A hydrokinetic torque coupling device comprises a casing, a torque converter, a torsional vibration damper and a lockup clutch disposed within the casing. The torque converter comprises an impeller and a turbine-piston coaxially aligned with the impeller and axially movable toward and away from the casing to position the hydrokinetic torque coupling device into and out of a lockup mode in which the turbine-piston is non-rotatably frictionally coupled to the casing. The torsional vibration damper comprises an input member non-moveably secured to the turbine-piston, a first retainer plate and the elastic members elastically coupling the input member to the first retainer plate. The input member includes an actuating portion configured to actuate the lockup clutch. The lockup clutch is disposed within the casing between the actuating portion of the input member and a cover shell of the casing for frictionally coupling the casing and the turbine-piston.

Systems and methods provide for the mitigation of vibrational forces acting on a horizontal stabilizer of an aircraft. According to one aspect, a damper is coupled to a front portion of a horizontal stabilizer to dampen vibrations in a first degree of freedom, with another damper coupled to a mounting point of the horizontal stabilizer to dampen vibrations in a second degree of freedom. The dampers may be passive, operating independently to mitigate vibrational forces, or active, applying a mitigating force to the horizontal stabilizer based on real-time or estimated vibration states.

A three-loop inertial stabilization system with active jitter suppression and optical control to reduce line-of-sight (LOS) jitter based on platform induced motion in cantilevered gimbal systems. A first loop comprises at least one rate sensor, a Kalman state estimator, and a rate to angle module. A second loop comprises a mirror system, a focal plane and centroid processing module, an open-loop closed loop selector, a signal combiner and a loop integrator. A third loop comprises a fast steering mirror, offload module and at least one gimbal motor driver, wherein the three loops suppress the jitter of the cantilevered gimbal system.

An electromagnetic actuator including: an inner axial member; an outer housing member; a stator and a mover configured to have electromagnetic oscillation force exerted between them, each being securely assembled to different one of the members; and plate springs elastically connecting the members at opposite axial sides thereof, wherein the outer housing member includes an outer tubular member and first and second lid members attached to opposite axial openings thereof, and a first axial side of the outer tubular member has a small-diameter constricted section, and the constricted section has axially inner and outer stepped walls, and the axially inner stepped wall positions a first axial side of the stator or the mover assembled to the outer housing member, while the axially outer stepped wall and the first lid member support a periphery of the corresponding plate spring.

An electrically driven actuator includes a vibration damping device; and an electrically driven unit operated by using electricity. The vibration damping device includes a vibration absorbing unit provided between a first support and a second support provided to face the first support, and expanding and contracting by using electricity, a measurement unit that measures vibrations of the second support, and a control unit that electrically controls the vibration absorbing unit to cancel the vibrations of the second support which are measured by the measurement unit. The electrically driven unit includes a housing provided on a fixed side, a shaft movable in an axial direction which is a direction toward a movable side opposite to the fixed side with respect to the housing, and a drive unit provided between the housing and the shaft, and driving the shaft with respect to the housing.

An air compressor assembly may include a support structure, an operating unit including a compressor operatively connected to a motor through at least one drive belt, and at least one vibration isolator that is positioned between at least a portion of the support structure and at least a portion of the operating unit. The vibration isolator(s) is configured to dampen vibratory energy generated by the operating unit.

A bearing includes a bearing pad for supporting a rotary component and a housing attached to or formed integrally with the bearing pad. The housing includes a flexible column extending towards the bearing pad for providing the bearing pad with an airflow. The column supports the bearing pad from a location inward of an outer periphery of the bearing pad along an axial direction of the bearing. With such a configuration, a resistance of the bearing pad along a radial direction of the bearing is less at the outer periphery than a resistance of the bearing pad along the radial direction proximate the column.

A variable inertia flywheel having revolute joint assemblies, a roller guide, a first actuator and a second actuator. The revolute joint assemblies are in engagement with a primary mover and include a first member, a second member and a roller. The roller guide is disposed about the revolute joint assemblies. An inner surface of the roller guide is in contact with the rollers and defines cam profiles that cause the rollers to extend and contract, creating a torque disturbance opposed to a primary mover torque ripple. The first actuator is in engagement with the roller guide and moves the roller guide, changing the amplitude and/or the phase angle of the torque ripple. The second actuator is in engagement with the roller guide and rotates the roller guide, changing the phase angle of the torque ripple.

The present invention relates to a device which can measure, induce, and correct perturbations acting on an electromagnetic (EM) propagation source. Piezoelectric transducers are used to measure and control perturbations within a system to improve operation of an EM source. Perturbation measurements can be used to determine the environmental and system impacts on the EM source. Moreover, measurements can be used to correct or nullify perturbations applied to the EM source, through active or passive means.

A method of operating a vibration control system (VCS) using a single actuator which operates to attenuate a system frequency of a system is provided. The method includes determining whether current vibrations at a non-system frequency exceed a predefined level, determining a system response to compensate for the current vibrations exceeding the predefined level and adjusting the force response of the single actuator to respond to a system frequency and the non-system frequency according to the determined system response toward compensating for the current vibrations.