Abstract: A microelectromechanical gyroscope comprising a force-feedback circuit with a sideband modulator configured to impart to a mechanical oscillator a modulated force-feedback signal, and a frequency-feedback circuit which receives from the oscillator a modulated sense signal and is configured to keep the phase of the secondary resonant frequency of the oscillator equal to its primary oscillation frequency.

Abstract: A spherical electromagnetic machine includes a spherical stator, a plurality of longitudinal slots, a plurality of latitudinal slots, a plurality of longitudinal coils, a plurality of latitudinal coils, a first hemispherical shell rotor, and a second hemispherical shell rotor. The longitudinal slots and latitudinal slots are formed in, and are spaced evenly around, the outer surface. The longitudinal coils are disposed within a different one of the longitudinal slots. The latitudinal coils are disposed within a different one of the latitudinal slots. The first and second hemispherical shell rotors are mounted for rotation relative to the spherical stator body and have magnets on their inner surfaces. A Lorentz force causes movement of the first and second hemispherical shell rotors when electrical current is supplied to one or more of the longitudinal coils or to one or more of the latitudinal coils.

Abstract: A geared spherical electromagnetic machine with two-axis rotation includes an inner frame, an outer frame, a spherical body, a first coil, a second coil, a third coil, a first hemispherical body, a second hemispherical body, a first plurality of inner magnets, a second plurality of inner magnets, a first gearbox, and a second gearbox.

Abstract: The objective of the present invention is to provide a control moment gyroscope which can be provided in a limited space since the volume thereof can be reduced without change in performance by optimizing the shapes and mounting positions of each component. To this end, the control moment gyroscope of the present invention is a control moment gyroscope for generating torque in the orthogonal directions to both of two shafts which are perpendicularly disposed to each other by rotating the two shafts, and the control moment gyroscope comprises: a gimbal motor formed in a hollow cylinder shape and supplying momentum; spin motor provided inside the gimbal motor and supplying momentum in a perpendicular direction to the momentum of the gimbal motor; and a flywheel provided in the inside of the gimbal motor and supplied with the rotational force of the gimbal motor and the rotational force of the spin motor.

Abstract: An optical waveguide substrate includes: a substrate body in which an optical waveguide is formed; a cable holding part configured to have a cable holding hole into which a signal cable is inserted, the signal cable having one of an incidence part and an emission part that is arranged so as to face the optical waveguide and having a first magnetic part; and a second magnetic part configured to generate a repulsive force in the cable holding hole in association with the first magnetic part.

Abstract: Provided is a means for mitigating strict constraints between a virtual polyhedron inscribed in a rotor and a virtual polyhedron inscribed in a stator of a spherical stepping motor and a spherical AC servo motor and drastically increasing the degree of freedom in design. The above problem is solved by disposing permanent magnets at points of division of the sides of the virtual polyhedron inscribed in the rotor and electromagnets at points of division of the sides of the virtual polyhedron inscribed in the stator.

Abstract: The invention refers to an air supply system (1) for a group of cells (4) arranged for dosing the individual air demand of each electrolytic cell (2) that must be fed to its electrolyte through a system of controlled air diffusion. It comprises a low pressure blower (5), a central feed pipe (6) and a plurality of feed branches (7); a flow meter (8) and a flow regulator (9) are associated to each feed branch. The assembly is connected to a bent hose (12) arranged on the walls of said electrolytic cell (2) to allow connection with an isobaric ring (3), so that the fed air can be diffused homogeneously and sustainedly in time to the electrolyte through selectively perforated hoses (16). The present invention also refers to the process of installation, calibration and operation of the air supply system.

Abstract: A gyroscopic apparatus, having application as prime mover, has a pair, or alternatively multiple pairs, of flywheels disposed opposite one another. A pivot axis of the flywheels lies in a position midway between the flywheels for each pair. Each flywheel has its own separate electric motor or engine. A drive arrangement operates to spin the assembly unit about a second axis, in the same plane, but perpendicular to the flywheel pair axis.

