Abstract: Centrifugal gyroscopic devices are described herein. A representative device can include a shaft, an arm coupled to the shaft, a rotor coupled to the arm, and a control system operably coupled to the shaft, the arm, and/or the rotor. The shaft is rotatable about a first axis and the arm is configured to rotate with the shaft. The arm is pivotable about a second axis and the rotor is configured to pivot with the arm about the second axis. The rotor is further pivotable about a third axis. The control system is configured to bring the shaft, the arm, and the rotor into a resonant mode in which the shaft rotates at a rotational rate, the arm oscillates about the second axis at a first frequency substantially equal to the rotational rate, and the rotor oscillates about the third axis at a second frequency substantially equal to the first frequency.

Abstract: A gyroscopic roll stabilizer comprises a gimbal having a support frame and enclosure configured to maintain a below-ambient pressure, a flywheel assembly including a flywheel and flywheel shaft, one or more bearings for rotatably mounting the flywheel inside the enclosure, a motor for rotating the flywheel, and bearing cooling system for cooling the bearings supporting the flywheel. For smaller units, the bearing cooling system is effective to enable a flywheel with a moment of inertia less than 40,000 lb in2 to be accelerated at a rate of 5 rpm/s or greater. For larger units, the bearing cooling system is effective to enable a flywheel with a moment of inertia greater than 40,000 lb in2 to be accelerated at a rate of 2.5 rpm/s or greater.

Abstract: A gyroscopic roll stabilizer comprises a gimbal having a support frame and enclosure configured to maintain a below-ambient pressure, a flywheel assembly including a flywheel and flywheel shaft, one or more bearings for rotatably mounting the flywheel inside the enclosure, a motor for rotating the flywheel, and bearing cooling system for cooling the bearings supporting the flywheel. For smaller units, the bearing cooling system is effective to enable a flywheel with a moment of inertia less than 40,000 lb in2 to be accelerated at a rate of 5 rpm/s or greater. For larger units, the bearing cooling system is effective to enable a flywheel with a moment of inertia greater than 40,000 lb in2 to be accelerated at a rate of 2.5 rpm/s or greater.

Abstract: This invention discloses an inertial-thruster architecture wherein active and passive damping techniques result in the redirection, absorption, neutralization, and/or enhancement of the effect of torque-induced precession on both oscillatory and rotary devices. These novel mechanical and methodological embodiments demonstrate that the redirection of precession during the appropriate phase of operations will achieve the objective of rectilinear movement when combined with the displacement of one or more precessable masses.

Abstract: A free-space force feedback system that can be mounted to an input/output device so as to enable its operator complete ambulatory movement is provided. The input/output device may determine operator position, motion and torque (input) so that said device can interactively impart a command torque vector force (output) so as to provide from one to six degrees of freedom and highly realistic force feedback to an operator of the input/output device. The force feedback may be imparted by at least one orthogonally oriented MACSD (Multiple Axis Counter Spinning Disk), wherein MACSD may be mounted to the input/output device, thereby coupling reaction forces to the operator so that only the desired forces (command torque vectors) are felt without the need for connection to a fixed frame.

Abstract: In a method for driving stabilization of a motorized two-wheeled vehicle, in which two gyroscopes situated side-by-side are present having axes of rotation in parallel to each other, the gyroscopes each being tiltable about a tilting axis perpendicular to the axis of rotation, and the tilting axes of the two gyroscopes also being parallel to each other, the gyroscopes rotating about their axes of rotation in directions of rotation opposite to each other, and in the case of a detected unstable driving behavior of the two-wheeled vehicle, the two rotating gyroscopes are tilted about their respective tilting axis at a first angular velocity, the tilting directions being counter to each other; and the two gyroscopes are subsequently tilted back again at a second angular velocity about their respective tilting axis into their original orientation.

