Honeywell International Inc.

Ken E Young

Timothy Hindle

Tim Daniel Barber

Kevin Witwer

Toren S Davis

Emray R Goossen

Kostandin Gjika

Torey Davis

Paul B Talbert

Stella Silvana Dearing

Timothy Barber

Timothy Daniel Barber

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

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.

Two-dimensional vibration isolator

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

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

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

A payload launch lock mechanism includes a base, a preload clamp, a fastener, and a shape memory alloy (SMA) actuator. The preload clamp is configured to releasibly restrain a payload. The fastener extends, along an axis, through the preload clamp and into the base, and supplies a force to the preload clamp sufficient to restrain the payload. The SMA actuator is disposed between the base and the clamp. The SMA actuator is adapted to receive electrical current and is configured, upon receipt of the electrical current, to supply a force that causes the fastener to elongate without fracturing. The preload clamp, in response to the fastener elongation, either rotates or pivots to thereby release the payload.

Payload launch lock mechanism

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.

Launch lock assemblies including axial gap amplification devices and spacecraft isolation systems including the same

Methods and systems are provided for attaching and detaching a payload device to and from, respectively, a gimbal system without requiring use of a mechanical tool. The gimbal system includes a gimbal assembly that includes a payload socket arranged to attach a payload device to the gimbal assembly. The payload socket is preferably arranged to allow any of a plurality of payload devices to attach to and detach from the payload socket without requiring use of a mechanical tool.

Growing community of inventors

Glendale, AZ, United States of America

Ken E Young