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

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

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

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

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

Abstract: A magneto-rheological fluid valve includes a magnetic field generator having at least one electromagnetic coil and at least one magnetic pole having a pole length Lm. The magneto-rheological fluid valve further includes at least one flow channel adjacent to the electromagnetic coil. The at least one flow channel has a gap width g, wherein the ratio Lm/g is greater than or equal to 15.

Abstract: A magneto-rheological fluid damper includes a damper body having a reservoir for a magneto-rheological fluid, a piston rod, a piston rod guide disposed within the damper body, where the piston rod guide has a passage therein for receiving the piston rod. The magneto-rheological fluid damper further includes at least a first piston rod seal and at least a second piston rod seal arranged to seal between the piston rod guide and the piston rod. The magneto-rheological fluid damper further includes a fluid chamber defined between the piston rod guide and the piston rod, the fluid chamber being in communication with the reservoir. The magneto-rheological fluid damper further includes a piston rod guide filter arranged in a communication path between the fluid chamber and the reservoir to filter particulates out of the magneto-rheological fluid entering the fluid chamber. The magneto-rheological fluid damper further includes an accumulator arranged between the piston rod guide and the damper body.

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 turbine engine with a takeoff fan speed and a landing fan speed, the aircraft engine includes a fan duct with a HQ (Herschel-Quincke) acoustic control noise reduction tube. The acoustic control noise reduction tube contains a movable frequency tuner obstruction. The movable frequency tuner obstruction is movable within the acoustic control noise reduction tube, with the movable frequency tuner obstruction movable along a fixed tube path length between a first takeoff frequency obstruction tube path location, and a second landing frequency obstruction tube path location, with the frequency tuner obstruction positioned at the first takeoff frequency location with the takeoff speed, and the frequency tuner obstruction positioned at the second landing frequency location with the landing speed to reduce noise.

Abstract: A damper device comprising a first mode having a first level of damping, a second mode having a second level of damping corresponding to a predetermined function, a sensor system having a first output corresponding to a normal position and a second output corresponding to an end stop approaching position, and a control system operable for receiving the first output and the second output and executing the first mode and the second mode. The damper device is operable in the first mode when the control system receives the first output and is operable in the second mode when the control system receives the second output.

Abstract: A controllable suspension system for controlling the relative motion between a first body and a second body includes at least one strut including a magneto-rheological fluid damper. The fluid damper includes a piston rod guide disposed within a damper body. The piston rod guide has a passage therein for receiving a piston rod. A piston rod bearing assembly is disposed in the piston rod guide to engage with and support reciprocal motion of the piston rod. At least a first piston rod seal and at least a second piston rod seal are arranged to seal between the piston rod guide and the piston rod. A fluid chamber is defined between the piston rod guide and the piston rod. A piston rod guide gas charged accumulator is arranged between the piston rod and the damper body.

Abstract: A magneto-rheological fluid damper includes a damper body having a reservoir for a magneto-rheological fluid, a piston rod, a piston rod guide disposed within the damper body, where the piston rod guide has a passage therein for receiving the piston rod. The magneto-rheological fluid damper further includes at least a first piston rod seal and at least a second piston rod seal arranged to seal between the piston rod guide and the piston rod. The magneto-rheological fluid damper further includes a fluid chamber defined between the piston rod guide and the piston rod, the fluid chamber being in communication with the reservoir. The magneto-rheological fluid damper further includes a piston rod guide filter arranged in a communication path between the fluid chamber and the reservoir to filter particulates out of the magneto-rheological fluid entering the fluid chamber. The magneto-rheological fluid damper further includes an accumulator arranged between the piston rod guide and the damper body.

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: Please replace the Abstract with the following amended Abstract: A magneto-rheological fluid valve includes a magnetic field generator having at least one electromagnetic coil and at least one magnetic pole having a pole length Lm. The magneto-rheological fluid valve further includes at least one flow channel adjacent to the magnetic field generator. The at least one flow channel has a gap width g, wherein the ratio Lm/g is greater than or equal to 15.

Abstract: An aircraft turbine engine with a takeoff fan speed and a landing fan speed, the aircraft engine includes a fan duct with a HQ (Herschel-Quincke) acoustic control noise reduction tube. The acoustic control noise reduction tube contains a movable frequency tuner obstruction. The movable frequency tuner obstruction is movable within the acoustic control noise reduction tube, with the movable frequency tuner obstruction movable along a fixed tube path length between a first takeoff frequency obstruction tube path location, and a second landing frequency obstruction tube path location, with the frequency tuner obstruction positioned at the first takeoff frequency location with the takeoff speed, and the frequency tuner obstruction positioned at the second landing frequency location with the landing speed to reduce noise.

Abstract: A system and method for absorbing vehicle body vibrations is described. The mechanical self-tuning vibration absorber system is utilized to absorb a body vibration with a varying frequency. In a particular application the absorber system provides for absorbing varying frequency vibrations of a helicopter aircraft body. The vibration absorber system utilizes asymmetrical damping to tune the resonant frequency of the system.

Abstract: A damper device comprising a first mode having a first level of damping, a second mode having a second level of damping corresponding to a predetermined function, a sensor system having a first output corresponding to a normal position and a second output corresponding to an end stop approaching position, and a control system operable for receiving the first output and the second output and executing the first mode and the second mode. The damper device is operable in the first mode when the control system receives the first output and is operable in the second mode when the control system receives the second output.

Abstract: A system and method for absorbing vehicle body vibrations is described. The mechanical self-tuning vibration absorber system is utilized to absorb a body vibration with a varying frequency. In a particular application the absorber system provides for absorbing varying frequency vibrations of a helicopter aircraft body. The vibration absorber system utilizes asymmetrical damping to tune the resonant frequency of the system.

Abstract: A controlled equilibrium device comprising a housing; at least one spring, each at least one spring having a spring stiffness; and a load leveling device movable through the housing between a first maximum displacement position and a second maximum displacement position, the load leveling device comprising a deadband displacement zone defined between a first deadband displacement threshold and a second deadband displacement threshold, the displacement required to reach the first and second deadband displacement thresholds being less than the displacement distances required to reach the first and second maximum displacement positions, the at least one spring stiffness being substantially constant when the displacement of the load leveling device is within the deadband zone, the stiffness of the at least one spring being modified to a second stiffness when the load leveling device is equal to or beyond either the first deadband displacement threshold or the second deadband displacement threshold.