Lord Corporation

Lawrie Technology Incorporated

Peter J Jones

Eric Seitter

Douglas Edward Ivers

Donald D Russell

Kevin C Cooney

Mark R Jolly

Douglas A Swanson

Gerald P Whiteford

Dennis P McGuire

Donald L Margolis

Douglas A Hodgson

Charles M Nobles

Zachary Fuhrer

Brian McGill

Marshall W Downing

Duncan J Lawrie

Peter L Valentine

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

Lead-lag dampers and assemblies for an articulated rotor and methods for operation

The rotary damper for controlling helicopter motions includes an outer canister with an inner paddle wheel receiving cavity which receives an inner paddle wheel with upper and lower elastomeric tubular intermediate members between the inner paddle wheel and the outer canister. The canister and inner paddle wheel form neighboring variable volume chambers in liquid communication through liquid damping conduits. A clockwise rotation of the inner paddle wheel about the center of rotation axis relative to the outer canister pumps damper liquid from a second variable volume chamber through a first liquid conduit towards a first variable volume chamber, and a counterclockwise rotation of the paddle wheel relative to the outer canister pumps the damper liquid from the first variable volume chamber through the first liquid conduit towards the second variable volume chamber with the elastomeric tubular intermediate members providing for the relative rotation and containing the damper liquid in the damper.

Rotary wing aircraft rotary lead lag damper

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. The helicopter rotor damper system includes a damper link linked with the torsional damper, with the torsional damper and the damper link connected between a helicopter blade and a helicopter rotor with the elastomeric torsional damper nonelastomeric bonding surfaces relatively rotating.

Helicopter aircraft vehicle rotor damper

A fluid-elastomeric damper assembly operable for damping relative motion between a first structure and a second structure including a housing structure grounded to the first structure and a plurality of elastomer seals coupled to the housing structure, the housing structure and the plurality of elastomer seals defining a fluid-elastomeric chamber operable for containing a fluid. The fluid-elastomeric damper assembly also including one or more piston structures disposed within the housing structure and the fluid-elastomeric chamber, the one or more piston structures grounded to the first structure and driven by the second structure, and the one or more piston structures each including a first substantially fluid-filled chamber and a second substantially-fluid-filled chamber in communication via an orifice, the first substantially fluid-filled chamber and the second substantially fluid-filled chamber also in communication with the fluid-elastomeric chamber. The housing structure is operable for pumping the fluid through the orifice.

Fluid-elastomeric damper assembly including internal pumping mechanism

A damper assembly including a spherical elastomer bearing member, wherein the spherical elastomer bearing member is operable for accommodating relative motion and/or vibration, and a flat elastomer bearing member, wherein the flat elastomer bearing member is operable for accommodating relative motion and/or vibration. The damper assembly also including a substantially rigid transition shim disposed between the spherical elastomer bearing member and the flat elastomer bearing member, wherein the substantially rigid transition shim is operable for coupling the spherical elastomer bearing member to the flat elastomer bearing member. The damper assembly further including a tension member attached to the substantially rigid transition shim, wherein the tension member is operable for precompressing the spherical elastomer bearing member and increasing the cocking stiffness of the damper assembly.

Flexbeam damper assembly having transition shim clamp device

A fluid and elastomer damper includes a first and second members and an elastomer section flexibly mounting the second member to the first member and allowing lateral movement therebetween. The elastomer section includes an inner wall forming a portion of a cavity defined within the damper and a damping fluid disposed within the cavity. A flexible damping plate separates the cavity into first and second chambers. At least one passageway is formed between the damping plate and the inner wall, the passageway exhibiting a gap dimension between the wall and the damping plate. When lateral movement occurs between the first and second members, the gap dimension is maintained substantially constant by flexing of the damping plate along the lateral direction.

Fluid damper including flexible damping plate

An active fluid mounting for isolating vibration between a vibrating member (21) and a structure (23). In one aspect, the active fluid mounting (20) includes an inner member (22), an outer member (24), a first flexible element (26), and an cartridge-like active fluid element (28) which is unitary and readily detachable, attached between the inner and outer members, (22) and (24). The cartridge-like active fluid element (28) preferably includes a first housing member (30) for attachment to inner member (22), a second housing member (32) for attachment to outer member (24), a second flexible element (34) for flexibly interconnecting first housing member (30) to second housing member (32), at least one fluid chamber (36) having a volume stiffness, a fluid (40) contained within, a moveable piston (42) interacting with fluid (40) in the fluid chamber (36) to cause pressure variations and produce dynamic forces which act between the inner and outer member, (22) and (24), and a preferable coil-and-magnet assembly (44) for driving piston (42) housed internally within active fluid element (28). In another aspect, a piston (42a) which is inductively driven is described. In yet another, an interchangeable motor unit including a magnet (68), coil (70), and pole pieces (66) is received within the inner member (22).

