Aircraft multi-axis modal suppression system

An aircraft multi-axis control system comprising a plurality of anti-symmetric control inputs on a first control axis for counteracting the effects of control inputs or structural resonances on a further control axis.

A system for providing structural mode suppression on a plurality of geometric axis of an aircraft having a plurality of axis flight controls for reducing structural resonances of airfoil, and aircraft body bending and torsional moments.

A system for providing structural mode suppression on a plurality of geometric axis of an aircraft having a plurality of axis flight controls for reducing structural resonances of airfoil, and aircraft body bending and torsional forces.

An active modal suppression system method including the steps of:

• monitoring aircraft structural vibrations due to excitation of natural aircraft bending on torsional modes;
• and, moving aircraft control surfaces to reduce flexible motion without affecting rigid body motion.

An active modal suppression system method including the steps of:

• monitoring aircraft structural vibrations due to excitation of natural aircraft bending on torsional modes;
• and, moving aircraft control surfaces to reduce flexible motion in conjunction with controlling the rigid body motion.

A method for providing modal suppression in an aircraft comprising the steps of:

• utilizing rudder movement to control the lateral body bending mode of the aircraft;
• and,
• utilizing anti-symmetric elevator control surface positions to control the body torsional mode of the aircraft.

An active multi-axis modal suppression system comprising:

• a plurality of sensors disposed in an aircraft providing information signals for suppressing structural modes;
• and,
• a plurality of canard, wing and tail deflections responsive to said information signals.

A system for suppressing vibrations due to excitation of natural modes of an aircraft having a multi-axis modal suppression control law wherein control systems and augmentation are utilized to control the modes of the rigid body modes of the aircraft.

A system for suppressing vibrations due to excitation of natural modes of an aircraft having a multi-axis modal suppression control law augmented by an integrated model suppression system.

A system for controlling the torsional vibration mode of an aircraft utilizing rudder and anti-symmetric elevator motion.

A system for controlling the lateral vibration mode of an aircraft utilizing anti-symmetric elevator and rudder motion.

A system for controlling the vertical vibration mode of an aircraft utilizing symmetric elevator motion.

A system for controlling the vertical vibration mode of an aircraft utilizing symmetric canard motion.

A system for controlling the vertical vibration mode of an aircraft utilizing symmetric flaperon and/or aileron motion.

A modal suppression system for an aircraft, the improvement comprising:

• the roll, pitch, and yaw rate gyros disposed adjacent the wing box front spar of the aircraft for reducing coupling of structural mode excitation.

A modal suppression system for an aircraft, the improvement comprising:

• the lateral & vertical accelerometers disposed adjacent the wing box front spar of the aircraft for reducing coupling of structural mode excitation.

A multi-axis modal suppression system for an aircraft having a plurality of control surfaces, said multi-axis modal suppression system having a dedicated control effector for each of a plurality of structural modes, and, any one of said plurality of control surfaces controlling different structural modes.

An integrated multi-axis modal suppression system having a modal command for controlling one of a plurality of control axis, said modal command cross-fed to a further one of said plurality of control axis thereby negating the effect of said modal command on other structural modes by inputs of other control surfaces.

A system for controlling vertical fuselage, lateral fuselage, torsional fuselage, vertical wing and torsional wing vibrational motions in an aircraft comprising utilizing rudder, symmetric elevator, anti-symmetric elevator, canard, anti-symmetric canard, symmetric flaperon and anti-symmetric flaperon control surface commands.