Abstract: A computer-assisted medical device includes a first articulated arm, a second articulated arm, an arm stabilizer, and a control system. The arm stabilizer includes first and second clamps and one or more sensors. The first and second clamps are configured to couple the arm stabilizer to the first and second articulated arms. At least one of a distance or a relative orientation between the first and second clamps is adjustable and the one or more sensors are configured to determine the distance or relative orientation. The control system is configured to implement a following mode in which the control system drives movement of the second articulated arm in response to movements of the first articulated arm and the arm stabilizer.

Abstract: A control device includes a housing having a base portion and an extension portion. The base portion of the housing has an inward facing side and an outward facing side. The control device includes a lever coupled to and pivotable relative to the housing, and a master cylinder portion supported by the housing. The master cylinder portion has a hollow fluid cylinder. The control device also includes a piston assembly supported by the housing. The piston assembly is movable relative to the master cylinder portion. At least part of the piston assembly is disposed within the master cylinder portion. The master cylinder portion is angled relative to the outward facing side of the base portion of the housing, such that the first end of the fluid cylinder is closer to the outward facing side than the second end of the fluid cylinder is relative to the outward facing side.

Abstract: The present disclosure provides an improved circular force generator having a housing configured to reduce vibrational forces transmitted to an aircraft structure. Additionally, the disclosed configuration provide the necessary safety redundancies required by the aviation industry. The circular force generator includes mounting point around the exterior of the CFG housing and a central mounting point thereby providing redundant mounting points.

Abstract: Systems and method for active vibration control on an aircraft. An active vibration control system (AVCS) is configured for an aircraft having an aircraft structure and a gun. The AVCS includes at least one control sensor on the aircraft, at least one force generator on the aircraft, and at least one controller in electronic communication with the sensor and the force generator. The controller is configured for determining, using the at least one control sensor, force generating commands for controlling vibrations acting on the aircraft structure, sending the force generating commands to the at least one force generator, causing the at least one force generator to produce a vibration canceling force, determining that the gun is firing, and in response to determining that the gun is firing, determining different force generating commands and sending the different force generating commands to the at least one force generator.

Abstract: Systems and methods for measuring a clearance between a rotating machine component and a sensor unit are disclosed. In some aspects, a system includes a sensor unit oriented to detect the rotating machine component as the rotating machine component rotates past the sensor unit, the sensor unit including at least a first sensing element and a second sensing element spaced apart from the first sensing element. The system includes a sensor processing unit in electrical communication with the sensor unit. The sensor processing unit is configured for receiving a first waveform from the first sensing element; receiving a second waveform from the second sensing element; and determining, based on a comparison between the first waveform and the second waveform, a distance between the blade tip and the sensor unit.

Abstract: Torque sensing devices, systems, and methods are capable of measuring and/or determining a torque being transmitted through a shaft by measuring the torsional deformation of the shaft over a short length thereof. Such devices, systems, and devices have a sensor positioned adjacent to the outer surface of the shaft as it rotates, the sensor being positioned to maintain a substantially constant distance between the sensor and the outer surface of the shaft. The sensors may be variable reluctance (VR) sensors rigidly attached to a frame mounted on a bearing (e.g., a hanger bearing), which is mounted on the shaft, such that relative radial motion between the shaft and the VR sensor is minimized (e.g., so that they move in unison). Reducing this amount of motion results in a more accurate torque measurement.

Abstract: Systems and method for active vibration control on an aircraft. An active vibration control system (AVCS) is configured for an aircraft having an aircraft structure and a gun. The AVCS includes at least one control sensor on the aircraft, at least one force generator on the aircraft, and at least one controller in electronic communication with the sensor and the force generator. The controller is configured for determining, using the at least one control sensor, force generating commands for controlling vibrations acting on the aircraft structure, sending the force generating commands to the at least one force generator, causing the at least one force generator to produce a vibration canceling force, determining that the gun is firing, and in response to determining that the gun is firing, determining different force generating commands and sending the different force generating commands to the at least one force generator.

Abstract: Actuators are components of machines, which move and/or control a mechanism or system. During operation, actuators can experience regeneration events, with the actuator actually generating excess energy (e.g., regenerative energy) which must be stored or dissipated to avoid damaging the power supply. An actuator motor controller is configured to implement field oriented voltage control and flux weakening voltage control without current sensors. Dissipating regenerative energy includes providing a motor controller to command a motor drive to modify an input voltage, or to dissipate regenerative energy in a dump circuit. This command can cause motor windings to dissipate regenerative energy. Systems having a plurality of actuators distribute regenerative energy from one actuator to another. A central controller provides centralized regeneration dissipation control for the plurality of actuators.

Abstract: Actuators are components of machines, which move and/or control a mechanism or system. During operation, actuators can experience regeneration events, with the actuator actually generating excess energy (e.g., regenerative energy) which must be stored or dissipated to avoid damaging the power supply. An actuator motor controller is configured to implement field oriented voltage control and flux weakening voltage control without current sensors. Dissipating regenerative energy includes providing a motor controller to command a motor drive to modify an input voltage, or to dissipate regenerative energy in a dump circuit. This command can cause motor windings to dissipate regenerative energy. Systems having a plurality of actuators distribute regenerative energy from one actuator to another. A central controller provides centralized regeneration dissipation control for the plurality of actuators.

