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: 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 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 rotary wing aircraft including a vehicle vibration control system.

Abstract: A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotating hub mounted vibration control system, the rotating hub mounted vibration control system mounted to the rotating rotary wing hub with the rotating hub mounted vibration control system rotating with the rotating rotary wing hub.

Abstract: A digital processing link for a vibration control system collects sensor signals at a transfer station and combines the sensor signals into a collective signal that is transmitted under a digital communications protocol to a base station. The sensor signals are separated at the base station and individually processed to produce one or more output control signals to actuators for counteracting the measured vibration.

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/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 rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotating hub mounted vibration control system, the rotating hub mounted vibration control system mounted to the rotating rotary wing hub with the rotating hub mounted vibration control system rotating with the rotating rotary wing hub.

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: 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: 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. An elastomer encompasses 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 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: Dendritic polymers with enhanced amplification and interior functionality are disclosed. These dendritic polymers are made by use of fast, reactive ring-opening chemistry (or other fast reactions) combined with the use of branch cell reagents in a controlled way to rapidly and precisely build dendritic structures, generation by generation, with cleaner chemistry, often single products, lower excesses of reagents, lower levels of dilution, higher capacity method, more easily scaled to commercial dimensions, new ranges of materials, and lower cost. The dendritic compositions prepared have novel internal functionality, greater stability (e.g., thermal stability and less or no reverse Michael's reaction), and reach encapsulation surface densities at lower generations. Unexpectedly, these reactions of polyfunctional branch cell reagents with polyfunctional cores do not create cross-linked materials.

Abstract: Poly(ester-acrylate) and poly(ester/epoxide) dendrimers. These materials can be synthesized by utilizing the so-called “sterically induced stoichiometric” principles. The preparation of the dendrimers is carried out by reacting precursor amino/polyamino-functional core materials with various branch cell reagents. The branch cell reagents are dimensionally large, relative to the amino/polyamino-initiator core and when reacted, produce generation=1 dendrimers directly in one step. There is also a method by which the dendrimers can be stabilized and that method is the reaction of the dendrimers with surface reactive molecules to pacify the reactive groups on the dendrimers.

Abstract: Methods of providing hyperbranched polymers by polymerization of appropriate AB2 monomers derived from the reaction of tris-(2-aminoethyl) amine and various other materials, namely, succinic anhydride, methyl acrylate, and dimethyl ita-conate.

Abstract: An inbred maize line, designated PH6WG, the plants and seeds of inbred maize line PH6WG, methods for producing a maize plant, either inbred or hybrid, produced by crossing the inbred maize line PH6WG with itself or with another maize plant, and hybrid maize seeds and plants produced by crossing the inbred line PH6WG with another maize line or plant and to methods for producing a maize plant containing in its genetic material one or more transgenes and to the transgenic maize plants produced by that method. This invention also relates to inbred maize lines derived from inbred maize line PH6WG, to methods for producing other inbred maize lines derived from inbred maize line PH6WG and to the inbred maize lines derived by the use of those methods.

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: Heterocycle terminated dendritic polymers. More specifically, the production of 2-pyrrolidone, 2-piperidone, 2-aza-cycloheptanone or 2-azetidinone-terminated dendritic polymers obtained by reacting precursor primary amine, (e.g., —NH2)-terminated dendritic polymers with certain functionalized methacrylate reagents to produce new and novel dendritic polymers terminated with ester substituted 2-pyrrolidone, 2-piperidone, 2 aza-cycloheptanone or 2-azetidinone groups.