Abstract: A gyroscope device and method are disclosed. An example of the gyroscope device includes a gyroscope element and a frame. A drive element for spinning the gyroscope element which also results in torque on the frame parallel to an axis of rotation of the gyroscope. A first torque application element is mounted on the frame to counter torque produced by the drive element to subsequently restrict the frame from freely rotating in a direction counter to the gyroscope element. A second torque application element imposes a torque on the frame perpendicular to the axis of rotation of the gyroscope element to tilt the axis of the gyroscope and effect direction of motion.

Abstract: A gyroscope device and method are disclosed. An example of the gyroscope device includes a gyroscope element and a frame. A drive element for spinning the gyroscope element which also results in torque on the frame parallel to an axis of rotation of the gyroscope. A first torque application element is mounted on the frame to counter torque produced by the drive element to subsequently restrict the frame from freely rotating in a direction counter to the gyroscope element. A second torque application element imposes a torque on the frame perpendicular to the axis of rotation of the gyroscope element to tilt the axis of the gyroscope and effect direction of motion.

Abstract: Embodiments of control moment gyroscopes (CMGs) are provided, as are embodiments of a method for fabricating CMGs. In one embodiment, a CMG includes a stator housing, an inner gimbal assembly (IGA), and a torque motor coupled to the stator housing and configured to rotate the IGA housing about a gimbal axis to selectively generate a desired output torque during operation of the CMG. The IGA includes, in turn, an IGA support structure housing rotatably coupled to the stator housing, a monolithic CMG rotor rotatably mounted to the IGA support structure housing, and a spin motor coupled to the IGA support structure housing and configured to rotate the monolithic CMG rotor about a spin axis.

Abstract: Embodiments of control moment gyroscopes (CMGs) are provided, as are embodiments of a method for fabricating CMGs. In one embodiment, a CMG includes a stator housing, an inner gimbal assembly (IGA), and a torque motor coupled to the stator housing and configured to rotate the IGA housing about a gimbal axis to selectively generate a desired output torque during operation of the CMG. The IGA includes, in turn, an IGA housing rotatably coupled to the stator housing, a CMG rotor rotatably mounted within the IGA housing, and a spin motor coupled to the IGA housing and configured to rotate the CMG rotor about a spin axis. The CMG rotor includes a rotor shaft, a rotor rim circumscribing the rotor shaft, and a plurality of radially-compliant spokes extending between the rotor shaft and the rotor rim.

Abstract: A gyroscope and a manufacturing method are provided. The gyroscope comprises: a substrate with a bottom driving electrode and a bottom measuring electrode, and a dielectric layer with a sealed cavity comprising: a central axis on the substrate; a support ring on the substrate rotatable around the central axis; a mass ring surrounding and having common central axis with the support ring; cantilevers connected with the support ring and the mass ring and suspend the mass ring in the cavity; elastic components among the support ring, the mass ring and two adjacent cantilevers; a top driving electrode overlaying the support ring, the mass ring, the cantilevers and the elastic components; a conductive plug connected with top driving electrode and bottom driving electrode on the elastic components. The mass ring comprises an insulation layer and a weight layer. Stability and performance of the gyroscope may be improved.

Abstract: Described is a torque amplifying device that is of centrifugal or gyroscopic type and has a unidirectional drive or drives. This device is used to control the body of a controlled object, such as an airplane, helicopter, land vehicle, cargo handling mechanism, earth moving machine or maritime device or vehicle. The torque amplifying devices are designed so that they supply a torque (momentum) to the body of the controlled object where it is connected. Thereby, the orientation or weight distribution of the body is controlled. The orientation is achieved without resorting to the physical properties of the surrounding environment (ground, water or air). Thus, it can apply a torque to this body in pitch, roll and/or yaw, so that it achieves the position or weight distribution the control system is calling for. The duration of the torque can be unlimited, until the conditions that produce it are intentionally changed.

Abstract: A self-contained momentum control system (MCS) for a spacecraft is provided for small satellites. The MCS features a miniaturized gyroscopic rotor with a rotational speed in excess of 20,000 RPM. The MCS includes at least three control moment gyroscopic mechanical assemblies (CMAs) rigidly mounted within a single enclosure, where each CMA mounted in an orientation whereby the longitudinal axis of each CMA is either orthogonal to every other CMA or is parallel to another CMA but in the opposite orientation. In order to further reduce the size of the MCS, an electronics package that is configured to interface command and control signals with and to provide power to the CMAs is included within the MCS enclosure. A plurality of shock isolation devices are used to secure each of the CMAs to the enclosure in order to reduce the launch load upon the CMAs thereby allowing the use of smaller rotor spin bearings. The MCS enclosure surrounding the CMAs and support structure is hermetically sealed.

