Abstract: Damping coefficient-regulating inductive heating systems are provided, as are isolator assemblies containing such inductive heating systems. In embodiments, the isolator assembly includes a damper coefficient-regulating inductive heating system and at least one isolator, which contains a hydraulic damper fillable with a damping fluid. The damper coefficient-regulating inductive heating system includes, in turn, an inductive heating device, a controller, and a sensor for monitoring data indicative of damping fluid temperature. The inductive heating device is positioned around a periphery of the hydraulic damper, such as the outer periphery of the damper, in a non-contacting relationship. During isolator operation, the controller receives data from the sensor and, in response thereto, controls the inductive heating device to selectively generate a varying magnetic field to induce heating of one or more damper components, such as metal bellows, in contact with the damping fluid.

Abstract: Damping coefficient-regulating inductive heating systems are provided, as are isolator assemblies containing such inductive heating systems. In embodiments, the isolator assembly includes a damper coefficient-regulating inductive heating system and at least one isolator, which contains a hydraulic damper fillable with a damping fluid. The damper coefficient-regulating inductive heating system includes, in turn, an inductive heating device, a controller, and a sensor for monitoring data indicative of damping fluid temperature. The inductive heating device is positioned around a periphery of the hydraulic damper, such as the outer periphery of the damper, in a non-contacting relationship. During isolator operation, the controller receives data from the sensor and, in response thereto, controls the inductive heating device to selectively generate a varying magnetic field to induce heating of one or more damper components, such as metal bellows, in contact with the damping fluid.

Abstract: Embodiments of three parameter isolators including rolling seal damper assemblies are provided. In one embodiment, the three parameter isolator includes first and second isolator end portions, which are opposed along a working axis. A main spring and a tuning spring are mechanically coupled in parallel between the first and second isolator end portions. A rolling seal damper assembly is further mechanically coupled between the first and second isolator end portions in parallel with the main spring and in series with the tuning spring. The rolling seal damper assembly includes a first hydraulic chamber, a second hydraulic chamber fluidly coupled to the first hydraulic chamber, and first and second rolling diaphragm seals partially bounding the first and second hydraulic chambers, respectively. In certain implementations, the rolling seal damper assembly also contains a thermal compensator piston to which the first rolling diaphragm seal is attached.

Abstract: Embodiments of three parameter isolators including rolling seal damper assemblies are provided. In one embodiment, the three parameter isolator includes first and second isolator end portions, which are opposed along a working axis. A main spring and a tuning spring are mechanically coupled in parallel between the first and second isolator end portions. A rolling seal damper assembly is further mechanically coupled between the first and second isolator end portions in parallel with the main spring and in series with the tuning spring. The rolling seal damper assembly includes a first hydraulic chamber, a second hydraulic chamber fluidly coupled to the first hydraulic chamber, and first and second rolling diaphragm seals partially bounding the first and second hydraulic chambers, respectively. In certain implementations, the rolling seal damper assembly also contains a thermal compensator piston to which the first rolling diaphragm seal is attached.

Abstract: An apparatus is provided for vibration damping and isolation. The apparatus includes an annular spring portion including a resilient member that is substantially equally resilient in two dimensions, an annular bellows portion including at least two pairs of diametrically opposed bellows providing damping in the two dimensions, and a rigid connection member coupling the annular spring portion and the annular bellow portion in parallel to one another.

Abstract: Launch lock assemblies with reduced preload are provided. The launch lock assembly comprises first and second mount pieces, a releasable clamp device, and a pair of retracting assemblies. Each retracting assembly comprises a pair of toothed members having interacting toothed surfaces. The releasable clamp device normally maintains the first and second mount pieces in clamped engagement. When the releasable clamp device is actuated, the first and second mount pieces are released from clamped engagement and one toothed member of each retracting assembly moves in an opposite direction relative to the other one toothed member of the other retracting assembly to define an axial gap on each side of the first mount piece.

