US 10,538,308 B2Granted

Aircraft empennage

AssigneeAirbus Operations S.L.

InventorsCarlos Garcia Nieto, Fernando Pereira Mosqueira, Iker Velez De Mendizabal Alonso, Enrique Guinaldo Fernandez, Francisco Javier Honorato Ruiz

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Abstract

An aircraft aerodynamic surface (1) including a torsion box (2) having a front spar (21) and rear spar (22), a first control surface (3) including a front spar (31) and a trailing edge (32) and a second control surface (4) having a front spar (41), a trailing edge (42), and a pivot device (5, 6, 7, 8) for pivotally attaching the first control surface (3) and the second control surface (4) to the rear spar (22) of the torsion box (2), the first control surface is an inboard control surface (4) including two lateral ribs (9, 9′), six inner ribs (11, 12, 13, 14, 15, 10) and an inner spar (16), and the second control surface (3) is an outboard control surface which includes two lateral ribs (20, 20′), three internal ribs (17, 18, 19), two internal spars (24, 24′) and one internal spar (23).

Claims12

Dependent claims

An aircraft aerodynamic surface comprising a torsion box having a front spar and rear spar, a first control surface comprising a front spar and a trailing edge and a second control surface comprising a front spar, a trailing edge, and means for pivotally attaching the first control surface and the second control surface to the rear spar of the torsion box,

wherein the first control surface is an inboard control surface which comprises:
a first lateral rib and a second lateral rib attached each one either to the trailing edge and to the front spar arranged,
six inner ribs located between the two lateral ribs wherein one inner rib of the six inner ribs is a central rib extended from the trailing edge to the front spar arranged so as to define an angle α4 with the spar in the range between 75° to 95°,
a first inner rib and a second inner rib of the six inner ribs are located between the first lateral rib and the central rib and inclined an angle α2, α3 towards the first lateral rib, and
a third inner rib, a fourth inner rib and a fifth inner rib of the six inner ribs are located between the second lateral rib and the central rib and inclined an angle α5, α6, α7 towards the second lateral rib, and
an inner spar parallel to the front spar and to the trailing edge, attached to the central rib and extended from the second inner rib inclined towards the first lateral rib to the third inner rib inclined towards the second lateral rib, and
the second control surface is an outboard control surface which comprises:
a first outboard lateral rib and a second outboard lateral rib, attached each one either to the trailing edge and to the front spar of the outboard control surface and arranged to define each lateral rib an angle, β1, β5,
three internal ribs located between the two lateral ribs wherein one of the three internal ribs is a central rib extended from the trailing edge to the front spar arranged to define an angle β3 with the spar in the range between 80° to 100°,
a second rib of the three internal ribs is located between the first lateral rib and the central rib and inclined towards the first lateral rib,
a third rib of the three internal ribs is located between the second lateral rib and the central rib, inclined towards the second lateral rib,
two internal spars parallel to the front spar and the trailing edge extended from the first lateral rib to the second lateral rib, and
one internal spar parallel to the front spar and the trailing edge extended from the second rib to the third rib.

10 more elements

An aircraft aerodynamic surface comprising:

a torsion box including a front spar and a rear spar;
a first control surface comprising a front spar and a trailing edge;
a second control surface comprising a front spar and a trailing edge, and
hinge fittings configured to pivotally attach the first control surface and the second control surface to the rear spar of the torsion box,
wherein the first control surface is an inboard control surface which comprises:
a first lateral rib and a second lateral rib each attached to at least one of the trailing edge and to the front spar arranged,
between the first and second lateral ribs are:
a central rib extending from the trailing edge to the front spar and defining an angle α4 with the front spar in a range of 75° to 95°,
first and second inner ribs between the first lateral rib and the central rib and inclined towards the first lateral rib, and
third, fourth and fifth inner ribs between the second lateral rib and the central rib and inclined towards the second lateral rib, and
an inner spar parallel to the front spar, attached to the central rib and extending from the second inner rib to the third inner rib, and
wherein the second control surface is an outboard control surface which comprises:
a first outboard lateral rib and a second outboard lateral rib each, attached to at least one of the trailing edge and the front spar of the outboard control surface and arranged to define each lateral rib an angle, β1, β5, respectively;
between the first and second outboard later ribs are:
a central inner rib extending from the trailing edge to the front spar arranged to define an angle β3 with the spar in the range between 80° to 100°;
a second inner rib between the first lateral rib and the central rib and inclined towards the first lateral rib,
a third inner rib between the second lateral rib and the central rib and inclined towards the second lateral rib,
internal spars parallel to the front spar and the trailing edge extended from the first lateral rib to the second lateral rib, and
at least one internal spar is parallel to the front spar and the trailing edge extended from the second rib to the third rib.

16 more elements

Dependencies are inferred from the claim text.