Abstract: A system may detect a vibration being applied to a tuned vibration absorber. The tuned vibration absorber may include a beam, a mass, springs, a sensor, and an actuator. The mass may be disposed on the beam at a current position. The actuator may be configured to adjust a position of the mass on the beam. The system may identify a target position of the mass on the beam based on the detected vibration. The system may generate a drive signal, based on the target position, to control the actuator to adjust the position of the mass on the beam. The system may control the actuator to adjust the position of the mass from the current position on the beam to the target position on the beam to attenuate the vibration.

Abstract: A shock absorbing apparatus includes a flexible membrane defining an accumulator cavity, and a compression assembly defining a compression cavity. The compression assembly is disposed within the flexible membrane such that viscous fluid contained within the cavities may be exchanged therebetween by a damping orifice, fluid conduit and or valve mechanism. The accumulator cavity deforms in response to the application of a transmitted impact load, and is capable of storing and releasing potential energy in response to the application and cessation of the transmitted impact load.

Abstract: A system may detect a vibration being applied to a tuned vibration absorber. The tuned vibration absorber may include a beam, a mass, springs, a sensor, and an actuator. The mass may be disposed on the beam at a current position. The actuator may be configured to adjust a position of the mass on the beam. The system may identify a target position of the mass on the beam based on the detected vibration. The system may generate a drive signal, based on the target position, to control the actuator to adjust the position of the mass on the beam. The system may control the actuator to adjust the position of the mass from the current position on the beam to the target position on the beam to attenuate the vibration.

Abstract: A rotary wing aircraft bearing that provides a constrained relative motion between a first rotary wing aircraft member and a second rotary wing aircraft member. The bearing includes an elastomeric mold bonded laminated bearing stack, the elastomeric mold bonded laminated bearing stack including a plurality of mold bonded alternating layers of nonelastomeric shim member layers and elastomeric shim members layers, the alternating layers having an exterior surface and an interior center distal from the exterior surface.

Abstract: A shock absorbing apparatus includes a flexible membrane defining an accumulator cavity, and a compression assembly defining a compression cavity. The compression assembly is disposed within the flexible membrane such that viscous fluid contained within the cavities may be exchanged therebetween by a damping orifice, fluid conduit and or valve mechanism. The accumulator cavity deforms in response to the application of a transmitted impact load, and is capable of storing and releasing potential energy in response to the application and cessation of the transmitted impact load.

Abstract: A shock absorbing apparatus includes a flexible membrane defining an accumulator cavity, and a compression assembly defining a compression cavity. The compression assembly is disposed within the flexible membrane such that viscous fluid contained within the cavities may be exchanged therebetween by a damping orifice, fluid conduit and or valve mechanism. The accumulator cavity deforms in response to the application of a transmitted impact load, and is capable of storing and releasing potential energy in response to the application and cessation of the transmitted impact load.

Abstract: 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.

Abstract: 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.

Abstract: A wear-indicating bearing and method of detecting wear in a bearing are disclosed. The bearing includes a bearing stack having a first end and a second end with a longitudinal axis defined between the first and second ends. The bearing stack includes a plurality of elastomeric layers sandwiched between non-elastomeric shim layers, where each layer is concentric about the longitudinal axis. At least one elastomeric layer is a marker layer configured to indicate wear of the bearing. The marker layer is made up of a first elastomeric composition and a second elastomeric composition, wherein the first and second elastomeric compositions have optically different characteristics. Upon fatigue of the bearing, the first elastomeric composition is detectable through a fracture extending from an exterior surface of the bearing stack.

Abstract: A shock absorbing apparatus includes a flexible membrane defining an accumulator cavity, and a compression assembly defining a compression cavity. The compression assembly is disposed within the flexible membrane such that viscous fluid contained within the cavities may be exchanged therebetween by a damping orifice, fluid conduit and or valve mechanism. The accumulator cavity deforms in response to the application of a transmitted impact load, and is capable of storing and releasing potential energy in response to the application and cessation of the transmitted impact load.

