Vibrations due to excitation of the natural modes of an aircraft's body
are suppressed by an active multi-axis modal suppression system. Dedicated sensors
are positioned in the aircraft at optimal locations for sensing modal induced vibrations.
The sensor produced signals are processed through control logic which, in response
thereto, and in response to aircraft inertial, velocity and altitude related signals
produces output control signals. The control signals effect control surface deployment
creating forces to suppress the natural mode induced vibrations on multiple geometric
axis's. More particularly, symmetric and anti-symmetric control surface deployments
are used on one or more geometric axis's to damp lateral, longitudinal, vertical
and most importantly torsional vibrational modes.
