilot. The apparatus includes a cylindrical member surrounding the rotor of the helicopter and being static with respect thereto so that variable pitch speed paddles connected to and forming a part of the blade assembly and which carry rotating foot members track the upper surface of the cylindrical member changing the pitch of the blade as it moves through a 360 degree rotation. The pitch is maximized when the blade moves rearwardly with respect to the direction of travel and the pitch collapses to a horizontal pitch when the blade moves forwardly, in the same direction of travel as the craft.

REFERENCES:
patent: 2064223 (1936-12-01), Rothenhoefer
patent: 2404522 (1946-07-01), Nemeth
patent: 2410545 (1946-11-01), Main
patent: 2437165 (1948-03-01), Locke
patent: 2677430 (1954-05-01), Prince
patent: 3026740 (1962-03-01), Covert

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