Honeywell International Inc.

Honeywell G.m.b.h.

Sperry Corporation

Dennis Wayne Smith

Peter E Jacobson

Theodis Johnson

Toren S Davis

Paul Buchele

Lawrence P Davis

Carlos J Stevens

Terry S Allen

Robert E Winkel

Steven Hadden

Gary L Gisler

Porter Davis

Stephen Edward Fiske

James T Hanks

Edward F Silvent

Roger Nagel

Mark H Warner

Hugh B Matthews, Sr

Embodiments of a thermally-conductive vibration isolator are provided, as are embodiments of a spacecraft isolation employing a plurality of thermally-conductive vibration isolators. In one embodiment, the thermally-conductive vibration isolator includes a first end portion, a second end portion substantially opposite the first end portion, and first and second load transfer paths from the first end portion to the second end portion. The first and second load transfer paths comprise a main spring and a damper in parallel with the main spring, respectively. An elongated thermal conduit, which has a thermal conductivity exceeding that of first load transfer path and the second load transfer path, extends from the first end portion to the second end portion.

Thermally-conductive vibration isolators and spacecraft isolation systems employing the same

A method and apparatus for controlling the preload of duplex rolling element bearings systems under various temperatures is described. A spacer or a plurality of spacers may be located adjacent to the rings of the duplex rolling element bearings. The spacer or spacers may be heated or cooled to increase or decrease the axial dimension of the spacer or spacers. Changing the axial dimension of the spacers changes the preload of the duplex rolling element bearing system. The preload of the system may be estimated by receiving an input from a sensor or sensors located on the duplex rolling element bearings system. The sensor may be a temperature sensor or a force transducer.

Active preload control for rolling element bearings

A rotor assembly is provided for deployment within the inner gimbal assembly of a control moment gyroscope (CMG). In one embodiment, the rotor assembly includes a rotor shell, a rotor shaft fixedly coupled to the rotor shell, and a rotor rim. The rotor rim includes an annular body and a strain relief member. A first end portion of the strain relief member is fixedly coupled to the annular body, and a second end portion of the strain relief member is fixedly coupled to the rotor shell to form a rim-shell joinder interface. The strain relief member has a flexibility sufficient to reduce the mechanical stress experienced by the rim-shell joinder interface during operation of the CMG.

Rotor assembly including strain relief feature

A control moment gyroscope (CMG) is provided for deployment on a spacecraft. The CMG includes an inner gimbal assembly (IGA), which, in turn, includes an IGA housing, a rotor rotatably coupled to the IGA housing, and a spin motor coupled to the IGA housing and configured to rotate the rotor about a spin axis. The CMG further comprises a stator assembly, which includes: (i) a stator assembly housing rotatably coupled to the IGA housing, and (ii) a torque module assembly coupled to the stator assembly housing and configured to rotate the IGA about a gimbal axis. A gimbal bearing is disposed between the IGA housing and the stator assembly housing. The gimbal bearing resides between the spin axis and the torque module assembly such that the distance between the gimbal bearing and the spin axis is less than the distance between the gimbal bearing and the torque module assembly.

Control moment gyroscope

Methods and apparatus are provided for rapidly moving a filter into and out of an optical beam. A shuttle carries the filter at a first end and first and second spaced apart pieces of magnetic material near the other end. A low friction guide-way supports the shuttle. A base supports the guide-way and a third magnetic piece and coil between the first and second pieces. When the shuttle is IN the first and third pieces form a first magnetic latch to releasably hold it IN and when the shuttle is OUT the second and third pieces form a second magnetic latch to releasably hold it OUT. Spring(s) between the shuttle and the base store energy when the shuttle is IN or OUT. Activating the coil weakens the magnetic attraction between the latch pieces, freeing the shuttle to move, driven by the spring(s) to the opposite OUT or IN position.

Fast insertion means and method

Method and apparatus are provided for reducing vibration in bearings. There are provided first and second bearing rings with races, rotating members rollingly engaging both first and second bearing races, a cage for aligning the rotating members between the first and second bearing races, and vibration reduction means coupled to the cage. The vibration reduction means preferably comprises one or more resonant spring-mass combinations mounted in or on the cage. Damping means is preferably included with the resonant spring-mass combinations. The resonant frequencies of the unmodified bearing cage are first determined and then the spring-mass combinations tuned so that the spring-mass combinations when attached to the cage absorb vibrational energy that would otherwise excite cage vibrations. By selecting the type of spring-mass combination different vibrational modes can be suppressed and/or controlled.

Damped bearing cage

An apparatus and method for selecting an appropriate viscous fluid for use in control moment gyroscopes, reaction wheels, momentum wheels and the like. Components such as the housing, the rotor, and the viscous fluid are modeled using a three-parameter isolator system, which allows optimization of the damping action for a given application.

