Abstract: Helicopter rotating hub mounted vibration control system for a rotary wing hub having periodic vibrations while rotating at an operational rotation frequency. The vibration control system includes a housing attachable to the rotary wing hub and rotating with the hub at the operational frequency. The housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and an adjacent rotor housing cavity subsystem. The rotor housing cavity contains a first coaxial ring motor with a first rotor and imbalance mass and a second coaxial ring motor with a second rotor and imbalance mass.

Abstract: A fluid-elastomeric damper assembly operable for damping relative motion between a first structure and a second structure including a housing structure grounded to the first structure and a plurality of elastomer seals coupled to the housing structure, the housing structure and the plurality of elastomer seals defining a fluid-elastomeric chamber operable for containing a fluid. The fluid-elastomeric damper assembly also including one or more piston structures disposed within the housing structure and the fluid-elastomeric chamber, the one or more piston structures grounded to the first structure and driven by the second structure, and the one or more piston structures each including a first substantially fluid-filled chamber and a second substantially-fluid-filled chamber in communication via an orifice, the first substantially fluid-filled chamber and the second substantially fluid-filled chamber also in communication with the fluid-elastomeric chamber.

Abstract: Methods and systems for monitoring rotating shaft shafts and couplings in an aircraft propulsion system is described. The measurement system/method provides for accurate and precise monitoring of a rotating shaft flexible coupling in a fixed wing aircraft vehicle propulsion system. The measuring system/method provides for a high reliability short take off vertical landing fixed wing aircraft in which the vertical propulsion dynamically rotating drive shaft system and couplings are monitored in real time. The vehicular shaft coupling misalignment measuring system utilizes multiple positional sensors to provide highly reliable and precise determination of the dynamic characteristics of the rotating sensor target components of the propulsion system drive shaft. The relative position of the sensors is rigidly fixed externally from the rotating targets with a structural frame.

Abstract: The invention provides a rotating tub washer with an on-off binary damper system for damping a problematic movement between the washer frame and the rotating tub. The on-off binary damper system has a friction pad and a housing friction damper surface, with the friction pad in contact with said housing friction damper surface.

Abstract: Tiltrotor aircraft drivelink includes a nonelastomeric outer drivelink member with a first linkend and a distal second linkend. The tiltrotor aircraft drivelink first linkend has a first linkend cavity with a first linkend cavity inner circumferential bonding surface, and a first linkend nonelastomeric inner member contained in the first linkend cavity, the first linkend nonelastomeric inner member having a first linkend outer circumferential bonding surface, and a first linkend elastomeric intermediate having an outer circumferential elastomeric bonding surface and an inner circumferential elastomeric bonding surface, the outer circumferential elastomeric bonding surface bonded to the first linkend cavity inner circumferential bonding surface and the inner circumferential elastomeric bonding surface bonded to the first linkend outer circumferential bonding surface, the elastomeric intermediate containing N nonelastomeric outboard bonded shims and no more than N?1 nonelastomeric inboard bonded shims.

Abstract: A coating for elastomers is provided comprising, a rubber modified epoxy resin, an epoxy reactive diluent, and an epoxy curative. The epoxy resin is modified with a carboxyl terminated butadiene acrylonitrile rubber, and the coating is capable of co-extrusion with an elastomeric substrate, such as a weatherstrip.

Abstract: The invention provides an aircraft with an auxiliary power unit isolated from the aircraft. An auxiliary power unit suspension system includes at least one suspension linkage. The suspension linkage terminates with a first low stiffness elastomeric rod end. The low stiffness elastomeric rod end has a low spring rate with the aircraft auxiliary power unit suspension system providing the aircraft auxiliary power unit with a suspended auxiliary power unit natural frequency, the suspended auxiliary power unit natural frequency below the aircraft auxiliary power unit operation frequency.

Abstract: A method for protecting a substrate from lightning strikes is provided including providing a lightning strike protectant composition to the substrate. The lightning strike protectant composition comprises a reactive organic compound and a conductive filler that, during the cure of the organic compound, is capable of self-assembling into a heterogeneous structure comprised of a continuous, three-dimensional network of metal situated among (continuous or semi-continuous) polymer rich domains. The resulting composition has exceptionally high thermal and electrical conductivity.

Abstract: The invention provides a rotary wing aircraft helicopter vehicle rod end and method of making a rod end. The rotary wing aircraft rod end includes a nonelastomeric inner member having an outer bonding surface segment and an axial bore with a center bore axis, a nonelastomeric outer member having an inner bonding surface segment and an axial bore center bore axis, and molded in place alternating elastomeric shims and nonelastomeric shims connecting the nonelastomeric inner member to the nonelastomeric outer member. The rod end includes a first inner elastomeric shim bonded to the nonelastomeric inner member outer bonding surface segment and to a first inner nonelastomeric shim and a second outer elastomeric shim bonded to the nonelastomeric outer member inner bonding surface segment and to a second outer nonelastomeric shim. The nonelastomeric inner member has a molded misalignment rotary wing aircraft rod end orientation with the outer nonelastomeric outer member.