Abstract: Various embodiments of the present invention include an attitude control system for use with small satellites. According to various embodiments, the system allows rapid retargeting (e.g., high slew rates) and full three-axis attitude control of small satellites using a compact actuation system. In certain embodiments, the compact actuation system includes a plurality of single-gimbaled control moment gyroscopes (SGCMG) arranged in a pyramidal configuration that are disposed within a small satellite.

Abstract: A control moment gyroscope (CMG) is provided for deployment on a spacecraft. The CMG includes a stator housing, an inner gimbal assembly disposed in the stator housing, and a torque motor coupled to the stator housing and at least partially disposed around an intermediate portion of the inner gimbal assembly. The torque motor is configured to rotate the inner gimbal assembly about a gimbal axis.

Abstract: 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.

Abstract: Described is a gyroscope with a vibrating structure, produced by micromachining in a thin wafer, which comprises a movable inertial assembly comprising at least one movable mass able to vibrate in the plane of the wafer along a drive axis x and along a sense axis y roughly perpendicular to the x-axis, an interdigital sensor comb and an interdigital drive comb. It furthermore comprises at least one additional interdigital comb, called the quadrature-error compensation comb, connected to the mass and which has two asymmetric air gaps e and ?e, ? being a positive real number, for subjecting the mass to an adjustable electrostatic stiffness due to coupling between the x-axis and the y-axis by applying a variable DC voltage V to this comb, the adjustable stiffness allowing compensation for the quadrature error of the gyroscope.

Abstract: A gyroscope power starter has a housing having a bottom and a concave head slanted at a predetermined angle relative to the housing, the concave head engaging a gyroscope rotor. An electric power source is mounted on the housing. A motor is rigidly mounted to a housing. The motor is connected to the power source for producing a rotational power in response to a switching force. A power rotor is connected in unity with the motor and protruding from an opening into the concave head of the housing to transmit the rotational motor power to the gyroscope rotor. An alignment member is formed in a concave center area. The alignment member protrudes into a groove of a gyroscopic rotor when the gyroscopic rotor is rotating.

Abstract: The gyrodyne includes an inertial wheel mounted, via a wheel support, on the moving part or rotor of a cardan assembly. The cardan assembly is provided with a stator and the rotor is rotatable with respect to the stator about a first axis of rotation, it being possible for the spinner of the inertial wheel to be set in rotation about a second axis of rotation not aligned with the first axis of rotation. The stator of the cardan is mounted on a block and fixed to this block via an arrangement of vibration attenuators or insulators. The mechanism for setting the rotor in rotation is at least partially housed in the interior volume of the block.

Abstract: A rotational vibration type gyro 1 is provided by which a detection sensitivity influence of the other axis direction on detection sensitivity in a detection axis direction. The rotational vibration type gyro 1 has: a drive weight 4, drive electrodes 3, a detection weight 5 having a pair of X-axis divisional detection weights 5A, 5A and a pair of Y-axis divisional detection weights 5B, 5B, an anchor 6, a pair of X-axis weight support springs 7A, 7A and a pair of Y-axis weight support springs 7B, 7B, a pair of X-axis weight connection springs 8A, 8A and a pair of Y-axis weight connection springs 8B, 8B, and a pair of X-axis detection electrodes 9A, 9A and a pair of Y-axis detection electrodes 9B, 9B.

Abstract: A signal torque module assembly (STMA) is provided for use within a control moment gyroscope of the type that includes a rotor assembly. The STMA comprises a torque module assembly (TMA), which includes: (i) a TMA housing, (ii) a torque motor coupled to the TMA housing, and (iii) a gear train coupled to the TMA housing and mechanically coupling the torque motor to the rotor assembly. A signal module assembly is coupled to the TMA housing, and an elongated connector electrically couples the signal module assembly and the rotor assembly. The elongated connector extends through the gear train.