Abstract: An apparatus for assisting the balance of a user is disclosed herein. The apparatus includes a first control moment gyroscope (CMG) and a second CMG configured as a scissor pair. The first CMG includes a first flywheel and a second flywheel, a first motor that rotates the first and second flywheels, a first gimbal supporting the first and second flywheel, and a first gimbal servo to rotate the first gimbal. The second CMG includes a third flywheel and a forth flywheel, a second motor that rotates the third and fourth flywheels, a second gimbal supporting the third and fourth flywheels, and a second gimbal servo to rotate the second gimbal. The apparatus additionally includes a gyroscope controller controlling the first gimbal servo and the second gimbal servo.

Abstract: Three spinning ring rotors, functioning as concentric ring gyro motors, are angled at ninety degrees with respect to one another and are arranged in an orthogonal association inside a substantially spherical housing that includes a central hub with a plurality of spokes attached to the spherical housing with holes for the spokes and coils used for steering. The mass distribution for the rings is such that the rotating ring masses are maximized and the containing mass is minimized. There is minimum friction for the primary rotation of the spinning ring rotors with all other angular forces translated across the containment structures uniformly. These spinning masses remain equal, unless the influence of precisely controlled and oriented destabilizing steering coils are used to disrupt the stability of one or more rotors by placing a controllable and varying magnetic field, from weak to strong, parallel to the axis of the spinning rotors.

Abstract: The embodiment herein generally relates to a system to apply moments to a user, particularly during gait. The system is a portable gyroscopic-assisted system, mounted on a user's body, particularly the upper body, particularly to influence orientation of users having difficulty with balancing during gait. The system comprises a plurality of variable-speed control moment gyroscopes (VSCMGs). The VSCMGs generate moments, particularly to counteract a fall to any direction. The VSCMGs are placed close to the center of mass of the user. The couple moments of the VSCMGs are transmitted to the user through a support structure that is tightly attached to the user. Particularly, the system controls moments based on detecting pre-fall conditions.

Abstract: Disclosed is a combination of six substantially identical interconnected rotating masses, with a pair each of the rotating masses being configured to rotate in one of each of the three planes (X, Y, and Z). Regardless of the orientation of the six masses, each pair of the six interconnected rotating masses may share substantially the same center of gravity and generate a separate yet interactive kinetic energy and angular momentum in each of the three planes, thereby providing resistance to rotational forces from external sources. This is known as “equal force presence.” In one embodiment, the rotating masses are ring-like masses. In alternative embodiment, the rotating masses are solid masses, similar to flywheels.

Abstract: A vehicle stabilizing means comprising a cradle (23) supported from a mounting (17) to lie to one side of the mounting, a rotor (19) supported from the cradle between a pair of spaced supports (25) to be rotatably supported by the supports, a drive coupled to the rotor enabling the rotor to rotate at a substantially constant angular velocity, the rotor being rotatable about a first axis, the supports located to the side of the cradle remote from the mounting, the cradle further comprises a base (31) which is rotatably supported from the mounting to be rotatable around a second axis which is perpendicular to the first axis of rotation of the rotor and which intersects the first axis of the rotor, the mounting intended in use to be fixed to the vehicle such that in operation the mean orientation of the first and second axes are substantially perpendicular to the direction of the axis of stabilization.

Abstract: The mechanical output power of a turbine engine can be electrically boosted by using a power control system which may include a power source, an electric machine, a prime mover coupled to the electric machine, and a power control module coupled to the power source and the electric machine. The power control module may be configured to operate the electric machine between a motoring mode driving a mechanical load and a generator mode supplying power to an electrical load at speeds normally associated with generating modes only.

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: Disclosed is a combination of six substantially identical interconnected rotating masses, with a pair each of the rotating masses being configured to rotate in one of each of the three planes (X, Y, and Z). Regardless of the orientation of the six masses, each pair of the six interconnected rotating masses may share substantially the same center of gravity and generate a separate yet interactive kinetic energy and angular momentum in each of the three planes, thereby providing resistance to rotational forces from external sources. This is known as “equal force presence.” In one embodiment, the rotating masses are ring-like masses. In alternative embodiment, the rotating masses are solid masses, similar to flywheels.