Abstract: A rotary wing aircraft bearing that provides a constrained relative motion between a first rotary wing aircraft member and a second rotary wing aircraft member. The bearing includes an elastomeric mold bonded laminated bearing stack, the elastomeric mold bonded laminated bearing stack including a plurality of mold bonded alternating layers of nonelastomeric shim member layers and elastomeric shim members layers, the alternating layers having an exterior surface and an interior center distal from the exterior surface.

Abstract: A snubbed isolator comprising: an inner member, the inner member (12) having: a lower member (25) including an upper surface (27) and base (32), wherein the base is wider than the upper surface; a stem (24) integral with the lower member, the stem including a top, wherein the top is oppositely positioned from the base; a surface associated with the top of the stem, the surface being capable of bearing load; an outer member (14) positioned outwardly from the inner member, the outer member having a surface that is wider near the base of the lower member and narrower proximate the upper surface of the lower member; an interlock between the inner and outer members; an elastomeric element (16) bonded between the inner and outer members; and at least one snubbing elastomeric element (34) bonded to the inner member and positioned to snub against a mounting structure.

Abstract: A rotary wing aircraft bearing that provides a constrained relative motion between a first rotary wing aircraft member and a second rotary wing aircraft member. The bearing includes an elastomeric mold bonded laminated bearing stack, the elastomeric mold bonded laminated bearing stack including a plurality of mold bonded alternating layers of nonelastomeric shim member layers and elastomeric shim members layers, the alternating layers having an exterior surface and an interior center distal from the exterior surface.

Abstract: A rotary wing aircraft bearing that provides a constrained relative motion between a first rotary wing aircraft member and a second rotary wing aircraft member. The bearing includes an elastomeric mold bonded laminated bearing stack, the elastomeric mold bonded laminated bearing stack including a plurality of mold bonded alternating layers of nonelastomeric shim member layers and elastomeric shim members layers, the alternating layers having an exterior surface and an interior center distal from the exterior surface.

Abstract: A wear-indicating bearing and method of detecting wear in a bearing are disclosed. The bearing includes a bearing stack having a first end and a second end with a longitudinal axis defined between the first and second ends. The bearing stack includes a plurality of elastomeric layers sandwiched between non-elastomeric shim layers, where each layer is concentric about the longitudinal axis. At least one elastomeric layer is a marker layer configured to indicate wear of the bearing. The marker layer is made up of a first elastomeric composition and a second elastomeric composition, wherein the first and second elastomeric compositions have optically different characteristics. Upon fatigue of the bearing, the first elastomeric composition is detectable through a fracture extending from an exterior surface of the bearing stack.

Abstract: 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.

Abstract: A tuned vibration absorber includes a mounting plate having at least two, and alternatively four, mounting holes in spaced relationship from a longitudinal center axis of the plate. An elastomeric spring is bonded to the mounting plate. A main tuning mass is bonded to the elastomeric spring opposite the mounting plate, and fine tuning masses are riveted directly onto the main tuning mass. The elastomeric spring and main mass both have a rectangular profile to maintain a low profile height from the mounting plate. A cover is formed of a single sheet of metal bent to form a rectangular box with one open side. The cover includes mounting flanges with holes that align with the mounting holes on the mounting plate. For mounting the vibration absorber on a stiffening ring of an aircraft frame, a spacing plate is positionable between a portion of the mounting plate and the stiffening rib of an aircraft frame, and adjacent to an overlapping secondary stiffening ring to provide a flat mounting surface.

Abstract: A mounting (20) which provides low vertical and lateral spring rates for excellent lateral and vertical vibration isolation yet provides a high roll stiffness for reacting torsional moments, while reducing isolator complexity and eliminating the need for a yoke or hanger. The mounting (20) includes a top member (34), a first arm (26) and a second arm (28) which are flexibly interleaved or attached. The first arm (26) is attached to a top member (34) by way of a pivot which can be a spring (30), the second arm (28) is also attached to the top member (34) by another pivot which can be a spring (32), and a third spring (36) attaches the arms (26) and (28) to each other. The arms (26) and (28) also attach to the supported member (22) preferably at their respective outboard ends (38), or at least one intermediate link can be used.

Abstract: 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.