Patent ID: 9051042
Filing Date: 2015-06-09
Classification: B64C,Y02T

Abstract:
1. An aircraft, comprising: a fuselage extending along a longitudinal axis, the said fuselage comprising a central portion and a rear portion; wherein the central portion is separated from the rear portion by a bulkhead, wherein the rear portion includes at least one support surface including a rear end of the fuselage, the support surface bearing at least one stabilizer including at least a horizontal stabilizer and a substantially vertical stabilizer, wherein said support surface and the at least one stabilizer pivot in relation to the central portion around at least one axis of the aircraft, said at least one axis including a pitch axis, wherein the at least one stabilizer or the support surface is equipped with at least one control surface, wherein the rear portion includes a fixed portion and a moveable portion that includes the support surface including the rear end, the horizontal stabilizer and the substantially vertical stabilizer, wherein the fixed portion remains fixed in relation to the central portion when the moveable portion pivots, wherein activation means to pivot the moveable portion are provided between the bulkhead and the support surface, wherein the fixed portion includes a first rib rearward of the bulkhead, the moveable portion includes a second rib onto which the support surface is mounted, and the activation means is between the first and the second rib.