Abstract: Mounting systems for structural members, fastening assemblies thereof, and vibration isolation systems including the same are provided. Mounting systems comprise a pair of mounting brackets, each clamped against a fastening assembly forming a mounting assembly. Fastening assemblies comprise a spherical rod end comprising a spherical member having a through opening and an integrally threaded shaft, first and second seating members on opposite sides of the spherical member and each having a through opening that is substantially coaxial with the spherical member through opening, and a partially threaded fastener that threadably engages each mounting bracket forming the mounting assembly. Structural members have axial end portions, each releasably coupled to a mounting bracket by the integrally threaded shaft. Axial end portions are threaded in opposite directions for permitting structural member rotation to adjust a length thereof to a substantially zero strain position.

Abstract: Embodiments of an isolator are provided. In one embodiment, the isolator includes a damper housing having a radially-extending partition wall through which a central opening is formed. First and second hydraulic chambers are located on opposing sides of the radially-extending partition wall and may be filled with a damping fluid. At least one restricted orifice is formed through the damper housing and fluidly couples the first and second hydraulic chambers. The isolator further includes a damper piston, which extends through the central opening, which is exposed to the damping fluid when the first and second hydraulic chambers are filled therewith, and which is configured to translate along the working axis with respect to the damper housing during operation of the isolator.

Abstract: Embodiments of a fluid damper are provided, as are embodiments of an Auxiliary Power Unit inlet system including a fluid damper. In one embodiment, the fluid damper includes a housing assembly containing first and second hydraulic chambers, which are fluidly coupled by way of a flow passage. A plunger is slidably disposed within the housing assembly and is moves through a range of translational positions in response to variations in damping fluid pressure when the fluid damper is filled with damping fluid. An annulus or other restricted flow path is fluidly coupled between the first and second hydraulic chambers and is at least partially defined by the flow passage and the plunger. The restricted flow path has at least one dimension, such as a length, that varies in conjunction with the translational position of the plunger.

Abstract: An apparatus is provided for vibration damping and isolation. The apparatus includes an annular spring portion including a resilient member that is substantially equally resilient in two dimensions, an annular bellows portion including at least two pairs of diametrically opposed bellows providing damping in the two dimensions, and a rigid connection member coupling the annular spring portion and the annular bellow portion in parallel to one another.

Abstract: Embodiments of a gas turbine engine are provided, as are embodiments of an annular bearing support damper and embodiments of a method for manufacturing an annular bearing support damper. In one embodiment, the gas turbine engine includes engine housing and a rotor assembly disposed within the engine housing. A rotor bearing supports the rotor assembly within the engine housing, and an annular bearing support damper is positioned between the rotor bearing and the engine housing. The support damper includes an annular housing assembly having a damping fluid annulus. An array of circumferentially-spaced damper pistons is movably coupled to the annular housing assembly and fluidly communicates with the damping fluid annulus. The damper pistons are fixedly coupled to the rotor bearing and moves in conjunction therewith to force the flow of damping fluid around the annulus during engine operation to reduce the transmissions of vibrations to the engine housing.

Abstract: Embodiments of a fluid damper are provided, as are embodiments of an Auxiliary Power Unit inlet system including a fluid damper. In one embodiment, the fluid damper includes a housing assembly containing first and second hydraulic chambers, which are fluidly coupled by way of a flow passage. A plunger is slidably disposed within the housing assembly and is moves through a range of translational positions in response to variations in damping fluid pressure when the fluid damper is filled with damping fluid. An annulus or other restricted flow path is fluidly coupled between the first and second hydraulic chambers and is at least partially defined by the flow passage and the plunger. The restricted flow path has at least one dimension, such as a length, that varies in conjunction with the translational position of the plunger.

