# US 11,440,648 B2 · Compact vibration isolation systems for aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,440,648 B2 - Document ID: US11440648B2 - Status: Granted - Kind: B2 - Application number: 16/855,706 - Filed: 2020-04-22 - Published: 2021-10-28 - Granted: 2022-09-13 - Earliest claimed: 2020-04-22 - Assignees: Textron Innovations Inc. - Applicants: Textron Innovations Inc. - Inventors: Peter Quinn Romano; Frank Bradley Stamps; Michael Scott Seifert - Web page: https://patentgrep.com/patent/US11440648B2 ## CPC - B64C 27/001: {Vibration damping devices} - F16F 7/1034: {of movement of a liquid} - F16F 13/10: the wall being at least in part formed by a flexible membrane or the like (F16F13/14 - F16F13/18 take precedence) - B64C 2027/002: {mounted between the rotor drive and the fuselage} - F16F 2222/08: Inertia - B64C: AEROPLANES; HELICOPTERS - F16F: SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION ## Abstract A liquid inertia vibration eliminator unit for an aircraft having first and second components includes an outer housing coupled to the first component of the aircraft, the outer housing forming an outer housing cavity. The liquid inertia vibration eliminator unit includes a spherical bearing disposed in the outer housing cavity and forming a spherical bearing cavity. A piston is disposed in the spherical bearing cavity and coupled to the second component of the aircraft. Top and bottom fluid chambers are disposed in the spherical bearing cavity on opposite sides of the piston. A tuning passage provides fluid communication between the top and bottom fluid chambers. A tuning fluid moves between the top and bottom fluid chambers via the tuning passage to isolate vibration between the first and second components of the aircraft. ## Claims ### Claim 1 A liquid inertia vibration eliminator unit for an aircraft having first and second components, the liquid inertia vibration eliminator unit comprising: an outer housing coupled to the first component of the aircraft, the outer housing forming an outer housing cavity; a spherical bearing disposed in the outer housing cavity and forming a spherical bearing cavity; a fluid chamber housing disposed in the spherical bearing cavity such that the spherical bearing is interposed between the fluid chamber housing and the outer housing; a piston disposed in the spherical bearing cavity and coupled to the second component of the aircraft; top and bottom fluid chambers disposed in the spherical bearing cavity on opposite sides of the piston and at least partially defined by the fluid chamber housing; a tuning passage providing fluid communication between the top and bottom fluid chambers; and a tuning fluid movable between the top and bottom fluid chambers via the tuning passage to at least partially isolate vibration between the first and second components of the aircraft. ### Claim 2 (depends on 1) The liquid inertia vibration eliminator unit as recited in claim 1 wherein the outer housing forms an inner surface defining the outer housing cavity, the spherical bearing substantially covering the inner surface of the outer housing and having a concave inner surface. ### Claim 3 (depends on 1) The liquid inertia vibration eliminator unit as recited in claim 1 wherein the piston oscillates inside the spherical bearing cavity in response to vibration of at least one of the first or second components of the aircraft. ### Claim 4 (depends on 3) The liquid inertia vibration eliminator unit as recited in claim 3 wherein the tuning fluid oscillates between the top and bottom fluid chambers via the tuning passage in response to the oscillations of the piston. ### Claim 5 (depends on 1) The liquid inertia vibration eliminator unit as recited in claim 1 wherein the piston further comprises a solid piston having an ellipsoid shape. ### Claim 6 (depends on 1) The liquid inertia vibration eliminator unit as recited in claim 1 further comprising a top piston rod coupled to a top side of the piston, the piston coupled to the second component of the aircraft via the top piston rod. ### Claim 7 (depends on 1) The liquid inertia vibration eliminator unit as recited in claim 1 wherein a top side of the piston at least partially defines the top fluid chamber and a bottom side of the piston at least partially defines the bottom fluid chamber. ### Claim 8 (depends on 1) The liquid inertia vibration eliminator unit as recited in claim 1 wherein the tuning passage further comprises an external tuning tube disposed outside of the outer housing. ### Claim 9 (depends on 1) The liquid inertia vibration eliminator unit as recited in claim 1 wherein the spherical bearing permits rotational and pivotal movement of the fluid chamber housing relative to the outer housing. ### Claim 10 (depends on 1) The liquid inertia vibration eliminator unit as recited in claim 1 further comprising a middle journal bearing interposed between a middle portion of the piston and the fluid chamber housing such that a top side of the middle journal bearing at least partially defines the top fluid chamber and a bottom side of the middle journal bearing at least partially defines the bottom fluid chamber. ### Claim 11 (depends on 1) The liquid inertia vibration eliminator unit as recited in claim 1 further comprising: a top journal bearing coupled to a top side of the piston; a bottom journal bearing coupled to a bottom side of the piston; and a middle journal bearing coupled to a middle portion of the piston between the top and bottom sides of the piston; wherein the journal bearings are annular and formed from an elastomeric material. ### Claim 12 (depends on 1) The liquid inertia vibration eliminator unit as recited in claim 1 further comprising a gas accumulator in fluid communication with the fluid chambers via a gas passage to pressurize the tuning fluid. ### Claim 13 (depends on 12) The liquid inertia vibration eliminator unit as recited in claim 12 further comprising a fluid chamber housing disposed in the spherical bearing cavity, the gas accumulator disposed on a top side of the fluid chamber housing. ### Claim 14 (depends on 12) The liquid inertia vibration eliminator unit as recited in claim 12 further comprising a top piston rod coupled to a top side of the piston, the gas accumulator disposed in the top piston rod. ### Claim 15 A rotorcraft comprising: a fuselage; a fuselage airframe supporting the fuselage; a pylon assembly subject to vibration; and a plurality of liquid inertia vibration eliminator units interposed between the fuselage airframe and the pylon assembly, each liquid inertia vibration eliminator unit comprising: an outer housing coupled to the fuselage airframe, the outer housing forming an outer housing cavity; a spherical bearing disposed in the outer housing cavity and forming a spherical bearing cavity; a fluid chamber housing disposed in the spherical bearing cavity such that the spherical bearing is interposed between the fluid chamber housing and the outer housing; a piston disposed in the spherical bearing cavity and coupled to the pylon assembly; top and bottom fluid chambers disposed in the spherical bearing cavity on opposite sides of the piston and at least partially defined by the fluid chamber housing; a tuning passage providing fluid communication between the top and bottom fluid chambers; and a tuning fluid movable between the top and bottom fluid chambers via the tuning passage to at least partially isolate vibration between the pylon assembly and the fuselage airframe. ### Claim 16 (depends on 15) The rotorcraft as recited in claim 15 wherein the pistons of the liquid inertia vibration eliminator units are coupled to an underside of the pylon assembly and the outer housings of the liquid inertia vibration eliminator units are coupled to a top side of the fuselage airframe. ### Claim 17 (depends on 15) The rotorcraft as recited in claim 15 wherein each liquid inertia vibration eliminator unit has a height H and a width W and wherein W>H. ### Claim 18 (depends on 17) The rotorcraft as recited in claim 17 wherein W≥2H. ### Claim 19 (depends on 15) The rotorcraft as recited in claim 15 wherein each liquid inertia vibration eliminator unit further comprises a mounting plate forming a clearance aperture coupled to an underside of the outer housing, the outer housing coupled to the fuselage airframe via the mounting plate.