Abstract: An active vibration control system (AVCS) and method for reducing motion and/or vibration of a seat frame within an aircraft includes vibration sensors, a controller, and force generators. In some embodiments, the vibration sensors and/or the force generators are attached to the seat frames. In other embodiments, the vibration sensors and/or the force generators are attached to aircraft structures, proximate to the seat frame. By monitoring the motion and/or vibration of the seat frame, the controller calculates a cancelling force to be generated by the force generators to reduce the vibration experienced by the seat frame and its occupant. Such seat frame vibration control can be implemented as a separate AVCS in an aircraft, or can be integrated in an existing AVCS that is also configured to provide vibration control in other parts thereof.

Abstract: Actuators are components of machines, which move and/or control a mechanism or system. During operation, actuators can experience regeneration events, with the actuator actually generating excess energy (e.g., regenerative energy) which must be stored or dissipated to avoid damaging the power supply. An actuator motor controller is configured to implement field oriented voltage control and flux weakening voltage control without current sensors. Dissipating regenerative energy includes providing a motor controller to command a motor drive to modify an input voltage, or to dissipate regenerative energy in a dump circuit. This command can cause motor windings to dissipate regenerative energy. Systems having a plurality of actuators distribute regenerative energy from one actuator to another. A central controller provides centralized regeneration dissipation control for the plurality of actuators.

Abstract: A control system for resonant inertial actuators estimates operating parameters of the resonant inertial actuators based on voltage and current feedback and dynamically limits selected parameters to maintain the safe, efficient, and cost effective operation of the resonant inertial actuators. Resistance within the electrical drives for the resonant inertial actuators is estimated from the voltage and current feedback and in conjunction with the modeling of the resonant inertial actuators other operating parameters are calculated or otherwise estimated. Having regard for the responsiveness of the resonant inertial actuators to changes in command signals, the command signals are adjusted to dynamically limit the estimated parameters.

Abstract: Structural health monitoring and protection systems and methods are provided. System and methods utilize structural information and/or enhanced built in testing capabilities for detecting failure modes that may cause damage to a structure. Systems and methods herein may protect a structure by mitigating one or more incorrect forces. The structure may be an aircraft, a rotary wing aircraft, or any other physical structure subject to vibrations and receptive to canceling of those vibrations.

Abstract: Rotary motion sensing systems are well-suited for integration in a bearing system of a rotary aircraft to provide information about the operational state of the rotor blades of the aircraft. In some embodiments, sensors are positioned on lateral sides of an elastomeric bearing system and output signals which may be processed to calculate one or more rotor blade operational states. The operational states include, for example, flap angle, lead-lag angle, and pitch angle. In other embodiments, sensors may be distributed along at least a portion of the length of a rotor blade to detect deflection of the rotor blade or its impact with another object. The operational state of the rotor blades may be transmitted to the pilot and/or the flight control computer of the aircraft in order for corrective action to be taken and/or may be stored within a control box for later review.

Abstract: Redundant active vibration and noise control systems and methods are provided, which include safety-critical systems and methods. In one embodiment, a safety-critical active vibration control system (SCAVCS) is provided, which includes a plurality of digital buses, a force generator, at least one sensor and at least one system parameter. The at least one force generator is in electronic communication with at least two digital buses. The force generator includes a pair of unbalanced masses, at least one motor, at least one microprocessor, at least one speed sensor, at least one accelerometer, and at least one power input. The at least one sensor is in electronic communication with each of the digital buses and with each of the microprocessors. The at least one system parameter is in electronic communication with each of the digital buses and each of the microprocessors.

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

Abstract: A control system for resonant inertial actuators estimates operating parameters of the resonant inertial actuators based on voltage and current feedback and dynamically limits selected parameters to maintain the safe, efficient, and cost effective operation of the resonant inertial actuators. Resistance within the electrical drives for the resonant inertial actuators is estimated from the voltage and current feedback and in conjunction with the modeling of the resonant inertial actuators other operating parameters are calculated or otherwise estimated. Having regard for the responsiveness of the resonant inertial actuators to changes in command signals, the command signals are adjusted to dynamically limit the estimated parameters.

Abstract: Structural health monitoring and protection systems and methods are provided. System and methods utilize structural information and/or enhanced built in testing capabilities for detecting failure modes that may cause damage to a structure. Systems and methods herein may protect a structure by mitigating one or more incorrect forces. The structure may be an aircraft, a rotary wing aircraft, or any other physical structure subject to vibrations and receptive to canceling of those vibrations.

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

Abstract: Redundant active vibration and noise control systems and methods are provided, which include safety-critical systems and methods. In one embodiment, a safety-critical active vibration control system (SCAVCS) is provided, which includes a plurality of digital buses, a force generator, at least one sensor and at least one system parameter. The at least one force generator is in electronic communication with at least two digital buses. The force generator includes a pair of unbalanced masses, at least one motor, at least one microprocessor, at least one speed sensor, at least one accelerometer, and at least one power input. The at least one sensor is in electronic communication with each of the digital buses and with each of the microprocessors. The at least one system parameter is in electronic communication with each of the digital buses and each of the microprocessors.