Patent ID: 9738379
Date: 2017-08-22
CPC Classifications: B64C

Claim:
1. A lift assembly for a rotorcraft, the lift assembly configured to fasten in removable manner to a fuselage of a rotorcraft and comprising: a fixed wing comprising in succession in a transverse direction: a left lift segment; a central box for fastening to the fuselage; and a right lift segment; the wing having at least two spars extending from the left lift segment to the right lift segment, the wing extending in elevation from a pressure side to a suction side and longitudinally from a leading edge to a trailing edge; a main gearbox extending in elevation from a bottom towards a top, the main gearbox having a mast for setting in rotation a lift rotor, the main gearbox passing through an opening in the suction side of the central box so that the bottom of the main gearbox is attached to a resilient suspension system arranged at the level of the pressure side of the central box, wherein the top projects from the central box and is fastened to at least one of the at least two spars by at least three suspension bars; and a reversible fastener system having a plurality of fastener means for reversibly fastening the central box to a plurality of fastener points of the fuselage; wherein the at least two spars include a leading edge spar and a trailing edge spar, each of the at least three suspension bars is fastened via a fitting to the leading edge spar or the trailing edge spar, the central box extends transversely from a left side beam to a right side beam, each side beam extends longitudinally from the leading edge spar to the trailing edge spar, and each side beam is secured to a stiffening piece extending between the side beam and one of the leading edge and trailing edge spars so that the central box defines a hollow inside space that receives the bottom of the main gearbox.