Abstract: Resilient aircraft engine mounts and mounting systems including the same are provided. A resilient aircraft engine mount comprises a base and a pair of opposed spiral springs in parallel forming a clevis with the base. A first spiral spring of the pair of opposed spiral springs has a first center opening extending therethrough. A second spiral spring of the pair of opposed spiral springs has a second center opening extending therethrough that is concentric with the first center opening for accepting a clevis pin. First and second spiral springs are each comprised of a rectangular cross section beam. The resilient aircraft engine mount is tunable in three translational axes to support three degrees of freedom vibration isolation. Two or more resilient aircraft engine mounts provide six degrees of freedom vibration isolation. Resilient aircraft engine mounts attach the aircraft engine to a pylon structure and help isolate vibratory forces.

Abstract: Launch lock assemblies with reduced preload are provided. The launch lock assembly comprises first and second mount pieces, a releasable clamp device, and a pair of retracting assemblies. Each retracting assembly comprises a pair of toothed members having interacting toothed surfaces. The releasable clamp device normally maintains the first and second mount pieces in clamped engagement. When the releasable clamp device is actuated, the first and second mount pieces are released from clamped engagement and one toothed member of each retracting assembly moves in an opposite direction relative to the other one toothed member of the other retracting assembly to define an axial gap on each side of the first mount piece.

Abstract: Embodiments of a launch lock assembly are provided, as are embodiments of a spacecraft isolation system including one or more launch lock assemblies. In one embodiment, the launch lock assembly includes first and second mount pieces, a releasable clamp device, and an axial gap amplification device. The releasable clamp device normally maintains the first and second mount pieces in clamped engagement; and, when actuated, releases the first and second mount pieces from clamped engagement to allow relative axial motion therebetween. The axial gap amplification device normally residing in a blocking position wherein the gap amplification device obstructs relative axial motion between the first and second mount pieces. The axial gap amplification device moves into a non-blocking position when the first and second mount pieces are released from clamped engagement to increase the range of axial motion between the first and second mount pieces.

Abstract: Embodiments of a launch lock assembly are provided, as are embodiments of a spacecraft isolation system including one or more launch lock assemblies. In one embodiment, the launch lock assembly includes first and second mount pieces, a releasable clamp device, and an axial gap amplification device. The releasable clamp device normally maintains the first and second mount pieces in clamped engagement; and, when actuated, releases the first and second mount pieces from clamped engagement to allow relative axial motion therebetween. The axial gap amplification device normally residing in a blocking position wherein the gap amplification device obstructs relative axial motion between the first and second mount pieces. The axial gap amplification device moves into a non-blocking position when the first and second mount pieces are released from clamped engagement to increase the range of axial motion between the first and second mount pieces.

Abstract: Resilient aircraft engine mounts and mounting systems including the same are provided. A resilient aircraft engine mount comprises a base and a pair of opposed spiral springs in parallel forming a clevis with the base. A first spiral spring of the pair of opposed spiral springs has a first center opening extending therethrough. A second spiral spring of the pair of opposed spiral springs has a second center opening extending therethrough that is concentric with the first center opening for accepting a clevis pin. First and second spiral springs are each comprised of a rectangular cross section beam. The resilient aircraft engine mount is tunable in three translational axes to support three degrees of freedom vibration isolation. Two or more resilient aircraft engine mounts provide six degrees of freedom vibration isolation. Resilient aircraft engine mounts attach the aircraft engine to a pylon structure and help isolate vibratory forces.

Abstract: Mounting systems for structural members, fastening assemblies thereof, and vibration isolation systems including the same are provided. Mounting systems comprise a pair of mounting brackets, each clamped against a fastening assembly forming a mounting assembly. Fastening assemblies comprise a spherical rod end comprising a spherical member having a through opening and an integrally threaded shaft, first and second seating members on opposite sides of the spherical member and each having a through opening that is substantially coaxial with the spherical member through opening, and a partially threaded fastener that threadably engages each mounting bracket forming the mounting assembly. Structural members have axial end portions, each releasably coupled to a mounting bracket by the integrally threaded shaft. Axial end portions are threaded in opposite directions for permitting structural member rotation to adjust a length thereof to a substantially zero strain position.