Cyclic actuation system for a controllable pitch propeller and a method of providing aircraft control therewith
First Claim
1. A propeller control system comprising:
- a propeller shaft which rotates about an axis of rotation to drive a plurality of propeller blades extending therefrom;
a translating pitch change yoke portion mounted within said propeller shaft along said axis of rotation; and
an articulatable pitch change yoke portion pivotally mounted to said translating pitch change yoke portion for axial movement therewith, said translating pitch change yoke portion axially movable along said axis of rotation to collectively change a pitch of said plurality of propeller blades, said articulatable pitch change yoke portion deflectable off said axis of rotation to cyclically change the pitch of said plurality of propeller blades.
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Accused Products
Abstract
A propeller control generates a once per revolution (1P) blade thrust variation through cyclic pitch of rigidly mounted non-flapping propeller blades. The resultant shaft bending moment is used to provide aircraft attitude control. Axial translation of a pitch change assembly including a pitch change yoke along an axis of rotation drives a pitch link attached to each propeller blade to collectively change the propeller blade pitch angle. The pitch change yoke includes a translating pitch change yoke portion and an articulatable pitch change yoke portion. Deflection of the articulatable pitch change yoke portion changes the pitch change effect of each pitch link as a function of its angular position such that a sinusoidal pitch angle is superimposed on normal pitch angle. Cyclic pitch change actuators deflect the articulatable pitch change yoke portion in any angular direction while the linear deflection of the cyclic pitch change actuators generate the magnitude of the cyclic pitch.
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Citations
27 Claims
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1. A propeller control system comprising:
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a propeller shaft which rotates about an axis of rotation to drive a plurality of propeller blades extending therefrom;
a translating pitch change yoke portion mounted within said propeller shaft along said axis of rotation; and
an articulatable pitch change yoke portion pivotally mounted to said translating pitch change yoke portion for axial movement therewith, said translating pitch change yoke portion axially movable along said axis of rotation to collectively change a pitch of said plurality of propeller blades, said articulatable pitch change yoke portion deflectable off said axis of rotation to cyclically change the pitch of said plurality of propeller blades. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12)
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13. A method of cyclically controlling a pitch of a plurality of rigidly mounted propeller blades comprising the steps of:
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(1) translating a first pitch change yoke portion and a second pitch change yoke portion mounted within a propeller shaft along an axis of rotation to collectively change a pitch of said plurality of propeller blades; and
(2) articulating the second pitch change yoke portion off said axis of rotation relative the first pitch change yoke portion to cyclically change the pitch of said plurality of propeller blades. - View Dependent Claims (14, 15, 16, 17, 18, 19)
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20. A flight control method for an aircraft comprising a propeller system having a plurality of rigidly mounted propeller blades, said method comprising the steps of:
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(1) mounting the propeller system to an aircraft wing such that the plurality of rigidly mounted propeller blades of the propeller system rotate generally within a plane defined generally transverse of an aircraft wing;
(2) collectively changing a pitch of the plurality of rigidly mounted propeller blades of the propeller system to generate a trust; and
(3) cyclically changing the pitch of the plurality of propeller blades to generate a moment. - View Dependent Claims (21, 22, 23, 24, 25, 26, 27)
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Specification