Active fluid mounting

A fluid-filled Active Vibration Absorber (AVA) (20) is described for attaching to, and controlling dynamic vibration of the member (22). The AVA (20) is comprised of primary tuning mass (23) preferably including an additional inertial tuning mass (26) which is associated with a primary resonant frequency (fn1), a flexible element (28) for interconnecting the primary mass (23) and, thus, interconnecting inertial tuning mass (26) to member (22), at least one, and preferably two, fluid chambers, (30) and (32), each having a defined volume stiffness Kv'1, Kv'2, a fluid (34) contained within the at least one and preferably two, fluid chambers, (30) and (32), a moveable piston (36) dynamically interacting with the fluid (34) in the at least one fluid chamber and preferably, in first and second fluid chambers, (30) and (32), to cause pressure variations which dynamically drive the primary tuning mass (23) within a range about the primary resonant frequency (fn1). Preferably, a coil (40) and magnet-and-pole assembly (38) driving the piston (36). The AVA (20) preferably includes a secondary resonance (fn2) which is tunable by adjusting the mass of the piston (36), volume stiffness Kv'1 of the first fluid chambers (30), and a piston area Ap1, amongst other parameters.

Fluid-filled active vibration absorber

A method and apparatus is described for limiting transient motions between an aircraft power member and aircraft structure. The apparatus incorporates a coupler (20) for use with inertial-type mounts and includes a body portion (21) having a coupler piston (32) telescopically received therein. Upon exceeding a transient relative motion which causes a fluid flow velocity to be exceeded, seat (38) formed on coupler piston (32) interacts with lip (39) on body portion (21) to cause a fluid flow restriction. This method and apparatus restricts and limits transient motions, i.e., acts as a snuffer, to limit further relative motion between an aircraft power member (54) and an aircraft structural member (52). The coupler piston (32) preferably includes a flexible seal (38) formed thereon and orifice (40) therethrough for providing additional throttle-type damping upon snubbing. This method and apparatus is particularly useful in inertial-type fluid mounts for mounting aircraft engines, fluid pylon isolators for helicopter pylon isolation, and Fluid Torque Restraint (FTR) systems for aircraft for limiting transient motions under certain conditions, such as during takeoff, landing, and maneuvers, yet providing isolation under normal operating conditions.

Method and apparatus for reducing transient motion between an aircraft

A flexible composite coupling (20) wherein a wound filament or roving is wound between two attachment members (22) and (24) and is fully or partially impregnated with a resin matrix such as urethane to form a flexible element (32). The attachment members (22) and (24) include radially extending flanges (26) and (28) which have a radiused periphery (30) formed on them, over which the flexible element (32) is wound. The flexible element (32) diverges inwardly from the flanges' (26) and (28) radiused periphery (30) to form opposed diaphragm portions (34) and (35) of the flexible element (32) which smoothly meet at a minimum diameter (36). Hoop winds (38) of a material with high strain capacity wrapped about this minimum diameter (36) pretension the filaments or roving within the flexible element (32).

Flexible composite coupling

A double pumper mount useful as a front mount for an aircraft engine. A pair of fluid chambers are selectively interconnectable by one of a plurality of inertia tracks by use of an adjustable cylindrical member which has the tracks formed as generally helical grooves extending about the periphery of the cylindrical member. These inertia tracks have different flow characteristics so as to produce differing notch frequencies so as to attenuate different vibrational frequencies. A second embodiment has a single inertia track whose length can be altered by rotating the cylindrical member to change the point at which the ingress/egress port of the fluid chamber engages the circumferential portion of the inertia track.

Adaptive fluid mount

A fluid mount with the capability of actively controlling the amount of vibrational energy transmitted thereacross. An actuator is provided in series or in parallel with the inertia track passageway of a double pumper isolation mount to permit the dynamic stiffness of the mount to be varied so as to control the amount of vibrational energy transmitted in a desired manner. A control system for permitting frequency-shaped force feedback control of the device is also disclosed. Utilization of the device as a tuned absorber is also described.

Fluid mount with active vibration control

A fluid mount particularly suited for mounting an engine in an aircraft. The mount includes a frame which is fastened to the engine and a support movably mounted in the frame and adapted to receive a wing pylon stub shaft. Opposed liquid-filled chambers are provided on opposite sides of the stub shaft support and are fluidly interconnected by an elongate tube. An auxiliary chamber is provided on the frame adjacent to the upper liquid chamber and is divided internally into a gas-filled portion and a liquid-filled portion which is in communication with the upper liquid chamber via an orifice. The auxiliary chamber accommodates changes in liquid volume without adversely affecting either the static or dynamic performance of the mount.

Growing community of inventors

Erie, PA, United States of America

Peter J Jones