Rotor blade lock for rotary/wing aircraft

Aeronautics and astronautics – Aircraft – heavier-than-air – Airplane and helicopter sustained

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416169R, B64C 2724

Patent

active

061617997

ABSTRACT:
The present invention comprises an apparatus for locking both rotor blades of a rotor/wing aircraft at a common point to form a rigid wing having a uniform bilateral aerodynamic response. In one embodiment of the present invention the rotor blades of a rotor/wing aircraft are locked together to form a rigid wing assembly. This is accomplished by locking the blades together by a locking mechanism that engages when the rotor speed drops below a certain threshold. With the rotor blades locked together, the wing assembly can then be locked in position with the appropriate pitch angle simply by securing the pitch link of the rotor blade that is oriented at the leading edge of the fixed wing. In another embodiment of the invention the blades are locked directly to the rotor by two locking mechanisms that engage the hub directly. By locking the rotor blades into a rigid assembly having a common control point, it is possible to provide a rotor/wing aircraft having a fixed wing with more predictable and controllable response to aerodynamic forces.

REFERENCES:
patent: 2518007 (1950-08-01), Herrick
patent: 3647315 (1972-03-01), Rostad et al.
patent: 3986686 (1976-10-01), Girard
patent: 5405104 (1995-04-01), Pande
patent: 5454530 (1995-10-01), Rutherford
patent: 5788181 (1998-08-01), Wilson

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