Aircraft with electric flight controls provided with a fuselage able to deform and vibrate

An aircraft with electric flight controls, provided with control surfaces able to be moved by electrically operated actuators, said aircraft comprising:

• controls and at least one flight control computer, said controls being actuated by a pilot and generating electric flight control datums which are sent to said flight control computer, the latter computer generating, on the basis of said electric flight control datums and flight control parameters, commands in roll, pitch and yaw, which are sent to said actuators to move said corresponding control surfaces;
• an inertial reference system comprising elements useful in navigation and elements useful in flight control, the latter elements being either of the gyrometer type or the accelerometer type;
• and
• a fuselage able to deform and vibrate with the formation of vibration nodes and antinodes distributed along the longitudinal axis of said aircraft,
• wherein:
• said inertial reference system has an exploded structure with said elements useful in flight control separated from said elements useful in navigation;
• said elements useful in flight control are distributed along said fuselage;
• each element useful in flight control, of the gyrometer type, is arranged at a vibration node of said fuselage;
• each element useful in flight control, of the accelerometer type, is arranged at a vibration antinode of said fuselage;
• and
• said elements useful in flight control are connected to said flight control computer so that the measurement signals they deliver are used as flight control parameters.