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: 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: One embodiment of an electronic system includes a network having a first sensing device with a first address and a second sensing device with a second address. The first sensing device includes first sensors, a first processor, a first memory, and a first communications device. The first sensors include a first dry bulb temperature sensor, a first relative humidity sensor, and a first radiant energy sensor. The second sensing device includes a second sensor, a second processor, a second memory, and a second communications device. The second processor includes a program to use the second communications device to communicate the second address and data derived from the second sensor to the first communications device.

Abstract: A magneto-rheological fluid damper includes a damper body having a reservoir for a magneto-rheological fluid, a piston rod, a piston rod guide disposed within the damper body, where the piston rod guide has a passage therein for receiving the piston rod. The magneto-rheological fluid damper further includes at least a first piston rod seal and at least a second piston rod seal arranged to seal between the piston rod guide and the piston rod. The magneto-rheological fluid damper further includes a fluid chamber defined between the piston rod guide and the piston rod, the fluid chamber being in communication with the reservoir. The magneto-rheological fluid damper further includes a piston rod guide filter arranged in a communication path between the fluid chamber and the reservoir to filter particulates out of the magneto-rheological fluid entering the fluid chamber. The magneto-rheological fluid damper further includes an accumulator arranged between the piston rod guide and the damper body.

Abstract: A device for harvesting an external source of energy includes an electricity generating device and a flexure. The piezoelectric flexure has a first stable bowl-shaped position and a second stable bowl-shaped position. The electricity generating device generates electricity based on movement of the flexure. The flexure remains in the first stable bowl-shaped position until a force provided by the external source of energy causes the flexure to move from the first stable bowl-shaped position toward the second stable bowl-shaped position.

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 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 driven to rotate about a rotating hub center Z axis by a gear box transmission. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating about the rotating hub center Z axis relative to the nonrotating body, a first nonrotating body vibration sensor outputting first nonrotating body vibration sensor data correlating to vibrations.

Abstract: A support strut includes a strut isolator with a first strut end member and a second strut end member, the second strut end distal from the first strut end. The first strut end member includes an outer rigid housing with an inner cavity. The second strut end member includes an inner rigid member extending into the outer rigid housing inner cavity and includes an inertial track extending in a direction from the first strut end towards the second strut end. The inertial track has a first entrance end proximate the first strut end and a second entrance end proximate the second strut end. The isolator includes a first outer tubular elastomer disposed between the outer rigid housing and the inner rigid member. The isolator includes a second inner end tubular elastomer disposed between the outer rigid housing and the inner rigid member proximate the second strut end.

Abstract: Center-bonded mounts for resiliently connecting a supported structure to a support structure are assembled from members that are adapted to disproportionately affect the axial and radial stiffness of the mount. Each of the members includes a shoulder portion for engaging an opposite side surface of the support structure and a neck portion that extends within a socket formed through the support structure. The shoulder portion of one member disproportionately affects the downward axial stiffness of the mount, and the neck portion of the other member disproportionately affects the radial stiffness of the mount. A mount stiffness characteristic of the individual members can be varied, and the varied members can be interchangeably combined to provide both a greater selection and a greater range of axial and radial stiffness characteristics for a given part count.

Abstract: A helicopter rotor damper system including a torsional damper with a damper centering bearing providing a damper center of rotation axis, a first elastomeric torsional damper with a first elastomeric torsional damper torsional elastomer bonded between a first elastomeric torsional damper first torsional damper nonelastomeric bonding surface and a first elastomeric torsional damper second torsional damper nonelastomeric bonding surface, and a second elastomeric torsional damper with a second elastomeric torsional damper torsional elastomer bonded between a second elastomeric torsional damper first torsional damper nonelastomeric bonding surface and a second elastomeric torsional damper second torsional damper nonelastomeric bonding surface.

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 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: Helicopter reduced vibration axial support struts and aircraft suspension system are disclosed with at least one vibration controlling fluid containing strut. The powered struts include an outer rigid housing containing an inner rigid member and first and second variable volume fluid chambers. Fluid pressure differentials are created between the first and second variable volume fluid chambers to control motion between the strut ends. The powered fluid containing struts, support isolators, suspension systems, and methods of operation provide reduced helicopter aircraft vibrations.

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 an aerostructure and at least one rotating machine creating troublesome vibrations, with the aircraft including a power source outputting electromagnetic force generator power outputs, a first and second distributed active vibration electromagnetic force generator, the first and second force generator including a distributed electronic control system and an electromagnetically driven mass, the force generators fixed to the aerostructure at first and second distributed active vibration control system sites, and electrical power distribution lines connecting the force generators with the power source with the power outputs outputted to the electromagnetic force generators, and a distributed force generator data communications network linking together the first and second distributed electronic control systems wherein the distributed electronic control systems communicate force generator vibration control data through the distributed force generator data communications network independently of t

Abstract: Low silica forms of faujasite-type zeolites are prepared from more siliceous forms of the same zeolite species by contacting the starting zeolite with a highly caustic concentrated sodium aluminate solution at elevated temperatures. In view of the fact that the process does not favor the formation of undesirable impurity phases such as zeolite A and thus does not require the presence of zeolite A nucleation inhibitors, the process is particularly advantageous in the production of forms of zeolite X having Si/Al.sub.2 molar ratios below 2.5.

Abstract: Difluoromethane (R32) is of current interest as a partial replacement for chlorodifluoromethane (R22) refrigerant heretofore widely used in vapor compression refrigeration systems. R32 has, however, proved to be more reactive than is desirable with the zeolite A adsorbent-desiccant compositions used in such systems to prevent corrosion and freeze-up problems. The sodium cation form of a zeolite having the crystal structure of zeolite B is found to be an effective adsorbent for that purpose and to be significantly less reactive with the R32.

Abstract: In the hydrothermal synthesis of crystalline microporous molecular sieves from a reaction system containing an organic templating agent, it is found that removal of at least some of the organic reagent prior to the time the formation of crystalline product is complete results in an increased yield of the product. The removal of the organic reagent disrupts the equilibrium that is normally established in the reaction system at the selected crystallization temperature between product formation and product dissolution and shifts the reaction toward the formation of additional product before a new equilibrium can form.

Abstract: In processes for removing mercury vapor from natural gas streams by selective adsorption in fixed adsorbent beds, water is invariably adsorbed along with the mercury impurity. During the periodic purge regeneration of the adsorbent bed it is desirable to recover as much as possible of the desorbed mercury in the spent regeneration gas in liquid form to avoid reintroducing the mercury into the environment. Cooling this spent regeneration gas under the high pressure conditions involved to condense the mercury can result in the highly undesirable formation of hydrocarbon hydrates if temperatures low enough to condense an adequate amount of mercury are employed. In the process of the present invention, the spent regeneration gas stream, from which some mercury has been removed by cooling, is further treated in a desiccant bed so that it is possible to cool it further in order to condense and remove additional mercury without encountering hydrocarbon hydrate formation.