Abstract: Rotary dampers and systems for use and installation within a rotary winged aircraft, and related methods, are provided herein. In some aspects, a rotary damper includes a housing having a rotor assembly positioned inside the housing. The rotary damper may further include at least one resilient member disposed adjacent to an outer portion of the housing. The at least one resilient member is externally visible from outside of the rotary damper. In some aspects, the resilient member includes a torsional spring of the rotary damper. In certain aspects, the resilient member is disk shaped and slidable within a portion of the rotary damper. In some aspects, at least one primary liquid orifice is provided in a portion of the at least one rotor member. In some aspects, at least one pressure equalization port is disposed within a portion of the rotor assembly.

Abstract: Improved active vibration control (AVC) devices, systems, and related methods are provided herein. An AVC device includes a controller adapted to receive real-time aircraft information and adjust at least one control parameter as a function of the real-time aircraft information is provided. An AVC device is adapted to detect changes in real-time aircraft information, as the aircraft moves from a steady state to transient performance, low and high air speeds, or vice versa. An AVC system (e.g., AVCS) includes one or more sensors, one or more actuators, and a controller adapted to receive real-time aircraft information and adjust at least one control parameter. In some aspects, a method of controlling vibration within an aircraft includes receiving vibration information from at least one sensor, receiving real-time aircraft information from an avionics system, adjusting at least one control parameter used in a control algorithm, and generating a force command.

Abstract: Integrated stator disk devices, systems, and methods for torque generation are provided. The resistive torque-generating device can include an integrated stator disk system including at least one metallic stator disk having a planar disk body, and at least one rotor disposed adjacent to the at least one metallic stator disk such that there are at least two shear areas formed by the at least one metallic stator disk and the at least one rotor; and magneto-rheological material disposed between portions of the at least one metallic stator disk and the at least one rotor. In some embodiments, the rotor(s) is/are a bent rotor(s), thereby providing for increased torque generation while fitting within tight space constraints.

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

Abstract: A method of bonding a vulcanized elastomer is provided comprising the steps of; providing an adhesive comprising a primary acrylate monomer, a reactive flexibilizing monomer, and further optionally comprising a toughener, an adhesion promoter and a free radical initiator, then depositing the adhesive on at least one surface of an elastomer or a second substrate, wherein the elastomer is a vulcanized elastomer, then bringing the elastomer substrate and second substrate together with the adhesive disposed therebetween, and allowing the adhesive to cure and bond the elastomer and second substrate together at a temperature of less than about 100° C. to produce a bonded structure.

Abstract: A non-contacting torquemeter capable of measuring torque in a rotating shaft with improved accuracy in the presence of relative motion between a rotating shaft and a transducer assembly is provided. The non-contacting torquemeter has improved robustness and reliability, and is able to self-calibrate. The non-contacting torquemeter is able to provide accurate torque measurements using a single transducer assembly positioned at a single azimuthal position on a rotating shaft.

Abstract: The present subject matter relates to devices, systems, and methods for indicating degradation in a component having None 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: An aircraft mounting system is provided having a yoke that is interlocked with engine mounts securable to the engine and the yoke is interchangeable with other yokes on other engines. An aft engine mount is also provided.

Abstract: Improved active vibration control (AVC) devices (20), systems, and related methods are provided herein. An AVC device (20) includes a controller (24) adapted to receive real-time aircraft information and adjust at least one control parameter as a function of the real-time aircraft information is provided. An AVC device is adapted to detect changes in real-time aircraft information, as the aircraft moves from a steady state to transient performance, low and high air speeds, or vice versa. An AVC system (e.g., AVCS) includes one or more sensors (22), one or more actuators (26), and a controller (24) adapted to receive real-time aircraft information and adjust at least one control parameter. In some aspects, a method of controlling vibration within an aircraft includes receiving vibration information from at least one sensor (22), receiving real-time aircraft information from an avionics system (40), adjusting at least one control parameter used in a control algorithm, and generating a force command.

Abstract: Systems, methods, and computer readable media for providing lossless transmission of sensor data in a wireless network are provided. In some aspects, a method for transmitting data in a wireless sensor network includes collecting data at a sensor node, attaching a timestamp to the data, buffering the data and the timestamp to a memory device and retransmitting the collected data where the sensor node fails to receive an acknowledgement message from the base station after the data transmission. In some aspects, a system can include a plurality of wireless sensor nodes having synchronized clocks and a base station. Collected sensor data can be associated with a timestamp via the clock prior to transmitting the data to the base station. The data can be buffered at a memory device and retransmitted therefrom to provide lossless data transmission.

