Abstract: A vibration control assembly includes a housing having an interior region and an inner mass including a cage disposed within the interior region of the housing and being rotatable within the housing about a first axis and a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis. At least one driving source includes a stator and is operable to interact with a magnetic field of the inner mass to drive rotation of the inner mass about at least one of the first axis and the second axis, wherein the at least one driving source is mounted within the interior region of the housing.

Abstract: A magnetically suspended control moment gyroscope comprising: a gimbal; a flywheel system, set in the gimbal; wherein the flywheel system comprises: a housing; a shaft, arranged in an inner cavity of the housing; a radial magnetic bearing, comprising: a first rotor portion and a first stator portion fixed to the shaft; an upper axial magnetic bearing and a lower axial magnetic bearing, wherein the upper axial magnetic bearing is fixed to an upper end of the first stator portion, the lower axial magnetic bearing is fixed to a lower end of the first stator portion; a wheel body, set in the radial magnetic bearing, fixed to the first rotor portion; an upper axial thrust plate and a lower axial thrust plate, wherein the upper axial thrust plate is fixed to an upper end of the wheel body, and is on an upper end of the upper axial magnetic bearing, the lower axial thrust plate is fixed to a lower end of the wheel body, and is under a lower end of the lower axial magnetic bearing.

Abstract: A gimbal load mounting assembly includes a first seating body. The gimbal load mounting assembly also includes a second seating body configured to slidably connect with the first seating body. The gimbal load mounting assembly also includes an adjustment device. The first seating body is configured to be connected with a supporting frame of a gimbal and is slidable in a first direction. The second seating body is configured to mount a load, and is slidable along the first seating body in a second direction. The adjustment device is provided on one of the first seating body and the second seating body, and is configured to drive the other one of the first seating body and the second seating body to move to adjust relative positions between the first seating body and the second seating body.

Abstract: A gimbal frame comprises at least one guide rod; and a center of gravity adjusting and locking mechanism mounted at the at least one guide rod. The center of gravity adjusting and locking mechanism comprises: a sleeve coupled to the guide rod and capable of moving on the at least one guide rod so as to adjust a center of gravity of the gimbal frame, a moving member disposed at one side of the at least one guide rod and disposed inside the sleeve, and an operating member coupled to the sleeve and in transmission connection with the moving member. When the operating member is operated, the moving member is driven to move towards the at least one guide rod so as to tightly abut against the at least one guide rod.

Abstract: An optical beam steering device is disclosed which includes an optical component for interacting with an optical beam, a gimbal supporting the optical component, a roll cage supporting the gimbal, and a mount that houses and rotatably supports the roll cage. The roll cage and the mount include adjustment features allowing for both linear and angular adjustments of the gimbal and the roll cage.

Abstract: A shock-resisting device includes a snubber that may be selectively moved from a retracted position to an engaged position to selectively create a stiff attachment between a vibration-isolated gimbal of the device, and an outer shell of the device. The gimbal is movable relative to the outer shell. The snubber includes a retainer maintaining the snubber in the retracted position, wherein the snubber is configured to move from the retracted position to the engaged position in response to loss of power to the retainer.

Abstract: A rotating machine comprises a shaft, a casing, at least one main magnetic bearing connected to the shaft for rotatably supporting the shaft inside the casing, at least one auxiliary radial rolling bearing and at least one auxiliary axial rolling bearing which are disposed between the shaft and the casing to respectively support radial loads only and axial loads only.

Abstract: The present invention controls rolling motion of a vehicle by eliminating the detrimental influence of gyro moment on the motion of the vehicle and actively using gyro moment generated by a flywheel constituting an energy storing device. The invention relates to an attitude control device for a vehicle mounted with a flywheel as an energy storage device, the flywheel being pivotally supported about first and second axes mutually orthogonal with each other, the flywheel being mounted on a body of the vehicle such that the first axis extends in a front-rear direction of the body, the attitude control device comprising locking means for locking movement of the flywheel about the first axis, wherein a rolling motion of the vehicle is controlled by locking the movement of the flywheel about the first axis using said locking means.

Abstract: A spherical orienting device includes a base, first and second actuation shafts, an orientable device, an inner member, a middle member, and an outer member. The first and second actuation shafts are rotatably held by the base for rotary actuation about first and second actuation axes, respectively, which intersect orthogonally at a spherical center of rotation. The orientable device is supported by first and second revolute support joints which are disposed for rotation about an orientation axis of the orientable device and a support axis, respectively. The inner member is fixed to the first actuation shaft and linked to the second support joint. The middle member is inwardly linked to the first support joint and outwardly linked to a middle revolute joint disposed for rotation about a linkage axis. The outer member is fixed to the second actuation shaft and linked to the middle revolute joint.

