Method and system for determining the attitude of an aircraft by multi-axial accelerometric measurements

The method involves determining an angle of pitch and/or an angle of heading and/or an angle of roll of an aircraft (100). A first pair of accelerometers (A5, A6) used for determination of the angle of heading is arranged on a side of a center of gravity (G) along an axis merged with a transverse axis of the aircraft. A second pair of accelerometers (A3, A4) used for determination of the angle of roll is arranged on a side of the center of gravity along a vertical axis (z) perpendicular to a plane formed by other axes (x, y). An independent claim is also included for an inertial navigation system.