Abstract: In an embodiment the system includes a method of mounting an engine in a rotary wing aircraft. The method includes providing a rotary wing aircraft having an aircraft body supported in flight through an exterior air space by a rotary wing system rotating with an operational rotating frequency (P) with a plurality of (N) rotary wings, the rotary wing aircraft body having a persistent in flight operational rotating frequency vibration. The method includes providing a first engine, the first engine for providing power to rotate the rotary wing system at the rotary wing system operational rotating frequency (P).

Abstract: Active vibration control systems (100) and methods are provided herein. Systems (100) are expandable and include a plurality of vibration control devices (110) and at least a first controller (102) digitally linked with a second controller (104) via an interface (108). The first and the second controllers exchange information for generation of a force control command (FCC) either the first or second controller. The FCC is then executed at a first vibration control device (110) of the plurality of vibration control devices (FG) for providing active vibration control within a vehicle. A method of providing vibration control in a vehicle includes providing a plurality of active vibration control devices (100) and providing at least a first controller (102) digitally linked with a second controller (104). The method further includes generating a FCC using information exchanged between the first and the second controllers.

Abstract: A fluid conduit connection system includes a bearing assembly comprising a bearing pipe comprising a fluid flow path, and a bearing element stack located exterior to the bearing pipe and disposed substantially annularly about the bearing pipe, wherein the bearing element stack is configured to receive a compressive force from the bearing pipe and wherein the bearing element stack is configured to allow rotation of the bearing pipe about a center of rotation of the bearing assembly.

Abstract: In an embodiment the invention includes an aircraft engine mounting system (20) for mounting an aircraft engine to an aircraft. The aircraft engine mounting system preferably includes an airframe structure member having a first engine end (28) and a distal second engine end (30), with an aircraft attachment between the first engine end and the distal second engine end, the aircraft attachment for interfacing the airframe structure member with the aircraft, the airframe structure member having an airframe structure member length (YL) from the first engine end to the distal second engine end. The aircraft engine mounting system preferably includes a first engine attachment structure member (36), the airframe structure member first engine end (28) contained by the first engine attachment structure member, with the first engine attachment structure member having an outer engine mount member (38) grounded to the aircraft engine.

Abstract: A wear-indicating bearing and method of detecting wear in a bearing are disclosed. The bearing includes a bearing stack having a first end and a second end with a longitudinal axis defined between the first and second ends. The bearing stack includes a plurality of elastomeric layers sandwiched between non-elastomeric shim layers, where each layer is concentric about the longitudinal axis. At least one elastomeric layer is a marker layer configured to indicate wear of the bearing. The marker layer is made up of a first elastomeric composition and a second elastomeric composition, wherein the first and second elastomeric compositions have optically different characteristics. Upon fatigue of the bearing, the first elastomeric composition is detectable through a fracture extending from an exterior surface of the bearing stack.

Abstract: A rotary wing system with a rotating blade and a fluid damper with a damper fluid in a first variable volume chamber and a second variable volume chamber, with a fluid damping flow valve controlled conduit and a fluid flow pressure sensing control valve assembly between the first variable volume chamber and the second variable volume chamber. The fluid flow pressure sensing control valve assembly has a fluid flow pressure sensing control valve assembly control valve for obstructing a damper fluid flow through the fluid damping flow valve controlled conduit. A working of the first variable volume chamber and the second variable volume chamber by rotary wing motions actuates the opening of the fluid flow pressure sensing control valve assembly control valve that obstructs the damper fluid flow through the fluid damping flow valve controlled conduit.

Abstract: An electromagnetic inertial actuator includes a support base and a parallel arrangement of a first flexure part, a voice coil motor part, and a second flexure part. The parallel arrangement is cantilevered from the support base.

Abstract: An assembly for managing heat and noise generated by an engine comprises a dash panel, an acoustic absorbing layer, a scrim, and a heat reflective coating. The acoustic absorbing layer comprises a plurality of fibers secure in a resin, where the acoustic absorbing layer is positioned proximate to the dash panel. The scrim is positioned proximate to the acoustic absorbing layer. The heat reflective coating comprises a polymer material and heat reflecting additives dispersed in the polymer material. The heat reflective coating is applied to the scrim as a solution of the polymer material and heat reflecting additives.

Abstract: A laminated bearing includes a plurality of elastomeric layers (113) and at least one fabric layer (112) arranged between at least two of the elastomeric layers. The at least one fabric layer and the elastomeric layers are bonded together to form at least one bonded laminated portion (110) of the laminated bearing (100), and a plurality of bonded laminated portions comprise the laminated bearing.

Abstract: A method of determining a parameter includes providing a sensor that provides a sensor analog voltage. A peak detecting circuit for detecting a peak voltage in the sensor analog voltage is also provided. The sensor analog voltage is provided to the peak detecting circuit, and the peak voltage is detected. A microprocessor is provided in sleep mode and is awakened once the circuit detects the peak voltage. The microprocessor samples and records the peak voltage and the microprocessor goes back to sleep.