Abstract: A rotary wing aircraft including a vehicle vibration control system.

Abstract: A rotary wing aircraft including a vehicle vibration control system.

Abstract: Systems and methods for producing bioproducts are shown. The systems and methods herein can be configured and used in an integrated biorefinery. The integrated biorefinery may comprise a sugar production facility such as a sugar mill, a production facility for one or more bioproduct(s) such as butanol, and optionally an ethanol production facility employing the system and method.

Abstract: A rotary wing aircraft including a vehicle vibration control system.

Abstract: A method and system is disclosed for controlling problematic vibrations in an aircraft having. The method and system have the ability to cancel problematic rotary wing helicopter vibrations using independent active force generator power and with distributed communications therebetween.

Abstract: Systems and methods for producing bioproducts are shown. The systems and methods herein can be configured and used in an integrated biorefinery. The integrated biorefinery may comprise a sugar production facility such as a sugar mill, a production facility for one or more bioproduct(s) such as butanol, and optionally an ethanol production facility employing the system and method.

Abstract: A rotary blade rotating hub mounted rotating assembly vibration control system including a first imbalance mass concentration rotor, a second imbalance mass concentration rotor, a third imbalance mass concentration rotor, and a fourth imbalance mass concentration rotor. The first imbalance mass concentration rotor has a first imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The second imbalance mass concentration rotor has a second imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The third imbalance mass concentration rotor has a third imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis. The fourth imbalance mass concentration rotor has a fourth imbalance mass concentration rotor center axis rotation centered on the rotating assembly center rotation axis.

Abstract: A method and system is disclosed for controlling problematic vibrations in an aircraft having. The method and system have the ability to cancel problematic rotary wing helicopter vibrations using independent active force generator power and with distributed communications therebetween.

Abstract: A rotary wing aircraft including a vehicle vibration control system.

Abstract: A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotating hub mounted vibration control system, the rotating hub mounted vibration control system mounted to the rotating rotary wing hub with the rotating hub mounted vibration control system rotating with the rotating rotary wing hub.

Abstract: An aircraft with an aerostructure and at least one rotating machine creating troublesome vibrations, with the aircraft including a power source outputting electromagnetic force generator power outputs, a first and second distributed active vibration electromagnetic force generator, the first and second force generator including a distributed electronic control system and an electromagnetically driven mass, the force generators fixed to the aerostructure at first and second distributed active vibration control system sites, and electrical power distribution lines connecting the force generators with the power source with the power outputs outputted to the electromagnetic force generators, and a distributed force generator data communications network linking together the first and second distributed electronic control systems wherein the distributed electronic control systems communicate force generator vibration control data through the distributed force generator data communications network independently of t

Abstract: A rotary blade rotating hub mounted rotating assembly vibration control system (20) including a first imbalance mass concentration rotor (28), a second imbalance mass concentration rotor (44), a third imbalance mass concentration rotor (38?), and a fourth imbalance mass concentration rotor (44?). The first imbalance mass concentration rotor has a first imbalance mass concentration rotor center axis of rotation (136) centered on the rotating assembly center rotation axis (28). The second imbalance mass concentration rotor has a second imbalance mass concentration rotor center axis of rotation (142) centered on the rotating assembly center rotation axis. The third imbalance mass concentration rotor has a third imbalance mass concentration rotor center axis of rotation (136?) centered on the rotating assembly center rotation axis. The fourth imbalance mass concentration rotor has a fourth imbalance mass concentration rotor center axis of rotation (142?) centered on the rotating assembly center rotation axis.

Abstract: An aircraft with at least one rotating machine creating troublesome vibrations, the aircraft comprised of an aerostructure, the aircraft including: a power source, the power source outputting a plurality of electromagnetic force generator power outputs, the aerostructure including a plurality of distributed active vibration control system sites, at least a first distributed active vibration electromagnetic force generator, the first distributed active vibration electromagnetic force generator including a first distributed electronic control system and a first electromagnetically driven mass, the first distributed active vibration electromagnetic force generator fixed to the aerostructure at a first distributed active vibration control system site, at least a second distributed active vibration electromagnetic force generator, the second distributed active vibration electromagnetic force generator including a second distributed electronic control system and a second electromagnetically driven mass, the seco

Abstract: A vibration-damped machine and method including beam being capable of gross movements in space relative to a stationary frame, means including a motor for causing the beam's gross movements; the gross movements tending to induce vibration into the beam, sensors for providing a signal representative of the induced beam vibration, an linear-acting inertial actuator mounted to the beam, and control means for receiving the signal and generating an output signal to actively drive the linear-acting inertial actuator at the appropriate phase, frequency and magnitude to damp induced beam vibrations. Embodiments of the vibration-damped machine are illustrated for a gantry robot, a horizontal machining center, an adhesive dispenser and a pivoting robot. The linear-acting inertial actuator is preferably controlled according to an inertial damping control method where the actuator is forced to behave as a damper attached to ground.