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: Electric Machines (i.e., electric motors or generators) convert electricity to mechanical work (or vice versa) by applying mechanical power to the shaft of the electric machine or extracting mechanical power form the shaft of the electric machine. This restricts the electrical characteristics, such as frequency or voltage, to the movement of the shaft of the electric machine in accordance to electric machine theory. In some cases, it is desired to perform electromechanical conversion from unorthodox movement, such as pulsating movement, slow movement, or low power movement. In many cases this is not possible with even electronic control without a transmission to convert the mechanical power to a compatible motion.

Abstract: Gyrodyne comprising an inertial wheel mounted, via a wheel support, on the moving part or rotor of a cardan assembly also comprising a stator and means of setting the rotor in rotation with respect to the stator about a first axis of rotation, it being possible for the spinner of said inertial wheel to be set in rotation about a second axis of rotation not aligned with said first axis of rotation, characterized in that said stator of said cardan is mounted on a block and fixed to said block via vibration-damping means, and in that said means of setting said rotor in rotation are at least partially housed in the interior volume of said block.

Abstract: A gimbal is described and which includes a fixed base member defining an axis of rotation; a second member concentrically oriented relative to the axis of rotation; a linear actuator oriented in immediate, adjoining force transmitting relation relative to the base member or to the second member, and which applies force along a linear axis which is tangential to the axis of rotation so as to cause the second member to rotate coaxially relative to the fixed base member; and an object of interest mounted to the second member such that the object of interest is selectively moved relative to the base member about the axis of rotation.

Abstract: A rotor assembly includes a shaft; a mass; and a plurality of adjustable struts. The struts have a first end coupled to the shaft and a second end coupled to the mass such that the mass is movable with respect to the shaft.

Abstract: A gyroscope (10) comprises an outer frame (11); an inner frame (12) positioned inside the outer frame and supported to be movable in one reciprocating direction; a plurality of proof masses (15) positioned inside the inner frame and supported to be movable in the direction orthogonal to the one reciprocating direction; a plurality of outer support suspensions (13) which connect the outer frame and the inner frame; a plurality of inner support suspensions (14) which connect the inner frame and each of the proof masses; actuators (16) for accelerating each of the proof masses; and detectors (17) for detecting displacement of the inner frame against the outer frame. The actuators oscillate the plurality of proof masses in-phase, and wherein Coriolis forces induced on each of the proof masses are summed up in the inner frame.

Abstract: An apparatus in one example has: a first component coupled to a second component by a suspension component; and the suspension component structured to maintain predetermined angular spring rates and to maintain high linear spring rates, that are higher than the angular spring rates, along linear axes of the suspension component that flex under predetermined increased dynamic loading of the suspension component.

Abstract: This invention relates to the use of transmissions in combination with gyroscopically based drive systems. The advantage of which is the ability to modulate the rotor or gyros rotational rate of spin semi autonomously from the precessional rate and effect a greater transfer of power while doing so. In addition the use of a transmission or transmissions helps create a back force in the gyroscopic system which results in a more effective drive.

Abstract: Gyroscope apparatus (100) having a compact size is disclosed herein. The apparatus (100) comprises a flywheel (402) having a centre cavity (401) and being arranged to be rotated about a Z-axis. The apparatus (100) further includes two motors (300, 350) and a gear assembly (200) driven by the two motors and arranged to rotate two shafts (102, 104) disposed along the Z-axis, thus rotating the flywheel about a Y-axis which is orthogonal to the Z-axis. Since flywheel (402) is disposed around the motors (300, 350) and the gear assembly (200), the apparatus can be made very compact.

Abstract: A power starting dock for gyroscope is comprised of an outer housing that has a bottom and a concave head. The head is slanted at an angle relative to the housing, and engages a gyroscope rotor, an electric power source on the housing, a spring-mounted motor on the housing connected to the power source for producing a rotational power in response to a switching force, and a power rotor fastened to the motor and protruding into the concave head of the housing. The power rotor serves to resiliently transmit rotational motor power to the gyroscope rotor.

