Abstract: A system that includes a magnetically actuated motion control device comprising a housing defining a cavity and including a slot therethrough. A movable member is located within the cavity and is movable relative to the housing. A magnetic field generator located on either the housing or the movable member causes the housing to press against the movable member to develop a friction force.

Abstract: A finger for a crop gathering auger for an agricultural combine, including an elastomeric tethering outrigger which arches a failure region of the finger and will retain a free end of the finger in connection with a mounting end thereof when the failure region is broken.

Abstract: Please replace the Abstract with the following amended Abstract: A magneto-rheological fluid valve includes a magnetic field generator having at least one electromagnetic coil and at least one magnetic pole having a pole length Lm. The magneto-rheological fluid valve further includes at least one flow channel adjacent to the magnetic field generator. The at least one flow channel has a gap width g, wherein the ratio Lm/g is greater than or equal to 15.

Abstract: An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. The assembly includes an elastomer encompassing the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment.

Abstract: A balance assembly for a rotating assembly comprising: a first movable rotor and a second movable rotor which are selectively movable about the rotating assembly; and a controller with a microprocessor operating with stored control programs for controlling movement of the first movable rotor and second movable rotor and adapted to calculate a value and to periodically modify the value and to cause the first movable rotor and the second movable rotor to move in accordance with the calculated value and the modified value, wherein the values are adjusted during a plurality of control iterations to reduce vibrational signals from an at least one vibration sensor.

Abstract: An aircraft with at least one rotating machine creating troublesome vibrations, the aircraft comprised of an aerostructure, the aircraft including: a power source, the power source outputting a plurality of electromagnetic force generator power outputs, the aerostructure including a plurality of distributed active vibration control system sites, at least a first distributed active vibration electromagnetic force generator, the first distributed active vibration electromagnetic force generator including a first distributed electronic control system and a first electromagnetically driven mass, the first distributed active vibration electromagnetic force generator fixed to the aerostructure at a first distributed active vibration control system site, at least a second distributed active vibration electromagnetic force generator, the second distributed active vibration electromagnetic force generator including a second distributed electronic control system and a second electromagnetically driven mass, the seco

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: An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. The assembly includes an elastomer encompassing the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment.

Abstract: The invention provides a furniture chair seatback tilt limiter system for adjustably limiting the seatback recline of a chair. The seatback tilt limiter system includes a first gear toothed rotator with a full forward seatback upright endstop and a full recline seatback endstop. The seatback tilt limiter system includes a second gear toothed rotator having an adjustment endstop. The first rotator is free to rotate between the full forward seatback upright endstop and the full recline seatback endstop when the rotator gear teeth are disengaged and the second rotator adjustment endstop limits the rotation of the first rotator to an adjustable reclined seatback tilt limit when the gear teeth are engaged.

Abstract: A 100% non-volatile, one-part liquid underfill encapsulant is disclosed for application to the active side of a large wafer or integrated circuit chip. Upon coating, the encapsulant is converted to a liquefiable, tack-free solid by exposure to radiation, particularly in the UV, visible and infrared spectrum. The underfill-coated wafer exhibits outstanding shelf aging of months without advancement of cure. The large wafer can be singulated into smaller wafer sections and stored for months after which during solder reflow assembly, the wafer connects are fixed and the underfill liquefies, flows out to a fillet and transitions to a thermoset state on heat activated crosslinking.

Abstract: A balanced rotating assembly with a spindle automatically provides balancer limits, which achieves a balancing state while substantially minimizing short term vibration increases and which provides for multi-plane balancer dithering.

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: 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: 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 method and kit for repairing vehicle door skins by reorienting vehicle hem flanges from a closed orientation to an open orientation to allow removal of a damaged door skin from a door frame and replacing with a new door skin with an open orientation hem flange that is reoriented to a closed orientation to integrate the door skin and door frame with an adhesive. The repair kit includes a first tool for lifting and opening the damaged door skin hem flange to allow removal of the damaged door skin and reuse of the door frame. The tool kit includes a second repair tool for reorientation and closing the new door skin replacement door skin hem flange on the reused door frame with an adhesive to provide a repaired vehicle door with the replacement skin and reused door frame integral as a vehicle door.

Abstract: An aqueous dispersion coating for rubber and polymer substrates comprises a blend of a polysiloxane and a curable polyurethane and various additives such as a urethane crosslinking agent, a heat resistant filler, and the like. The aqueous dispersion coating reduces the noise upon contact or movement of the coated substrate with an article and maintains the initial static coefficient of friction therewith over a period of time. A desired end use is as a coating on vehicle weatherstrips such as for doors, trunks, and other enclosing articles.

Abstract: A coolant-resistant and thermally stable primer composition comprising an organic-functional silane, preferably the reaction product of at least one amino-functional silane and at least one isocyanato-functional silane, is provided. The primer composition may additionally comprise a phenoxy resin, a phenolic resin and talc. A method for bonding an elastomer to a metal also is provided.

Abstract: A vibration isolation member comprising an inner member comprising an outer periphery having a first dimension; an outer member comprising a base and a shroud that extends away from the base, the shroud adapted to overlay the inner member, said shroud defining an inner periphery having a second dimension, the second dimension being less than the first dimension; and a resilient member constrained between the shroud and the inner member, whereby the vibration isolation member provides iso-elastic dynamic stiffness and an interference between the inner and outer members in the event of a failure of the resilient member.

Abstract: A multi-rate torsional coupling (20) features parallel first and second drive connections (82 and 84) between input (24) and output (22) members. The first drive connection (82) extends through a first resilient coupling (38), and the second drive connection (84) extends through a second resilient coupling (40). An angular play coupling (70) engages the second drive connection (84) at a particular torque load for transmitting additional torque through the torsional coupling (20) at a higher spring rate.

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.