Patent ID: 8360357

Claim:
An aircraft comprising: a fuselage, a wing integral with the fuselage at a point on a rigid central wing box, wherein sections of the wing are located on sides of the rigid central wing box and integral and fixed relative to the wing box to form a rigid wing, and a tail assembly integral with the fuselage, wherein the wing is mounted movably in translation relative to the fuselage along a longitudinal X direction of the aircraft essentially parallel to an axis of said fuselage between an extreme forward position Xav and an extreme rear position Xar of a point of reference of said wing, and wherein the rigid central wing box is determined in the front by a wing box front spar, in the rear by a wing box rear spar, and laterally by root ribs, wherein the sections of the wing comprise external front and external rear spars, the external front and external rear spars integral with and fixed relative to the wing box front spars and wing box rear spars to form the rigid wing.