# US 2021/0277975 A1 · Method for damping torsional vibrations in a drive train, and drive train > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2021/0277975 A1 - Document ID: US20210277975A1 - Status: Published application - Kind: A1 - Application number: 17/053,542 - Filed: 2019-05-03 - Published: 2021-09-09 - Earliest claimed: 2018-05-08 - Assignees: ZF Friedrichshafen AG - Applicants: ZF Friedrichshafen AG - Inventors: Daniel Wolf; Jörg Litzba; Johannes Schäfer; Georg Tenckhoff - Web page: https://patentgrep.com/patent/US20210277975A1 ## CPC - F16F 15/002: {characterised by the control method or circuitry (control of mechanical oscillations per se G05D19/00)} - B64D 31/00: Power plant control systems; Arrangement of power plant control systems in aircraft - F16F 15/10: Suppression of vibrations in rotating systems by making use of members moving with the system (by balancing F16F15/22 {; yielding couplings F16D3/00} ; with flywheels acting variably or intermittently F16H {; construction providing resilience or vibration-damping for gear elements F16H55/14}) - F16D 2300/22: Vibration damping - F16F 2228/066: Variable stiffness - F16F 2232/02: Rotary - F16F 2236/08: Torsion - F16F: SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F16D: COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES ## Abstract A torsional moment acting on a component in a drive train of an aircraft may be determined using at least one sensor, where the determined torsional moment is used for adjusting at least one adjustable damping element located in or on the component and/or for regulating a torsional stiffness in the torque-conducting component. As a result, the torsional load in the component may be reduced. ## Claims ### Claim 1 A method for damping torsional vibrations in a drive train in aircraft, the method comprising: determining a torsional moment acting on a torque-conducting component of the drive train using at least one sensor; adjusting at least one adjustable damping element located in or on the torque-conducting component of the drive train based on the torsional moment; and regulating a torsional stiffness of the torque-conducting component to reduce the torsional load in the component. ### Claim 2 (depends on 1) The method according to claim 1, wherein the torsional moment is determined using at least one of: a magnetoelastic or magnetoresistant sensor; an angular position sensor; and an acoustic sensor. ### Claim 3 (depends on 1) The method according to claim 1, wherein the torsional moment is determined using a first and second sensor element. ### Claim 4 (depends on 1) The method according to claim 1, wherein the torsional moment is determined using a sensor element located on a drive train component, and wherein the sensor element is located on at least one of a transmission, a shaft, and a bearing. ### Claim 5 (depends on 1) The method according to claim 1, wherein the torsional moment is determined using a sensor element integrated in a drive train component. ### Claim 6 (depends on 1) The method according to claim 1, wherein the determined torsional moment is used for adjusting two adjustable damping elements to reduce the torsional load in the component. ### Claim 7 A drive train in an aircraft, comprising: a component that is configured to conduct a torque in the drive train, wherein the component includes at least one sensor element, the at least one sensor element being configured to determine a torsional moment acting on the component, wherein the component includes at least one adjustable damping element the at least one adjustable damping element being configured to reduce a torsional load in the component to adjust the degree of damping in the component, and wherein the component includes a control and regulating unit, the control and regulating unit being configured to evaluate the determined torsional moment, and to control the adjustable damping element based on the evaluated torsional moment. ### Claim 8 (depends on 7) The drive train according to claim 7, wherein the damping element is integrated in a clutch unit, and wherein the clutch unit connects two sections of the component to one another. ### Claim 9 (depends on 7) The drive train according to claim 7, wherein two sensor elements are included for determining the torsional moment. ### Claim 10 (depends on 7) The drive train according to claim 7, wherein two damping elements, connected either in series or parallel, are included for reducing the torsional load. ### Claim 11 (canceled) ### Claim 12 (canceled) ### Claim 13 (canceled) ### Claim 14 (depends on 7) The drive train according to claim 7, wherein the aircraft is a helicopter. ### Claim 15 (depends on 7) The drive train according to claim 7, wherein the aircraft is an airplane. ### Claim 16 A torque-conducting component for use in a drive train of an aircraft, comprising: at sensor configured to determine a torsional moment acting on the torque-conducting component; an adjustable damping element configured to reduce a torsional load in the component to adjust the degree of damping in the component; and a control and regulating unit, the control and regulating unit being configured to evaluate the determined torsional moment, and to control the adjustable damping element based on the evaluated torsional moment. ### Claim 17 (depends on 16) The torque-conducting component of claim 16, wherein the damping element is integrated in a clutch unit, and wherein the clutch unit connects two sections of the torque-conducting component to one another. ### Claim 18 (depends on 16) The torque-conducting component of claim 16, wherein two sensor elements are included for determining the torsional moment. ### Claim 19 (depends on 16) The torque-conducting component of claim 16, wherein two damping elements, connected either in series or parallel, are included for reducing the torsional load. ### Claim 20 (depends on 16) The torque-conducting component of claim 16, wherein the torque-conducting unit is included in a helicopter. ### Claim 21 (depends on 16) the torque-conducting component of claim 16, wherein the torque-conducting unit is included in an airplane.