Abstract: The present invention relates to a reusable device for securely holding at least one fragile object against a functional surface solidly fixed to the structure of a satellite or spacecraft during at least one operational phase relating to this satellite, making the objects thus held more accessible and intervention on these objects easier, while at the same time preventing damage to these objects under the effect of sudden accelerations, both during this (these) operational phase(s) and while the hold is being established or while the hold is being released. The device according to the invention is characterized in that it comprises a rigid structure which partially grips this (these) object(s) and which supports at least one fixed jaw and at least one moving jaw substantially facing the fixed jaw(s), the object being immobilized between the fixed jaw and the moving jaw throughout the period of firm holding.

Abstract: The present invention controls rolling motion of a vehicle by eliminating the detrimental influence of gyro moment on the motion of the vehicle and actively using gyro moment generated by a flywheel constituting an energy storing device. The invention relates to an attitude control device for a vehicle mounted with a flywheel as an energy storage device, the flywheel being pivotally supported about first and second axes mutually orthogonal with each other, the flywheel being mounted on a body of the vehicle such that the first axis extends in a front-rear direction of the body, the attitude control device comprising locking means for locking movement of the flywheel about the first axis, wherein a rolling motion of the vehicle is controlled by locking the movement of the flywheel about the first axis using said locking means.

Abstract: A precessional device having independent control of the output torque generated by the device and the oscillation rate of the device is disclosed. The device comprises a rotor supported by an axle wherein the ends of the axle are supported by a circular race. The circular race is rotatable, and may be driven by a motor or other means, thereby controlling the oscillation rate of the device independently of the output torque arising from the rotation rate of the rotor. The motor may be controlled by a control program that adjusts the rotation rate of the circular race to modify the shape of the resistance curve.

Abstract: The present invention relates to a reusable device for securely holding at least one fragile object against a functional surface solidly fixed to the structure of a satellite or spacecraft during at least one operational phase relating to this satellite, making the objects thus held more accessible and intervention on these objects easier, while at the same time preventing damage to these objects under the effect of sudden accelerations, both during this (these) operational phase(s) and while the hold is being established or while the hold is being released. The device according to the invention is characterized in that it comprises a rigid structure which partially grips this (these) object(s) and which supports at least one fixed jaw and at least one moving jaw substantially facing the fixed jaw(s), the object being immobilized between the fixed jaw and the moving jaw throughout the period of firm holding.

Abstract: Methods and apparatus are provided for reorienting control moment gyros (CMGs) to compensate for CMG failure or change in spacecraft (S/C) mass properties or mission. An improved CMG comprises a drive means for rotating the CMG around an axis not parallel to the CMG gimbal axis. Releasable clamps lock the CMG to the spacecraft except during CMG array reorientation. CMGs arrays are combined with attitude sensors, a command module, memory for storing data and programs, CMG drivers and sensors (preferably for each CMG axis), and a controller coupling these elements. The method comprises determining whether a CMG has failed or the S/C properties or mission changed, identifying the working CMGs of the array, determining a new array reorientation for improved spacecraft control, unlocking, reorienting and relocking the CMGs in the array and updating the S/C control parameters for the new array orientation.

Abstract: An energy storage flywheel system includes a flywheel assembly that is rotationally mounted in a housing assembly, and one or more actuator assemblies. The actuator assemblies are configured to selectively engage and disengage the flywheel assembly. When the actuator assemblies engage the flywheel assembly, the actuator assemblies provide support for, and inhibit rotation of, the flywheel assembly. When the actuator assemblies disengage the flywheel assembly, the actuator assemblies no longer support the flywheel assembly, and no longer inhibit its rotation.

Abstract: Provided is a gimbal mechanism comprising a support stand, an outer frame and an inner frame. The support stand includes a spaced pair of L-shaped legs comprising a first member having at least one first slot formed therethrough. The outer frame is nested within the support stand and comprises outer frame sides joined to outer frame ends. Each one of the outer frame sides is pivotally engagable to the first slot of an adjacent one of the first members such that the outer frame is selectively angularly and laterally positionable relative to the support stand. The inner frame is nested within the outer frame and comprises inner frame ends joined to inner frame sides. Each one of the inner frame ends is pivotally engagable to an adjacent one of the outer frame ends such that the inner frame is selectively angularly adjusted relative to the outer frame about an inner frame axis.

Abstract: A mechanical device, comprising: a gyroscopic element (9), (10) constrained to rotate around a central axis (3) and spaced apart therefrom, the gyroscopic element (9), (10) having an axis of rotation and being moveable between a first orientation, in which the axis of rotation thereof passes through or close to the central axis (3), and a second orientation, in which the axis of rotation thereof is substantially perpendicular to the displacement of the gyroscopic element form the central axis (3).

Abstract: A passive caging system for use in gyro-stabilized sensor platforms and the like, employing a pneumatic dashpot in place of automatic caging gyro brakes, pin-locking devices, springs, fluid damped pistons, or air bladders. A pneumatic dashpot in combination with a normally closed solenoid valve provides effective damping of shock forces while the system is in the unpowered state. When power is applied to the system, the solenoid valve is open and unrestricted movement of the sensor platform is enabled.