Patent ID: 8733700

Claim:
An aircraft comprising at least one inertial reference unit and a reference unit support fixed to a structural element of the aircraft, wherein the aircraft comprises, for each inertial reference unit: a memory including recorded support installation angles representative of angular positioning errors relative to an aircraft coordinate system of the reference unit support corresponding to said inertial reference unit, said support installation angles being determined beforehand on a basis of measurement of coordinates of points of a reference coordinate system and of characteristic points of said reference unit support; and calculating module to calculate corrected data on a basis of data measured by the inertial reference unit and corresponding support installation angles, wherein each reference unit support comprises: a platen to extend substantially horizontally in the aircraft, said platen defining a vertical direction of the support orthogonal to the platen, an axial direction and a transversal direction of the support extending in a plane of the platen and to extend substantially parallel to the pitch and roll directions of the aircraft respectively; a rear wall extending from a rear side of the platen; at least two centering pins, one of the centering pins being a front pin carried by a front edge of the platen opposite the rear wall, and another one of the centering pins being a rear pin carried by the rear wall, said front and rear pins having axes extending in the axial direction of the support, the rear pin comprising a contact surface to be integrally in contact with a case of the inertial reference unit; and two contact plates formed on the platen close to a front side of the platen opposite the rear wall, said contact plates being spaced apart in the transversal direction of the support, said contact plates being integrally in contact with the case of the inertial reference unit.