Abstract: A rotary wing aircraft bearing that provides a constrained relative motion between a first rotary wing aircraft member and a second rotary wing aircraft member. The bearing includes an elastomeric mold bonded laminated bearing stack, the elastomeric mold bonded laminated bearing stack including a plurality of mold bonded alternating layers of nonelastomeric shim member layers and elastomeric shim members layers, the alternating layers having an exterior surface and an interior center distal from the exterior surface.

Abstract: A flexible pipe joint (200) includes a body (210) having a pin-end member (230) telescopically fitted within a box-end member (220), the pin-end member (230) including an outer connection profile (235) and the box-end member (220) including a complementary inner connection profile (225), a bearing (240) including an outer bearing surface (244), wherein the bearing (240) is fitted within the body (210) such that at least a portion of an inner body surface (212) interfaces with at least a portion the outer bearing surface (244), and wherein the bearing (240) includes an inner bearing surface (243), and an extension pipe (270) including an outer extension pipe surface (289), wherein the extension pipe (270) is fitted within the bearing (240) such that at least a portion of the inner bearing surface (243) interfaces with at least a portion of the outer extension pipe surface (289).

Abstract: A riser tensioner bearing is provided. The riser tensioner bearing is an asymmetric bearing having an outer member comprising a cylindrical outer profile and an at least partially spherical interior profile, and an inner member comprising an at least partially spherical outer profile and a substantially cylindrical outer profile.

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: Systems, devices, and methods for a hub-based active vibration control (AVC) design includes at least one pair of co-rotating motorized imbalanced rotors that create a controllable rotating force vector that can be controlled to cancel hub loads on a rotating hub. This control is achievable using a configuration in which each rotor has an axis of rotation that is offset from the hub axis of rotation. In this way, in a loss of operation failure mode, the system is designed such that centrifugal forces will cause the masses to spin to an orientation of low static imbalance.

Abstract: The present subject matter relates to devices, systems, and methods for indicating degradation in a component having one or more elastomeric elements. For example, a degradation indicator can include an indicator element in communication with at least a portion of the one or more elastomeric elements, wherein the indicator element is configured to show visible degradation or damage when a specific and predetermined condition of the one or more elastomeric elements is reached.

Abstract: Aircraft support structures, systems, and methods are disclosed. In one embodiment, an aircraft system includes a rotating component and a support (e.g. strut) that supports the rotating component. The support includes a locking assembly (P1) that is configured to lock, automatically, an inner member (214) of the support with respect to an outer member (208) of the support for stiffening the support in response to reaching or exceeding a predetermined threshold amount of displacement, load, stress, or rotation. The aircraft support structures, systems, and methods herein utilize self-locking and self-unlocking supports (e.g. struts) for increasing or decreasing a stiffness of the support.

Abstract: A torque monitoring system includes a rotatable measurement interface and a stationary data receiver. The measurement interface is configured to be attached to a rotatable shaft. The measurement interface includes a strain gauge, a processor, and a near field communication (NFC) transceiver coil. The stationary data receiver is stationary with respect to the rotating shaft. The stationary data receiver includes a processor and an NFC transceiver coil. The rotatable measurement interface receives operating power via its NFC transceiver coil that is derived from a radio signal wirelessly transmitted by the NFC transceiver coil in the stationary data receiver. The processor in the rotatable measurement interface is configured to receive strain gauge signals from the strain gauge indicative of torque on the rotatable shaft and wirelessly transmit digital data indicative of the strain gauge signals through the NFC transceiver coils to the processor in the stationary data receiver.

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 double knuckle coupling suitable for transmitting torque applied to a first input shaft to a second shaft wherein the coupling accommodates angular changes between the shafts. Additionally, the disclosure describes an improved mud motor transmission incorporating the coupling.

Abstract: A pumping system is provided. The pumping system includes an output conduit, a first sensor, a second second sensor, a feedforward active controller, and a fluid flow normalizer (FFN). The output conduit is associated with an output of a positive displacement pump. The first sensor is configured to measure a fluid flow characteristic (FFC) within the output conduit. The second sensor is configured to measure a phase of the positive displacement pump. The feedforward active controller is configured to receive information related to the FFC, receive information related to the phase of the positive displacement pump, and determine an FFC variability value. The first fluid flow normalizer (FFN) is configured to at least one of add fluid to the output of the positive displacement pump and remove fluid from the output of the positive displacement pump in response to a signal from the feedforward active controller.

Abstract: An isolator (200) has an outer housing (224) comprising an outer housing bore (234), an inner member (240) received coaxially within the outer housing (224), a precompressed compression compliance component (CCC) (230) disposed between the outer housing (224) and the inner member (240), the CCC (230) being configured to bias the inner member (240) in an axial direction, and a precompressed rebound compliance component (RCC) (232) disposed between the outer housing (224) and the inner member (240), the RCC (232) being configured to bias the inner member (240) in an opposite axial direction.

Abstract: An engine mount assembly for mounting an engine which produces a torque to a body having a persistent troublesome frequency vibration is disclosed. The engine mount assembly includes two fluid elastomeric chambers groundable to the body, an intermediate cradle link disposed between the two fluid chambers, a lateral link grounded to the body and the intermediate cradle, and a fluid conduit connecting the two fluid chambers. When subjected to torque a positive fluid pressure is generated within the fluid chambers and fluid conduit with the two fluid chambers share a plurality of loads while a transfer of the persistent troublesome frequency vibration from the body to the engine is inhibited.

Abstract: An engine mount system having failsafe securement points. The engine mount system includes a forward mount carrying a coat hanger shackle having a spherical bearing and a cylindrical hearing. Securement of the engine mount to a support utilizes pins and bolts with a retaining double wrench washer incorporated into the final mounting structure. The engine mount system additionally includes an aft mount.

Abstract: A subsea pipeline system has a subsea pipe and a pipeline vibration damper (PVD) attached to the pipe.

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: Circular force generator (CFG) devices, systems, and methods are disclosed having indirectly driven imbalanced rotors for generating vibrations and/or imparting vibration control. A CFG device (10) includes a first set of imbalanced rotors (12) disposed about a center point and a second set of imbalanced rotors (12) disposed about the center point. The first set of imbalanced rotors is configured to co-rotate synchronously. The second set of imbalanced rotors is configured to co-rotate synchronously. The first and second sets of imbalanced rotors are configured to create a controllable rotating force vector having a controllable magnitude and phase about the center point. A CFG system includes a controller and one or more CFG devices configured to receive control commands from the controller. A method of generating a force via a CFG device includes receiving a force command and generating a force in response to receiving the force command.

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: Systems, methods, and computer program products for directional force weighting of an active vibration control system involve arranging a plurality of force generators in an array, identifying individual component forces corresponding to force outputs of each of the plurality of force generators, determining a combination of the individual component forces that will produce a desired total force vector, and adjusting the outputs of each of the plurality of force generators such that the combination of the individual component forces are at least substantially similar to the desired force vector.