Patent ID: 8820673
Filing Date: 2014-09-02
Classification: B64C

Abstract:
1. An aircraft provided with a fuselage extending along a roll axis (AXR) from a front end to a rear end, and along a pitching axis (AXT) from a first side to a second side, the aircraft having a rotary wing above the fuselage and a fixed wing, the aircraft having a control system for controlling the pitch of the blades of the rotary wings, the rotary wing being above both the fuselage and the fixed wing, said fixed wing being made up of at least one wing comprising: a first half-wing extending parallel to the pitching axis from said first side, and a second half-wing extending parallel to the pitching axis from said second side, wherein each half-wing is provided with a top lift portion and a bottom lift portion, said bottom lift portion of a half-wing being arranged in the wake (S) of the top lift portion of that half-wing, the wake (S) being generated by a stream of air (F) coming from said rotary wing and impacting against the top face of the top lift portion when said aircraft is hovering, wherein each top lift portion extends from a top proximal end arranged against the fuselage towards a top distal end, each bottom lift portion extending from a bottom proximal end in the proximity of the fuselage to a bottom distal end remote from said fuselage, with each top distal end being connected to a bottom distal end, and wherein each top distal end is secured and fastened directly to a bottom distal end.