Abstract: The present subject matter relates to systems and methods for active vibration control system speed monitoring and control in which a speed protection monitor configured to receive index pulses as inputs to monitor the speed of one or more force generators. A rotary actuator control system can be connected in communication with the speed protection monitor and the one or more force generators, wherein the rotary actuator control system is configured to shut down or adjust the speed of the one or more force generators if the one or more force generators are determined to be operating at undesired speeds.

Abstract: Torque measurement devices, systems, and methods are provided. Exemplary torque measurement devices, systems, and methods include providing rotating electronics and non-rotating electronics configured for remote power transmission and remote interrogation via near field and switched reactance communications. The rotating electronics and the non-rotating electronics can communicate analog information without batteries or a physical connection therebetween.

Abstract: Devices, systems, and related methods for balancing two or more pieces of independently rotating (e.g., not synchrophased) machinery are provided. In some aspects, the devices, systems, and methods can provide improved balancing techniques and can include providing a controller configured to simultaneously measure/receive vibration data and control balancers, one balancer at a time. In some aspects, the controller can calculate a beating cycle or a beating period using vibration data received from multiple rotating machines. In some aspects, a balance correction command can be derived in part from either one of: (a) an interpolation of an average vibration of the first rotating machine from a complex vibration of the multiple rotating machines or (b) an average vibration derived from one or more rules applied based upon the duration of the beating period or the beating cycle.

Abstract: A gimbal (200) has an intermediate plate (202), a first plate (204) offset from the intermediate plate (202) in a first direction, a first bearing (208) having a first rotational axis connected between the intermediate plate (202) and the first plate (204), a second plate (206) offset from the intermediate plate (202) in a second direction opposite the first direction, and a second bearing (210) having a second rotational axis connected between the intermediate plate (202) and the second plate (206).

Abstract: Aft-mounting systems, devices, and methods for turboprop and turboshaft engines include two or more coupling elements 201, 211, 221 that are configured to couple an aft portion of an engine of an aircraft to a support structure of the aircraft. The two or more coupling elements are together configured to react forces generated in a vertical direction and in a lateral direction transverse to the engine but allow substantially unrestricted rotation of the engine with respect to the support structure about an axis of rotation of the engine.

Abstract: Systems and methods are disclosed that include providing an isolating mule shoe having an integrated axial isolator coupled to a landing sleeve of a drill string at an upper end of the axial isolator. The axial isolator includes an elastomeric component that is coupled between a first component and a second component. The first component and the second component are configured to displace axially with respect to one another as a result of a force imparted upon the landing sleeve to provide vibration control.

Abstract: The invention includes an aircraft engine mounting system for mounting an aircraft engine to an aircraft. The mounting system includes a yoke member having a first end and a second end, with an aircraft attachment between the first end and the second end, the aircraft attachment for interfacing the yoke member with the aircraft, the yoke member having a yoke member length (YL) from the first end to the second end. The mounting system preferably includes a first engine mount, the yoke member first end contained by the first engine mount, with the first engine mount having first engine mount housing grounded to the aircraft engine. The mounting system preferably includes a second engine mount, the yoke member second end contained by the second engine mount, with the second engine mount having a second engine mount housing grounded to the aircraft engine.

Abstract: An engine attachment system (EAS) includes a forward collar (202), an aft collar (204), at least one truss subassembly (216) disposed between the forward collar and the aft collar for supporting an engine, and at least one vibration isolator (206,208) integrated with each of the forward and aft collars for isolating engine vibration and reducing noise. A method of attaching a turboprop engine includes providing an EAS and hoisting a turboprop engine at least partially within the at least one truss subassembly (216).

Abstract: An adhesive for bonding comprising a blocked isocyanate and organic carbonate, and optionally a phenoxy resin, catalyst, metal acetylacetonate, and a process for using such an adhesive to bond elastomers, such as liquid silicone rubber to substrates, such as polycarbonate in an injection molding process.

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: Hub-mounted active vibration control (HAVC) devices, systems, and related methods are provided. An HAVC device (100) includes a housing (206) having a tolerance ring (600) attached to a rotary hub (702). The tolerance ring can accommodate dissimilar coefficients of thermal expansion between dissimilar metals. The HAVC device can also include a plurality of coaxial ring motors (308A, 308B, 310A, 310B) configured to rotate a plurality of imbalance masses for controlling vibration. An HAVC system can further include a de-icing distributor (208) for communicating instructions to one or more heating sources (HS) provided at one or more rotary blades (802) of a vehicle or aircraft. A method of controlling vibratory loads occurring at a moving platform can include providing a moving platform, mounting a vibration control device to a portion of the moving platform, and rotating at least one pair of imbalance masses such that the combined forces of the masses substantially cancel unwanted vibration of the platform.

Abstract: Films comprising a resin matrix, an entanglement polymer, and a latent curative, wherein the resin has a functionality of at least 2.0 and a viscosity of at least 0.1 Pascal-seconds, and the film is dimensionally stable at 25° C. The films are particularly useful for the bonding of elastomers to rigid substrates, such as rubber to metal, and contain no volatile organic compounds (VOCs), and are shelf stable for extended periods of time.

Abstract: An aqueous composition is provided comprising a resin, a curative, a filler, a surfactant, and water; wherein the resin comprises an average molecular weight of less than about 800 Daltons and comprises at least 50 weight percent of at least one of: (a) an unmodified epoxy or phenoxy resin, or (b) a surfactant-modified epoxy or phenoxy resin. This composition, applied to a substrate and dried, can then be cured so as to thermoset the resin and self-assemble to form continuous pathways of filler within the resin matrix.

Abstract: This invention relates to an undersea riser bearing designed to operate at higher temperatures over an extended time frame while maintaining performance advantages of high capacity laminate (HCL) elastomeric composite bearings.

Abstract: The present subject matter relates to improved damping fluid mount devices, systems, and methods in which a damping fluid mount (100) includes an inner member (110), an elastomer section (130) that is affixed to an outer surface of the inner member (110), and a cup (200) containing viscous fluid (300). The elastomer section (130) has an outer diameter that is variable along an elastomer contour, and a crimped portion of the cup is radially crimped into the elastomer section (130) such that the crimped portion precompresses the elastomer section (130) and substantially mimics the elastomer contour.

Abstract: An acrylic adhesive composition is provided comprising a free-radical polymerizable monomer, an initiation system and a co-accelerator that enhances the reactivity of the initiation system by increasing the reaction rate between the oxidizing agent and the reducing agent. The free radical-polymerizable monomer preferably comprises methyl methacrylate (MMA), the initiator system preferably comprises N,N-diisopropanol-p-toluidine (DIIPT) and benzoyl peroxide (BPO), and the co-accelerator preferably comprises 1,4-diazabicyclo[2.2.2]octane (or triethylene diamine (TDA)).

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.