Abstract: In one embodiment, a micro-gyro device for measuring rotational movement about an input axis includes a driving element generating a driving signal. A MEMS gyro includes a motor rotor and a motor assembly. The motor rotor receives the driving signal and oscillates about a motor axis at a frequency determined as a function of the driving signal. The motor assembly oscillates around a rate axis, which is orthogonal to the motor axis, as a function of the frequency of the motor rotor oscillation. A capacitance of the motor assembly changes as a function of the oscillation of the motor assembly. Driving element feedback circuitry, including a first band-pass filter, is between the motor rotor and the driving element. The driving element feedback circuitry causes the driving element to generate the driving signal as a function of an amplitude of the motor rotor oscillation for maintaining the amplitude of the motor rotor oscillation within a predetermined range.

Abstract: A power starting dock for gyroscope is comprised of an outer housing that has a bottom and a concave head. The head is slanted at an angle relative to the housing, and engages a gyroscope rotor, an electric power source on the housing, a spring-mounted motor on the housing connected to the power source for producing a rotational power in response to a switching force, and a power rotor fastened to the motor and protruding into the concave head of the housing. The power rotor serves to resiliently transmit rotational motor power to the gyroscope rotor.

Abstract: An apparatus for the control and alignment of a sensor on a moving vehicle is provided that includes a gimbal ball supported by an outer axis structure and adapted to pivot about an outer elevation axis and about an outer azimuth axis. The outer axis structure is mounted to a vehicle. An inner axis structure includes a cardan shaft that is provided in the ball and is used to support a payload. An inner elevation axis passes through the cardan shaft. The payload is moved about inner pitch inner roll and inner yaw axes over a limited range of motion by the use of a plurality of permanent magnet wide-gap motors that are disposed on the plane of the cardan shaft and maximally away from the yaw axis in the ball. The motors are adapted to each urge the payload to move in two perpendicular axes, depending upon the current that is applied through conductors which pass through a flux field. Control circuitry is used to energize the motors in any desired combination to produce motion in roll, pitch, or yaw.

Abstract: A precessional device having independent control of the output torque generated by the device and the oscillation race 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, for example, a motor, thereby controlling the oscillation rate of the device independently of the output torque arising front 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: A containment vessel used to enclose an energy storage flywheel system during certification testing of the energy storage flywheel system includes a plurality of concentrically disposed vessels. One or more intermediate shields are freely disposed within an outer shield, and an inner shield is freely disposed within the intermediate shields. The inner shield includes a deflector rim disposed proximate one of its ends that is configured to absorb the energy of ejected material, in the highly unlikely event of a flywheel failure during testing.

Abstract: An apparatus is described which reduces a time delay and a resultant phase shift in a gyroscope motor drive signal. The motor drive signal originates from a numerically controlled oscillator whose output is sampled at a predetermined rate. The apparatus includes a first element which upsamples the oscillator output signal samples and a band pass filter configured to receive an output from the first element and remove spectral components from the output of the first element. The apparatus further includes a third element which generates a tuning parameter, ??o, for tuning of the band pass filter and a scaling multiplier configured to normalize an output of the filter.

Abstract: An apparatus for the control and alignment of a sensor on a moving vehicle is provided that includes a gimbal ball supported by an outer axis structure and adapted to pivot about an outer elevation axis and about an outer azimuth axis. The outer axis structure is mounted to a vehicle. An inner axis structure includes a cardan shaft that is provided in the ball and is used to support a payload. An inner elevation axis passes through the cardan shaft. The payload is moved about inner pitch inner roll and inner yaw axes over a limited range of motion by the use of a plurality of permanent magnet wide-gap motors that are disposed on the plane of the cardan shaft and maximally away from the yaw axis in the ball. The motors are adapted to each urge the payload to move in two perpendicular axes, depending upon the current that is applied through conductors which pass through a flux field. Control circuitry is used to energize the motors in any desired combination to produce motion in roll, pitch, or yaw.

Abstract: An apparatus and a method for controlling the path of oscillatory travel of a device within a two-axis system. A device, such as a camera, is held in a two axis gimbal system having motors for driving the azimuth and pitch axes. A two degree-of-freedom gyroscope is fixed to the case of the device. A first derivative circuit is interposed between a first input port for a loop for controlling device movement with respect to a first axis and a second input port for a loop for controlling device movement with respect to a second axis. Likewise, a second derivative circuit is interposed between the two input ports so that a periodic signal driving with respect to one axis generates a derivative function for driving with respect to the cross-axis. The cross axis signal is scaled to counteract the direct torquing of the gyro rotor that otherwise prevents smooth oscillatory slewing or scanning by the device.