Abstract: A moving tracks dozer equalizer link elastomeric bearing assembly including a concentric outer member operable for securely engaging a equalizer link bore structure associated with a first end portion of an equalizer link structural member, wherein the concentric outer member is disposed substantially within the equalizer link bore structure. The dozer equalizer link elastomeric bearing assembly also including a concentric inner member operable for securely engaging a pin structure associated with a second moving track roller frame assembly structural member, wherein the concentric inner member is disposed substantially within the concentric outer member.

Abstract: The controllable suspension system includes a strut with a magnetorheological fluid damper. The magnetorheological fluid damper includes a longitudinal damper tubular housing having a longitudinally extending axis and an inner wall for containing magnetorheological fluid.

Abstract: An aqueous composition that includes (A) a butadiene polymer latex that is prepared by an emulsion polymerization in the presence of a styrene sulfonate stabilizer and (B) a phenolic resin. A preferred aqueous butadiene polymer latex is one that is prepared by emulsion polymerization of at least 60 weight percent dichlorobutadiene monomer (based on the amount of total monomers used to form the butadiene polymer), in the presence of a styrene sulfonate stabilizer.

Abstract: A vehicle suspension system for large vehicles includes at least one elastomeric bearing. The bearing includes at least one substantially cylindrical elastomeric portion, at least one substantially frustospherical elastomeric portion, and at least one non-extensible shim disposed between and bonded to the substantially cylindrical elastomeric portion and the substantially frustospherical elastomeric portion.

Abstract: An equipment engine mounting system/method for mounting an equipment engine to an equipment frame. The equipment engine mounting system includes a first engine mount disposed between the equipment engine and the equipment frame, including a first engine mount nonextensible inner member having an outer bonding surface. The first engine mount including a first engine mount nonextensible outer member, the first engine mount nonextensible outer member having an inner bonding surface. The first engine mount includes an intermediate elastomer between the first engine mount nonextensible inner member and the first engine mount nonextensible outer member, the first engine mount intermediate elastomer bonded to the first engine mount nonextensible inner member outer bonding surface and the first engine mount nonextensible outer member inner bonding surface.

Abstract: An aircraft vehicular front wheel landing gear assembly is provided that includes a nonelastomeric outer upper strut tubular member having an inner axial center bore with a tubular cylindrical frictional interface inner surface segment, and a nonelastomeric inner lower strut member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer strut member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer strut member. The assembly includes an elastomeric surface effect damper member encompassing the nonelastomeric inner strut member outer bonding surface segment. The elastomeric surface effect damper member has an inner bonding surface segment and an outer elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner strut member outer bonding surface segment.

Abstract: The computer programmable system and program product include first program instructions for actively driving a first imbalance mass concentration rotor and a second imbalance mass concentration rotor at a vibration canceling rotation frequency while controlling the rotational position of the first imbalance mass concentration and the second imbalance mass concentration to produce a rotating net force vector to inhibit periodic vibrations. The program product includes second program instructions to opposingly orient the first imbalance mass concentration relative to the second imbalance mass concentration during a starting stopping rotation speed less than the vibration canceling rotation frequency. The system includes a fault mode control protocol for controlling a rotation of the rotors during a sensed failure of the rotating assembly vibration control system.

Abstract: An active balancer for dynamically balancing a rotating machine is provided. The active balancer has a balancer body which rotates with the rotating machine and at least one controllable position counter weight having a real-time adjustable position relative to the balancer body and the rotating machine inorder to produce an actively adjustable controllable counter weight balance force for dynamically balancing the rotating machine. The active balancer includes a spring with the balancer body mounted to the rotating machine through the spring wherein the balancer body mass resonates on the spring with a torsional vibration canceling frequency which cancels a torsional vibration of the rotating machine.

Abstract: A method/system for controlling helicopter vibrations is provided that includes a vibration canceling force generator for actively generating a vibration canceling force. The system includes a resonant actuator having a natural resonant frequency and a resonant actuator electronic control system. The resonant actuator electronic control system provides an electrical drive current to the resonant actuator to drive the resonant actuator about the resonant frequency when commanded by a received command signal. The resonant actuator has a feedback output with the feedback output fed back into the resonant actuator electronic control system wherein the resonant actuator electronic control system adjusts the electrical drive current based on the resonant actuator feedback output to generate the vibration canceling force.

Abstract: A vehicle operator input device for controlling the vehicle with the operator input device including an operator interface lever moveable by a vehicle operator in first and second directions about an axis. The operator input device includes a sensor system with a sensor target. The sensor system senses the moveable operator interface lever and provides an operator interface lever position signal as a function of a position of the operator interface lever.

Abstract: The present invention broadly comprises an aircraft motion control auxiliary power unit suspension system device, the aircraft motion control auxiliary power unit suspension system device comprising a first motion control nonelastomeric member and a second motion control nonelastomeric member, a first motion control elastomer member disposed to operatively interconnect the first motion control nonelastomeric member and the second motion control nonelastomeric member. The first motion control elastomer member includes an exterior surface coating formed from an elastomeric polymer dissolved in an organic solvent and the elastomeric polymer dissolved in the solvent is applied to an exterior surface of the first motion control elastomer member, the solvent evaporates, and the elastomeric polymer crosslinks.