Honeywell International Inc.

Lockheed Martin Corporation

Timothy Hindle

Ken E Young

Tim Daniel Barber

Toren S Davis

Dale Thomas Ruebsamen

Brian H Hamilton

Paul Buchele

Ryan Goold

Steven Hadden

Torey Davis

Neil Evan Goodzeit

Harald Juergen Weigl

James H Boyd

Robert E Winkel

Brett McMickell

Paul B Talbert

Louis R Jackson

Kostandin Gjika

Michael Brett McMickell

Stella Silvana Dearing

Kevin Witwer

Timothy Daniel Barber

Dylan Jaksich

James R Boyd

Timothy Barber

A vehicle includes a vehicle body, a vehicle power source, and an actuator. The vehicle power source includes a housing and a power generator. The housing is rotationally mounted on the vehicle body and is configured to rotate, relative to the vehicle body, about a first rotational axis. The power generator is rotationally mounted within the housing and is configured to rotate about a second rotational axis and generate power. The first rotational axis and the second rotational axis are orthogonally disposed. The actuator is coupled to the housing and is operable to selectively rotate the housing about the first rotational axis. By gimballing the rotating mass of the power source a gyroscopic torque can be applied to the vehicle improving its maneuverability.

Dual-purpose control moment gyroscope for vehicle control

A launch lock system includes a first portion rigidly coupled to the second portion in a first state and the first portion movable in all directions relative to the second portion in a second state. The launch lock system includes a fastener subassembly coupled to the second portion, and the fastener subassembly is movable relative to the second portion from a first position to a second position. The launch lock system includes at least one pivot arm subassembly having a pivot arm movable between a first position and a second position. The pivot arm is coupled to the first portion in the first position. In the first state, the pivot arm is in the first position and cooperates with the fastener subassembly in the first position, and in the second state, the pivot arm is uncoupled from the first portion and the fastener subassembly.

Launch lock system with increased release clearance in all directions

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.

Damping coefficient-regulating inductive heating systems and isolator assemblies including the same

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.

Three parameter isolators containing rolling seal damper assemblies

A turbocharger system can include a housing that includes a bore defined at least in part by a bore wall; a rolling element bearing unit that includes an outer race; and a mixed-element damper assembly disposed at least in part between the outer race and the bore wall where the mixed-element damper assembly includes a lobed-spring element and a squeeze film damper element.

Turbocharger bearing damper assembly

Embodiments of isolators, such as three parameter isolators, including a main spring linear guide system are provided. In one embodiment, the isolator includes first and second opposing end portions, a main spring mechanically coupled between the first and second end portions, and a linear guide system extending from the first end portion, across the main spring, and toward the second end portion. The linear guide system expands and contracts in conjunction with deflection of the main spring along the working axis, while restricting displacement and rotation of the main spring along first and second axes orthogonal to the working axis.

Isolators including main spring linear guide systems

An apparatus is provided for vibration damping and isolation. The apparatus includes a housing having an inner surface defining a passage therethrough, a first bellows disposed within the housing passage, the first bellows having an outer surface and spaced apart from the housing inner surface to define a first chamber having a volume, and a second bellows disposed within the housing passage, the second bellows having an outer surface and spaced apart from the housing inner surface to define a second chamber having a volume. The apparatus further includes a restrictive flow passage in fluid communication with the first and second chambers, fluid disposed within the first chamber, the second chamber, and the restrictive flow passage, and a shaft positioned externally to the housing and coupled with the first bellows and the second bellows. The shaft is configured to selectively receive a force to thereby move the fluid through the restrictive flow passage to increase the first chamber volume and decrease the second chamber volume or to decrease the first chamber volume and increase the second chamber volume.

Vibration isolator using externally pressurized sealing bellows and an external shaft

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.

Launch lock assemblies with reduced preload and spacecraft isolation systems including the same

Embodiments of a vibration isolation system are provided. In one embodiment, the vibration isolation system includes a first isolator having opposing mounting interfaces, a tuning spring disposed between the opposing mounting interfaces, and a piezoelectric actuator disposed between the opposing mounting interfaces and coupled in series with the tuning spring, as taken along a first load path through the first isolator. A controller is operably coupled to the piezoelectric actuator. During operation of the isolation system, the controller varies a control voltage supplied to the piezoelectric actuator to dampen vibrations transmitted through the first load path.

Vibration isolation systems including multi-parameter isolators providing piezoelectric-based damping

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. Structural members may be vibration isolator struts in vibration isolation systems.

Mounting systems for structural members, fastening assemblies thereof, and vibration isolation systems including the same

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.

Fluid dampers having temperature-dependent viscosity compensation and auxiliary power unit inlet systems employing the same

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.

Annular bearing support dampers, gas turbine engines including the same, and methods for the manufacture thereof

Gas turbine engine, broadband damping systems, and methods for producing broadband-damped gas turbine engine are provided. In one embodiment, the gas turbine engine includes an engine case, a rotor assembly mounted within the engine case for rotation about a rotational axis, and a broadband damping system disposed between the rotor assembly and the engine case. The broadband damping system includes a first set of three parameter axial dampers angularly spaced around the rotational axis, and a second set of three parameter axial dampers angularly spaced around the rotational axis and coupled in parallel with the first set of three parameter axial dampers. The first and second sets of three parameter axial dampers are tuned to provide peak damping at different rotational frequencies to increase the damping bandwidth of the broadband damping system during operation of the gas turbine engine.

Gas turbine engines including broadband damping systems and methods for producing the same

In an embodiment, and by way of example only, a vibration isolator is used for coupling between a payload and a base and includes a rod, a magnetic damper, a first spring, and a second spring. The magnetic damper includes a movable section and stationary section. The movable section comprises a conductive material and has an opening through which the rod extends. The stationary section includes a magnet disposed around and spaced apart from the movable section and is coupled to the base. The first spring couples the movable section to the rod. The second spring is coupled to the rod and stationary section. In another embodiment, the vibration isolator also includes a voice coil actuation system.

Vibration isolators and isolation systems

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.

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Peoria, AZ, United States of America

Timothy Hindle