Lord Corporation

Textron Innovations Inc.

Paul Joseph Bachmeyer

Doug Hodgson

Douglas A Swanson

Scott K Thompson

Bryan J Pittman

Michael R Blewett

Gerald P Whiteford

Wallace C Flower

Douglas A Hodgson

Kirk W Olsen

Thomas R Law

Peter A Masterson

Darrin Michael Jones

Nicholas V Anderson

Marvin D Ohme

Francis J DePriest

Jacques Lemire

Systems and method for active vibration control on an aircraft. An active vibration control system (AVCS) is configured for an aircraft having an aircraft structure and a gun. The AVCS includes at least one control sensor on the aircraft, at least one force generator on the aircraft, and at least one controller in electronic communication with the sensor and the force generator. The controller is configured for determining, using the at least one control sensor, force generating commands for controlling vibrations acting on the aircraft structure, sending the force generating commands to the at least one force generator, causing the at least one force generator to produce a vibration canceling force, determining that the gun is firing, and in response to determining that the gun is firing, determining different force generating commands and sending the different force generating commands to the at least one force generator.

Active vibration control system in a gunfire vibration environment

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.

Aircraft landing gear assembly shimmy damper

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. The assembly includes a grease disposed between the outer elastomer surface and the nonelastomeric outer member frictional interface inner surface segment with the greased grooved outer elastomer surface engaging the nonelastomeric outer member frictional interface inner surface segment and inhibiting an oscillating rotation.

An aircraft front nose landing gear having both elastomeric and nonelastomeric elements is provided along with a method of making the same. The aircraft front nose landing gear includes the ability to reduce/inhibit oscillating shimmy rotation vibrations. The method further provides for making a landing gear with a shimmy damper for further reducing oscillating rotations.

Aircraft front nose landing gear and method of making an aircraft landing gear

An aircraft vehicular front wheel landing gear assembly is provided that includes a nonelastomeric outer upper strut tubular member having an inner axial center bore with a tubular cylindrical frictional interface inner surface segment, and a nonelastomeric inner lower strut member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer strut member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer strut member. The assembly includes an elastomeric surface effect damper member encompassing the nonelastomeric inner strut member outer bonding surface segment. The elastomeric surface effect damper member has an inner bonding surface segment and an outer elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner strut member outer bonding surface segment. The assembly includes a surface effect lubricant disposed between the elastomeric surface effect damper outer elastomer surface and the nonelastomeric outer strut member frictional interface inner surface segment with the elastomeric surface effect damper outer elastomer surface engaging the nonelastomeric outer strut member frictional interface inner surface segment and inhibiting an oscillating shimmy rotation.

A vibration isolation device is disclosed. More specifically the vibration isolation device of the present invention comprises a fuse for decreasing the mount stiffness when loads above a threshold load value are applied to the device. The fuse for decreasing the mount stiffness comprises a shear pin with shear locations that comprise annular grooves with semielliptical cross sections.

Vibration isolation device with load dependent stiffness

A surface effect damper comprising a housing having a wall that defines a chamber, the housing having a first end, a second end and an axis; at least one contact element movable through the chamber between the housing ends in a first direction and in a second direction; and at least two damping elements substantially surrounding each contact element, each of the at least two damping elements being movable away from the axis and into frictional engagement with the wall as the at least one contact element is moved in a first direction and each of the at least two damping elements being movable toward the axis as the at least one contact element is moved in a second direction.

Surface effect damper

A system for supporting an auxiliary power unit in an aircraft tailcone wherein the auxiliary power unit is supported by a focalized suspension system supporting the power unit, the focalized suspension system having a plurality of support means each having a line of action, the lines of action intersecting at the focal point. The support system simplifies removal and installation of the auxiliary power unit from and into the aircraft's tailcone.

Growing community of inventors

Cary, NC, United States of America

Paul Joseph Bachmeyer