Cary, NC, United States
Cary, NC, United States

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Patent
LORD Corporation | Date: 2016-11-09

A snubbed isolator is provided having an increased capability for three-dimensional damping of vibrations for a component affixed or attached to a structure through the snubbed isolator, where the snubbed isolator is attached to the structure. The snubbed isolator includes a mounting plate for attaching to the structure, an elastomeric element, and a stem for mounting the component. The elastomeric element is disposed between the mounting plate and the stem.


A vehicle a nonrotating vehicle body, a rotating machine member, and including a vehicle vibration control system, the vehicle vibration control system including a vehicle vibration control system controller, a vehicle rotating machine member sensor for inputting vehicle rotating machine member data correlating to the relative rotation of the vehicle rotating machine member rotating relative to the nonrotating vehicle body into the vehicle vibration control system controller, at least a first nonrotating vehicle body vibration sensor, the at least first nonrotating vehicle body vibration sensor inputting at least first nonrotating vehicle body vibration sensor data correlating to vehicle vibrations into the vehicle vibration control system controller, at least a first nonrotating vehicle body circular force generator, the at least a first nonrotating vehicle body circular force generator fixedly coupled with the nonrotating vehicle body, the at least first nonrotating vehicle body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the vehicle rotating machine member sensor data correlating to the relative rotation of the vehicle rotating machine member rotating relative to the nonrotating vehicle body wherein the vehicle vibration sensed by the at least first nonrotating vehicle body vibration sensor is reduced.


Patent
LORD Corporation | Date: 2016-01-08

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.


Patent
LORD Corporation | Date: 2016-04-29

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.


An aircraft vibration control system includes an aircraft vehicle (520) having a gear box transmission (526), a nonrotating aerostructure body (524) and a rotating hub (522) driven by the transmission. A hub mounted vibration control system (HMVCS) (20) is mounted to the hub (522) with the HMVCS rotating with the hub about a rotating hub center Z-axis. The system includes a sensor (552) for outputting data correlating to rotation of the hub (522) relative to the nonrotating aerostructure body (524), and at least a first vibration sensor (554) outputting at least first vibration sensor data correlating to vibrations. The system includes first, second and third force generators (530) fixedly coupled with the aerostructure body (524) proximate the transmission (526) and oriented relative to the Z-axis, and wherein the HMVCS (20) and force generators are controlled to provide at least five degrees of freedom control and wherein the vibration sensed by the at least first nonrotating aerostructure body vibration sensor (554) is reduced.


Patent
LORD Corporation | Date: 2016-06-15

A hub-mounted active vibration control (HAVC) system is provided. The HAVC system comprises a mechanical unit (300) attached to a rotary hub (702) and configured to rotate therewith. The mechanical unit (300) includes at least one pair of imbalance masses co-rotating at substantially a same frequency. A de-icing distributor (208) is provided over at least a portion of the mechanical unit (300), wherein the de-icing distributor is configured to communicate instructions to one or more heating sources provided at one or more rotary blades.


Patent
Lord Corporation and Toyota Jidosha Kabushiki Kaisha | Date: 2015-04-01

A manufacturing method of a joint panel includes: joining an outer panel to an inner panel by applying an adhesive to an outer edge of the outer panel; performing electrodeposition coating on a surface of the outer panel of the joint panel in which the outer panel is joined to the inner panel; and burning, onto the outer panel, a coating film formed on the surface of the outer panel by the electrodeposition coating. The adhesive used herein is a room temperature curing adhesive that does not flow at the time of the burning.


A rotary wing aircraft including a vehicle vibration control system. 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 relative to the body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, the at least first nonrotating body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the rotary wing aircraft member sensor data correlating to the relative rotation of the rotating rotary wing hub rotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced.


Patent
LORD Corporation | Date: 2015-08-18

A method of bonding a vulcanized elastomer is provided comprising the steps of; providing an adhesive comprising a primary acrylate monomer, a reactive flexibilizing monomer, and further optionally comprising a toughener, an adhesion promoter and a free radical initiator, then depositing the adhesive on at least one surface of an elastomer or a second substrate, wherein the elastomer is a vulcanized elastomer, then bringing the elastomer substrate and second substrate together with the adhesive disposed therebetween, and allowing the adhesive to cure and bond the elastomer and second substrate together at a temperature of less than about 100 C. to produce a bonded structure.


Patent
LORD Corporation | Date: 2016-05-24

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.

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