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: A torque converter comprises a stationary mount, input and output shafts, a primary frame (301) supported by the stationary mount for rotation about a primary axis and coupled for rotation with one of the input and output shafts (302,303), a secondary frame (50) supported by the primary frame (301) for rotation about a secondary axis perpendicular to the primary axis and coupled for rotation with the other of the input and output shafts, a plurality of flywheels (10) supported by the secondary frame (50) with their spin axes disposed at an angle to one another in the same plane, or in mutually parallel planes, and torsional springs acting between the flywheels and the secondary frame to cause the flywheels to oscillate in use, so as to effect a gyroscopic torque coupling between the primary and secondary frames.

Abstract: Disclosed is a combination of six substantially identical interconnected rotating masses, with a pair each of the rotating masses being configured to rotate in one of each of the three planes (X, Y, and Z). Regardless of the orientation of the six masses, each pair of the six interconnected rotating masses may share substantially the same center of gravity and generate a separate yet interactive kinetic energy and angular momentum in each of the three planes, thereby providing resistance to rotational forces from external sources. This is known as “equal force presence. In one embodiment, the rotating masses are ring-like masses. In alternative embodiment, the rotating masses are solid masses, similar to flywheels.

Abstract: A propulsion system includes an engine and a rotating member rotatably engaging the engine. The rotating member comprises a plurality of drive members positioned around the circumference of the rotating member. Each of the drive members has an unlocked state in which the drive members apply substantially no torque to the rotating member, and a locked state, in which the drive members apply substantially a torque to the rotating member. At a selected time, a first set of the drive members are in the unlocked state and a second set of the drive members are in the locked state to provide a propulsive force.

Abstract: Gimbal power systems and methods are operable to provide power to a device attached to the gimbal. An exemplary embodiment is configured to rotate a rotational member of the gimbal system about an axis, wherein a stator of a rotary power transformer affixed to the rotational member rotates about the axis, and wherein an end of an electrical connection coupled to a power connector of a rotor winding of the rotary power transformer remains substantially stationary as the stator of the rotary power transformer rotates about the axis.

Abstract: A method of operating an anti-phase six degree-of-freedom tuning fork gyroscope system comprises the steps of driving a first three degree-of-freedom gyroscope subsystem, and driving a second three degree-of freedom gyroscope subsystem in an anti-phase mode with the first gyroscope subsystem at an anti-phase resonant frequency. Acceleration or an angular rate of motion is sensed by means of the first and second three degree-of-freedom gyroscope subsystems operating in a flat frequency response range where the anti-phase resonant frequency is designed. Response gain and phase are stable and environmental and fabrication perturbations are avoided by such operation. A anti-phase six degree-of-freedom tuning fork gyroscope system which operates as described is also characterized.

Abstract: The present invention provides a thrust generator capable of generating thrust without using reaction of a combustion product, and a navigation body utilizing the same. The thrust generator has a rotation axis, a plurality of tops arranged symmetrically around the rotation axis, and a motor device for rotating the tops around the rotation axis. The spinning axis of the top is arranged along the radial direction of the rotation axis. The “top” generates a force by which it rises perpendicularly from the ground, that is, so-called couple of forces. By using the couple of forces, thrust is generated.

Abstract: A disturbance-cancellation system and method is provided that facilitates the adaptive cancellation of periodic disturbances. The disturbance-cancellation system and method includes a pair of control moment gyroscopes (CMGs) arranged together as a scissored pair. The scissored pair of CMGs is used to create a periodic torque with a controllable amplitude and frequency. The periodic torque created by the CMGs is adaptively controlled to cancel out periodic disturbances in the system. The system and method creates a periodic torque with a controllable amplitude and frequency by rotating the inner-gimbal assemblies of the CMGs in opposite directions at substantially equal phase and angular velocity. Amplitude matching can be achieved by adjusting the rotor spin rate. The steady-state constant motion results in a periodic torque along the output axis of the scissored pair, while components of torque along axes orthogonal to this one cancel out.

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: The present invention is a combination of three interconnected gyroscopic ring-like rotating masses, with each of the three ring-like masses rotating in a separate plane. Each of the three interconnected rotating masses will share substantially the same center of gravity and generate a separate yet interactive kinetic energy and angular momentum in each of the three planes, thereby providing resistance to rotational forces from external sources.

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: 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.