Abstract: The gyroscopic actuator is a new device based on a mechanism designed to make us of the conservation of the kinetic momentum, so that it supplies a torque (momentum) to the platform where it is located. Thus it can orientate this platform in pitching, rolling or yawing, so that it achieves the attitude that a control system requires. Its scheduled use is in aeronautical fields (operation control in aeroplanes), automotion (stabilisation of any type of land vehicle), naval (manoeuvres and stabilisation of naval platforms) and aerospace (satellite attitude control).

Abstract: A gyro torque converter includes an input shaft and an output shaft. The input shaft is fixedly connected to rotate a first drive member. A gimbal is supported by the input shaft. A second drive member is driven by the first drive member. A first shaft is driven by the second drive member. A drive unit is mounted on the first shaft. A second shaft extends from the drive unit. A plurality of gyro members are rotatably mounted on the second shaft.

Abstract: A calculation system for calculating the control signals which are designed to perform a frequency-dependent weighting of the angular velocity signals and the angular position signals. The angular velocity indicators are preferably used for stabilization in a high frequency band while the angular position indicators are suitable for stabilization in a low frequency band. A further calculation system which is designed to perform the frequency-dependent weighting such that the control signals for frequencies below a certain frequency are substantially determined by the angular position signals and the control signals for higher frequencies are substantially determined by the angular velocity signals.

Abstract: An oscillation suppression device comprises a base body to be secured to a ship body, a gimbals secured to the base body, a damper, a flywheel provided in the gimbals, and a motor for rotating the flywheel, etc. The gimbals is supported by bearings built into a pair of side walls of the base body, respectively, such that it can rotate around a first axis. The flywheel can rotate around a second axis. A rotor member of the motor is attached to the flywheel, and a stator member is attached to the gimbals. The rotor member and stator member are located inside the locus-of-rotation of the gimbals. The base body includes a cover portion covering the outer surface of the gimbals.

Abstract: A hybrid wafer gyroscope includes a combination of micro-machined components and traditional electromechanical components to form a miniature gyroscope having a high degree of stability. The gyroscope includes a rotor, gimbal, flexures, and stop cutouts micro-machined out of one or more layers of silicon, forming a unitary, planar, and disk-shaped rotor subassembly, which spins about a drive shaft.

Abstract: A gyro torque converter includes an input shaft and an output shaft. An outer gimbal is supported by the input shaft and the output shaft. An inner gimbal is rotatably mounted within the outer gimbal. The inner gimbal is connected to be rotatably driven by the input shaft. A gyro is rotatably mounted within the inner gimbal.

Abstract: I provide four-dimensional gyroscope with self-action demonstrating the movement of the center of the masses activated by the artificially created non-compensated inertial forces inside it, and which has a lower part and the upper part of the body with the photo-elements forming mass M together with the body of the device; and small masses synchronously rotating in the different directions and creating the rotational inertia; and during the rotation of the small masses, the body of the device, together with the small masses, move translationally along the axis x, creating the translational inertia; and the axis of the rotation of the small masses is fixed on the body, which is moving translationally establishing the connection between the translational and rotational inertia and the accelerating spring and motor-break provide the self-action of the device with the movement of the center of the masses.

Abstract: In a CMG array used to change the attitude of a satellite, noise in the motion of the inner gimbal as it is moved is detected and the speed of the CMG rotors is changed to reduce the noise.

Abstract: A calculation system for calculating the control signals which are designed to perform a frequency-dependent weighting of the angular velocity signals and the angular position signals. The angular velocity indicators are preferably used for stabilization in a high frequency band while the angular position indicators are suitable for stabilization in a low frequency band. A further calculation system which is designed to perform the frequency-dependent weighting such that the control signals for frequencies below a certain frequency are substantially determined by the angular position signals and the control signals for higher frequencies are substantially determined by the angular velocity signals.