Air flow channeling yaw control device
AssigneeLockheed Martin Corporation
InventorMark D. Buchholz
Life of this patent
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Abstract
An air flow channeling yaw control device includes a vane cover, a vane array, and an actuator. The vane array includes a plurality of vanes, each of the plurality of vanes comprising a first edge and a second edge, the first edge being hingedly coupled to the vane cover and the second edge being hingedly coupled to a wing of an aircraft. The wing includes a leading edge and a trailing edge. The actuator is configured to move the plurality of vanes from a retracted position into a deployed position. The plurality of vanes, when moved into the deployed position, are configured to direct a flow of air flowing over the leading edge of the wing through channels created by the plurality of vanes. The plurality of vanes, when moved into the retracted position, are configured to retract within the wing.
Claims20
An air flow channeling yaw control device comprising:
- a vane cover;
- a vane array comprising a plurality of vanes, wherein:
- each of the plurality of vanes comprises a first edge and a second edge, the first edge configured to be hingedly coupled to the vane cover and the second edge configured to be hingedly coupled to a wing of an aircraft;
- and
- at least one of the plurality of vanes comprises a gurney flap;
- and
- an actuator configured to move the plurality of vanes from a retracted position into a deployed position, wherein the plurality of vanes, when moved into the deployed position, are configured to direct a flow of air flowing over a leading edge of the wing through channels created by the plurality of vanes.
A wing of an aircraft, the wing comprising:
- an air flow channeling yaw control device;
- and
- a cavity configured to accommodate the air flow channeling yaw control device;
- wherein the air flow channeling yaw control device comprises:
- a vane cover;
- a vane array comprising a plurality of vanes, each of the plurality of vanes comprising a first edge and a second edge, the first edge being hingedly coupled to the vane cover and the second edge being hingedly coupled to a portion of the cavity;
- and
- an actuator configured to move the plurality of vanes from a retracted position into a deployed position, wherein the plurality of vanes, when moved into the deployed position, are configured to direct a flow of air flowing over a leading edge of the wing through channels created by the plurality of vanes.
Dependencies are inferred from the claim text.