Retractable vortex generator system for an aircraft
AssigneeAirbus Operations S.L.
InventorAlberto Arana Hidalgo
Life of this patent
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Abstract
A retractable vortex generator system for an aircraft. The system comprises a skin, a slot arranged on the skin, a plate comprising a contour configured for energizing the boundary layer of an air current, and driving means configured for rotating the plate between a first and a second position. In the first position at least part of the contour of the plate protrudes through the slot, and in the second position the plate is retracted within the slot.
Claims17
A retractable vortex generator system for an aircraft, the system comprising:
- a skin,
- a slot arranged on the skin,
- a plate comprising a contour configured for energizing a boundary layer of an air current, and
- driving means configured for rotating the plate 180 degrees between a first position and a second position,
- wherein in the first position, at least part of the contour of the plate protrudes through the slot, and
- wherein in the second position, the plate is retracted.
A retractable vortex generator system for an aircraft, the system comprising:
- a skin, a slot arranged on the skin, a plate comprising a contour configured for energizing a boundary layer of an air current, and driving means configured for rotating the plate between a first position and a second position,
- wherein in the first position, at least part of the contour of the plate protrudes through the slot, and
- wherein in the second position, the plate is retracted
- wherein the driving means comprises a motor and a gear rod mechanism,
- wherein the motor is configured for mechanically actuating the gear rod mechanism for rotating the plate between the first and the second position
- wherein the gear rod mechanism comprises at least a first rod and a second rod,
- wherein the first rod is articulately connected to the plate, the first rod being further articulately connected to the second rod by means of a ball joint, and the second rod is further articulately connected to the motor.
A retractable vortex generator system for an aircraft, the system comprising:
- a skin, a slot arranged on the skin, a plate comprising a contour configured for energizing a boundary layer of an air current, and driving means configured for rotating the plate between a first position and a second position,
- wherein in the first position, at least part of the contour of the plate protrudes through the slot, and
- wherein in the second position, the plate is retracted,
- wherein the plate comprises at least one metallic flap fixed thereon, the at least one metallic flap configured for rotating with the plate around a rotation center,
- wherein the driving means comprises at least one electromagnet configured to alternate its polarity,
- wherein when said electromagnet has a first polarity, the at least one metallic flap abuts against the electromagnet in a first electromagnetic balance corresponding to the first position of the plate,
- wherein when said electromagnet has a second polarity, the at least one metallic flap abuts against the electromagnet in a second electromagnetic balance corresponding to the second position of the plate, and
- wherein a change of polarity of the electromagnet causes a rotation of the plate between the first and the second position.
Dependencies are inferred from the claim text.