Rotorcraft blade-vortex interaction controller
AssigneeThe United States of America as represented by the United States National Aeronautics and Space Administration
InventorFrederic H. Schmitz
Life of this patent
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Abstract
Blade-vortex interaction noises, sometimes referred to as "blade slap", are avoided by increasing the absolute value of inflow to the rotor system of a rotorcraft. This is accomplished by creating a drag force which causes the angle of the tip-path plane of the rotor system to become more negative or more positive.
Claims6
An apparatus for decreasing blade-vortex interaction noise of a rotorcraft having a fuselage and a rotor system, comprising:
- control means for increasing the absolute value of inflow to the rotor system;
- and
- means for actuating the control means under flight condition when infow is near zero,
- wherein the control means comprises first and second drag panels mounted respectively on opposite sides of the fuselage and being movable between operative and inoperative positions by the actuating means and being vertically oriented and extending radially outwardly when in the operative position.
A method of decreasing blade-vortex interaction noise of rotorcraft having a fuselage and a rotor comprising:
- creating a drag force to cause a more negative angle for the tip-path plane of the rotor system,
- wherein creating said drag force comprises deploying a vertically aligned drag structure having a drag surface sufficient to create the drag force.
A method of decreasing blade-vortex interaction noise of rotorcraft having a fuselage and a rotor comprising:
- creating a negative drag force (a net thrust) to cause a more negative angle for the tip-path plane of the rotor system,
- wherein creating said drag force comprises deploying a vertically aligned a drag structure having a drag surface sufficient to create the drag force.
An apparatus for decreasing blade-vortex interaction noise of a rotorcraft havign a fuselage and a rotor system, comprising:
- control means for increasing the absolute value of inflow to the rotor system;
- and
- means for actuating the control means under flight conditions when inflow is near zero,
- wherein the control means comprises first and second drag panels mounted respectively on opposite sides of the fuselage and being movable between operative and inoperative positions by the actuating means, and
- wherein the first and second drag panels have a combined drag surface area sufficient to produce a drag force at least equal to a drag force of the fuselage.
Dependencies are inferred from the claim text.