A mounting system for a vibration isolation device comprises a support structure having an opening disposed therein, the opening having a concave recess; a thin elastomeric component attached to a surface of the concave recess; and a spherical elastomeric bearing disposed in the opening and attached to the thin elastomeric component, the spherical elastomeric bearing having a beveled upper portion, a middle portion and a beveled lower portion configured to engage the vibration isolation devices.

An aircraft, has an airframe, a transmission, and a liquid inertia vibration elimination (LIVE) system disposed between the airframe and the transmission via spherical bearings of two legs and via a central spherical bearing.

A vertical take-off and landing (VTOL) aircraft includes an airframe having a transverse axis and a longitudinal axis that is substantially perpendicular relative to the transverse axis. A transmission and rotor support platform is arranged in the airframe. A transmission is supported by the transmission and rotor support platform. An energy attenuation system mechanically links the transmission and rotor support platform with the airframe. The energy attenuation system includes a first plurality of collapsible support members selectively facilitating rotation of the transmission and rotor support platform about the transverse axis and a second plurality of collapsible support members, the first and second pluralities of support members selectively facilitating translation of the transmission and rotor support platform along an axis that is substantially parallel to the rotor axis.

A vibration damping device equipped with a resonator mechanism comprising at least one resonator, the at least one resonator having a first beater extending from an embedded end to a free beating end. The resonator consists of an elastically deformable base equipped with a first branch and a second branch connected by a central section, the embedded end being embedded at the first branch, the first branch extending from a first end to a second end each rigidly fastened to a mount, the second branch extending from a first end section to a second end section each rigidly fastened to a vibration source.

An aircraft includes a frame, a transmission, and a liquid inertia vibration elimination (LIVE) system coupled between the frame and the transmission. The LIVE system is configured to attenuate communication of vibrations from the transmission to the frame. The LIVE system includes a first liquid zone, a second liquid zone, a plug at least partially segregating the first liquid zone from the second liquid zone, and the plug has an aperture in fluid communication with the first liquid zone and the second liquid zone. A splash guard is disposed within the second liquid zone and offset from the plug.

An aerial vehicle system includes a signal generator, a plurality of computing components, a plurality of communication antennas, a first structural component configured to at least in part block a noise signal generated by the signal generator from the plurality of computing components, and a second structural component configured to at least in part block the noise signal generated by the signal generator from the plurality of communication antennas, wherein the first structural component and the second structural component form a portion of a structural frame of the aerial vehicle system.

A liquid inertia vibration elimination (LIVE) system having an upper end cap, a lower end cap, a spindle located between the upper end cap and the lower end cap, and an external tube connected between the upper end cap and the lower end cap.

A rotary wing aircraft includes a rotor system rotatable about an axis relative to an airframe. A plurality of blade assemblies is mounted to the rotor system. A higher harmonic control system is operable to generate a harmonic load at the rotor system according to a higher harmonic control signal. An active vibration control system is operable to generate vibration forces about the aircraft according to an active vibration control signal. A controller is operable to issue the higher harmonic control signal and the active vibration control signal to coordinate the higher harmonic control system and the active vibration control system to reduce vibration within the airframe.

An aircraft is provided and includes an airframe, an engine, a drive portion driven by the engine, a rotor apparatus, which includes a rotor rotatable relative to the airframe and a fairing, a gearbox disposed to transmit rotational energy from the drive portion to the rotor to drive the rotor to rotate relative to the airframe and which generates a rotor rotation vibration, support members by which the gearbox is disposed on the airframe and an actuation system including actuation elements disposed at the fairing, the actuation system being configured to generate an anti-vibration moment using the actuation elements disposed at the fairing to counter the rotor rotation vibration.

A strut assembly for a vibration isolation device is disclosed, comprising a piston spindle; a first elastomeric member and a second elastomeric member bonded to the piston spindle and in contact with an upper housing and a lower housing, respectively; a first strut support and a second strut support attached to or integral with the upper housing and the lower housing, respectively; a first strut spindle and the second strut support configured to be placed in the first strut support and the second strut support, respectively; and one or more removable struts configured to be engaged to the first strut spindle and to the second strut spindle, wherein at least one of the first or second strut spindles is removable such that the one or more struts can be replaced without breaking a bonding of the first elastomeric member, the second elastomeric member, or both.