Method and apparatus for reducing transient motion between an aircraft power member and structure during takeoff, landing and maneuvers
May 10, 2016. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.Patent References 2705118 3122162 Damper device, in particular for the suspension of an engine Rubber elastic engine mounts or supports with hydraulic damping Vibration suppression system Elastically yieldable block structure, in particular for the suspension of an engine of a vehicle Vibration damping bushing Viscous spring damper Rubber and fluid type vibration damper Double-ended liquid line thermal insulator InventorsAssigneeApplicationNo. 644147 filed on 05/10/1996US Classes:267/136, RESILIENT SHOCK OR VIBRATION ABSORBER137/513.3, With leak passage137/517, Biased open188/379, Resiliently supported damping mass267/293Including central guide rod or tube through springExaminersPrimary: Poon, Peter M.Attorney, Agent or FirmForeign Patent References
International ClassesF16M 001/00F16F 007/10 F16K 015/00 AbstractA method and apparatus is described for limiting transient motions between an aircraft power member and aircraft structure. The apparatus incorporates a coupler (20) for use with inertial-type mounts and includes a body portion (21) having a coupler piston (32) telescopically received therein. Upon exceeding a transient relative motion which causes a fluid flow velocity to be exceeded, seat (38) formed on coupler piston (32) interacts with lip (39) on body portion (21) to cause a fluid flow restriction. This method and apparatus restricts and limits transient motions, i.e., acts as a snuffer, to limit further relative motion between an aircraft power member (54) and an aircraft structural member (52). The coupler piston (32) preferably includes a flexible seal (38) formed thereon and orifice (40) therethrough for providing additional throttle-type damping upon snubbing. This method and apparatus is particularly useful in inertial-type fluid mounts for mounting aircraft engines, fluid pylon isolators for helicopter pylon isolation, and Fluid Torque Restraint (FTR) systems for aircraft for limiting transient motions under certain conditions, such as during takeoff, landing, and maneuvers, yet providing isolation under normal operating conditions.Field of SearchSupported by mechanical springINERTIA OF DAMPING MASS DISSIPATES MOTION (E.G., VIBRATION DAMPER) Resiliently supported damping mass Axial Elastomeric Including central guide rod or tube through spring Having rigid spacer plate between plural elastomeric segments Including energy absorbing means or feature (e.g., supplemental vehicle equipment, such as motor mount, seat, etc., including additional fluid or friction energy absorber) RESILIENT SHOCK OR VIBRATION ABSORBER Rubber With leak passage Biased open Plural biasing means Coaxial oppositely directed seats Mounting | |
