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

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Patent
LORD Corporation | Date: 2016-11-03

An adhesive composition having two distinct reaction mechanisms, a first being the reaction between a tri-functional isocyanate and an active hydrogen compound and a second begin the free radical initiation of an acrylic monomer. This adhesive develops tack strength through the first reaction allowing two substrates to remain in position relative to one another while the free radical cure of the acrylic monomer takes place to fully bond the substrates together, for example when adhering a rubber liner to the inside of a metallic tank.


An aircraft mounting system is provided having a yoke that is interlocked with engine mounts securable to the engine and the yoke is interchangeable with other yokes on other engines. An aft engine mount is also provided.


Patent
LORD Corporation | Date: 2017-02-22

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.


Patent
LORD Corporation | Date: 2017-04-19

Systems and methods are disclosed herein that include providing an active torsion damper control system that includes a rotatable component (206) and a rotatable measurement interface (302) disposed on the rotatable component, the rotatable measurement interface having at least one torsional strain gauge configured to measure a strain of the rotatable component, a torque management (306) computer configured to determine a resonant frequency of the rotatable component and a corrective torque needed to be applied to the rotatable component to excite the resonant frequency as a function of the measured strain, and a correction motor (308) configured to impart the corrective torque on the rotatable component.


Patent
LORD Corporation | Date: 2017-02-22

Structural health monitoring and protection systems and methods are provided. System and methods utilize structural information and/or enhanced built in testing capabilities for detecting failure modes that may cause damage to a structure. Systems and methods herein may protect a structure by mitigating one or more incorrect forces. The structure may be an aircraft, a rotary wing aircraft, or any other physical structure subject to vibrations and receptive to canceling of those vibrations.


Patent
LORD Corporation | Date: 2017-02-23

Motion control bearings and methods making such with the capability to monitor properties therein is provided. Devices and methods for creating and using motion control bearings for rotary wing aircraft in particular are disclosed using wireless communication and monitoring of multiple load, motion and health related information items related to the bearing and blade at the wing hub. Static and dynamic blade orientation provides additional information on flight regime, thrust vectors, and gross vehicle weight. Power is provided using kinetic energy power harvesting.


Patent
LORD Corporation | Date: 2017-06-28

A helicopter engine mounting system is provided for mounting an engine (50) to an aircraft body (54). The aircraft body (54) is supported in flight by a rotary wing system (56) rotating with an operational rotating frequency (P) with a plurality of (N) rotating blades (58), said aircraft body having a persistent in flight operational rotating frequency vibration from said rotating blades. The engine mounting system includes a top fluid chamber fluid engine mount (60t) and a bottom fluid chamber fluid engine mount (60b). The top fluid chamber fluid engine mount (60t) has a bottom end (62) for grounding to said aircraft body (54), and said bottom fluid chamber fluid engine mount (60b) has a bottom end (62) for grounding to said aircraft body. The top fluid chamber fluid engine mount (60t) has a top fluid chamber (64t) distal from said top fluid chamber fluid engine mount bottom end (62). The bottom fluid chamber fluid engine mount (60b) has a bottom fluid chamber (64b) proximate said bottom fluid chamber fluid engine mount bottom end (62). The system also includes an intermediate cradle (65) with a lateral link (4), said lateral link having a first end (68a) for grounding to said aircraft body (54) and a second distal end (68c). The second distal end (68c) is distal from said first end (68a) and is linked to said intermediate cradle (65). The top fluid chamber fluid engine mount bottom end (62) and said bottom fluid chamber fluid engine mount bottom end (62) are each grounded to said aircraft body (54), with said intermediate cradle (65) disposed between said top fluid chamber fluid engine mount (60t) and said bottom fluid chamber fluid engine mount (60b) and said engine (50). A fluid conduit (70) connects said top fluid chamber fluid engine mount top fluid chamber (64t) with said bottom fluid chamber fluid engine mount bottom fluid chamber (64b) wherein a transfer of said persistent in flight operational rotating frequency vibration from said aircraft body (54) to said engine (50) is inhibited.


Patent
LORD Corporation and GMC Inc. | Date: 2017-06-28

Systems and methods are disclosed herein that include providing a flexible joint for use in a steel catenary riser that includes a compression bearing (106) having a transition shim (120) and a plurality of alternating flexible elements (116) and shims (118) collectively stacked and bonded to a lower portion of the transition shim (120). The flexible joint also includes an inner bonding material (126) having a profile that is complementary to a profile of an extension tube (104), the inner bonding material (126) being disposed between the extension tube (104) and compression bearing (106) and configured to serve as a bonding mechanism between extension tube and compression bearing.


Dampers (100), assemblies, and methods are provided for lead-lag damping for an articulated rotor and includes a lead-lag damper (100) having a first end connector (102) configured to be coupled to a rotor hub (H), a second end connector (104) configured to be coupled to one of a plurality of rotor blades (B), and a body portion (110) coupled to the first end connector (102) and to the second end connector (104). The body portion (110) includes one or more elastomeric material layers (120) arranged in a lengthwise direction between the first end connector (102) and the second end connector (104), with each of the elastomeric material layers (120) having a substantially chevron-shaped profile in a crosswise direction.


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.

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