Patent ID: 8639399

Claim:
An aircraft, said aircraft comprised of a nonrotating vehicle structure, said nonrotating vehicle structure including a plurality of distributed active vibration control system sites, with said aircraft including: at least a first distributed active vibration circular force generator, said first distributed active vibration circular force generator fixed to said nonrotating vehicle structure at a first distributed active vibration control system site, at least a second distributed active vibration circular force generator, said second distributed active vibration circular force generator fixed to said nonrotating vehicle structure at a second distributed active vibration control system site, a plurality of electrical power distribution lines, said electrical power distribution lines connecting said circular force generators with a power source, a distributed circular force generator data communications network, said distributed circular force generator data communications network linking together at least said first distributed active vibration circular force generator and at least said second distributed active vibration circular force generator, with at least said first distributed active vibration circular force generator and at least said second distributed active vibration circular force generator communicating circular force generator vibration control data through said distributed force generator data communications network independently of said electrical power distribution lines, with said first distributed active vibration circular force generator and said second distributed active vibration circular force generator outputting circular forces into said nonrotating vehicle structure to minimize a plurality of troublesome vibrations.