Abstract: 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.

Abstract: 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.

Abstract: A mount for mounting a second structure on a first structure is provided. The mount (100) comprises a housing (10) having a first attachment surface for attachment to the first structure. The mount (100) also includes a biasing member (60) having a first end (62) located within the housing (10). A cupshaped retaining member (22) has a second attachment surface (29) for attaching the retaining member (22) to the second structure, wherein the retaining member (22) is adapted to receive a second end (64) of the biasing member (60) and at least partially locate within the housing (10) such that the biasing member (60) is constrained by the retaining member (22) and the housing (10). A cap (40) surrounds the retaining member (22) and provides a seal between the exterior of the retaining member (22) and the interior of the housing (10).

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

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