Methods and apparatus for tuned axial damping in rotating machinery with floating bearing cartridge

A switch assembly includes an arm assembly, a primary spring, one or more secondary springs, and a latch assembly. The arm assembly is configured to rotate between at least a first rotational position and a second rotational position. The primary spring is coupled to the arm assembly and is configured to bias the arm assembly toward a third rotational position that is located between the first and second rotational positions. Each secondary spring is disposed in the switch assembly and is configured to selectively bias the arm assembly toward the third rotational position when the arm assembly reaches a predetermined rotational distance from either the first or second rotational positions. The latch assembly is disposed in the switch assembly and is operable to selectively hold the arm assembly in either the first or second rotational positions, and to selectively release the arm assembly from the rotational position in which it is holding the arm assembly.

Non-linear spring force switch assembly

A signal transfer assembly that is configured to transfer one or more electrical signals between two or more conductive paths that are rotating relative to one another includes two substrates or more substrates and one or more interface assemblies. The substrates each include one or more conductors on one or more surfaces. Each interface assembly is disposed between two substrates and is configured to allow relative rotation between the two substrates. Each interface assembly also electrically couples selected ones of the conductors on each of the substrates together, thereby allowing electrical signals to pass through the assembly.

Relative rotation signal transfer assembly

Disclosed is a bearing assembly with thermal compensation. The bearing assembly includes a bearing mechanism defined by a pair of races and a plurality of bearing elements. The races are manufactured from a material having a coefficient of thermal expansion that is substantially different than the coefficient of thermal expansion of the material from which the bearing elements are manufactured. A thermal compensation mechanism of the bearing assembly is contiguous with the races. The thermal compensation mechanism permits movement of the races relative to the bearing elements in a direction parallel the rotational axis of the bearing mechanism as a result of the effect of temperature variations on the materials of the races and bearing elements.

Hybrid duplex bearing assembly having thermal compensation

A system is disclosed for supplying a lubricant to a bearing assembly, such as that in a gyroscope of a spacecraft. The system includes a housing which is connected to the bearing assembly and which forms a pressurized chamber. A collapsible member, such as a bellows, in the pressurized chamber houses a supply of lubricant. One or more valves regulate and control the flow of lubricant from the collapsible member to the bearing assembly. In response to the actuation of the valves, flow of lubricant is caused by pressure exerted on the collapsible member. Lubricant flow conduits may also be formed within the housing, so that lubricant may be provided directly to a portion of the bearing assembly.

Gas pressurized oil replenishment system for bearing assemblies

A control moment gyroscope including a rotor extending along a rotor axis. The rotor includes a first and second rotor end. A gimbal housing includes a magnetic suspension system for magnetically suspending the rotor within the gimbal housing to allow rotation of the rotor about the rotor axis. A first and second conical clutch positioned adjacent to the first and second rotor end, respectively, and connected to the gimbal housing couples the rotor to the gimbal housing if the magnetic suspension system is inoperative. The gyroscope also includes an apparatus for forcing the first and second clutches to couple the rotor to the gimbal housing.

Touchdown and launch-lock apparatus for magnetically suspended control

A lubricating film thickness measuring system and method includes a rolling element bearing having a relatively rotatable electrically insulated inner and outer races forming a raceway therebetween. Rolling elements are movably mounted in the raceway. Apparatus is provided for measuring capacitance across the bearing. The measuring apparatus includes an oscillator circuit and a phase detection circuit and is responsive to a phase angle shift between a first signal going from an oscillator circuit to the bearing and from the bearing to the phase detection circuit, and a second signal received by the phase detection circuit directly from the oscillator circuit. The method involves applying a predetermined electrical signal across the rolling elements and measuring the capacitance across the rolling elements thereby providing a measure of the lubricating film thickness.

Lubrication film thickness measuring system and method

The lubrication insertions system of the present invention inserts lubricating oil into the critical areas of a bearing. The system comprises a delivery element for delivering lubricating oil to a predetermined point relative to the bearing. The bearing, which is rotating, causes the lubricating oil to be slung outward of the spin axis of the bearing. A cage element, having a lip that extends beyond the edge of the bearing, captures the lubricating oil and directs the lubricating oil into the bearing to the outer race of the bearing and to the rolling elements of the bearing, which track the oil to the inner race of the bearing.

Lubrication insertion system

A rotating, conductive, heat transfer device is provided. The device includes an outer race having an axis, an inner race coaxial with the outer race, and a plurality of bearing balls disposed in a radial direction between the inner race and the outer race. The device also includes a plurality of separators disposed alternately in a peripheral direction between the bearing balls. The device has a first track and a second track, supported by the inner race, for supporting the separators. The inner race has a first, fixed, inner ring portion with a first bearing surface, and has a second, separable, inner ring portion with a second bearing surface. The outer race has a third bearing surface, disposed in a radial direction opposite to the first bearing surface. The outer race also has a fourth bearing surface, disposed in a radial direction opposite to the second bearing surface. The first and second and third and fourth bearing surfaces are in contact with a spherical surface of each bearing ball. The device also has a plurality of coil springs, which urge the second inner ring portion in an axial direction toward the first inner ring portion, thereby applying first and second and third and fourth forces normal to the respective first and second and third and fourth bearing surfaces, for providing heat conduction from one race to the other race.

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Phoenix, AZ, United States of America

Dennis Wayne Smith