Aircraft tail surface
AssigneeAirbus Operations S.L.U.
InventorsRaúl Carlos Llamas Sandin, Kwing So Choi, Yaxing Wang
Life of this patent
Estimating the term…
Abstract
An aircraft tail including: a leading edge, a trailing edge, a tip and a root, and a single protrusion protruding from the leading edge, wherein the single protrusion protrudes from the leading edge only in a direction opposite to the trailing edge and is closer to the tip than to the root, and includes a first lateral side and a second lateral side that originate from different points of the leading edge along the tail span, wherein the first lateral side is closer to the tip than to the second lateral side, and the protrusion is entirely in a section of the leading edge between 50% and 95% of the tail span from the root.
Claims17
An aircraft tail comprising:
- a leading edge, a trailing edge, a tip and a root, and
- a single protrusion protruding from the leading edge,
- wherein the single protrusion protrudes from the leading edge only in a direction opposite to the trailing edge and is closer to the tip than to the root;
- and
- wherein the single protrusion includes a first lateral side and a second lateral side that each originate from leading edge at different points along a tail span of the leading edge and converge at a protrusion tip,
- wherein the different points are not coincident with the tip or the root,
- wherein the first lateral side is closer to the tip than to the second lateral side,
- wherein the single protrusion is located entirely in a section of the leading edge between 50% and 95% of the tail span starting from the root,
- wherein the single protrusion has a length extending from the leading edge to the protrusion tip in a direction parallel to a chord of the aircraft tail and a width extending in a direction perpendicular to the length,
- wherein a ratio of the length to the width of the single protrusion is in a range of 0.8 to 1.2, and
- wherein the single protrusion is asymmetrical about a line extending parallel to the chord and passing through the protrusion tip.
A vertical tail in an aircraft tail assembly including:
- a leading edge and a trailing edge, each extending from a root of the vertical tail to a tip of the vertical tail;
- and
- a single protrusion extending from and forward of the leading edge, wherein the single protrusion includes:
- a first lateral edge extending from a first point on the leading edge to a protrusion tip at a forwardmost portion of the single protrusion;
- and
- a second lateral edge extending from a second point on the leading edge to the protrusion tip,
- wherein the second point is closer to the root than is the first point,
- wherein the single protrusion is entirely within a section of the leading edge between 50% and 95% of a span of the leading edge starting from the root,
- wherein the single protrusion has a length extending from the leading edge to the protrusion tip in a chordwise direction of the vertical tail and a width extending in a direction perpendicular to the length, and
- wherein a ratio of the length and the width of the single protrusion is in a range of 0.8 to 1.2, and
- wherein the single protrusion is shaped asymmetrically about a direction extending chordwise through the vertical tail and passing through the protrusion tip.
Dependencies are inferred from the claim text.