Abstract: A payload stabilizer and methods for stabilizing a payload suitable for use with video camera payloads. The support and stabilizing apparatus has a gimbal having two or more mutually perpendicular axes about which motion is generated by at least two of a pan motor, a tilt motor and a roll motor wherein the pan motor is integral to the gimbal handle and surrounds the main post. The stabilizer has a feedback system providing supplemental torques to the payload through a gimbal.

Abstract: Apparatus and associated methods relate to torque amplifiers. In an illustrative example, prime movers may be disposed radially to and orbiting about a central axis. Each prime mover, for example, may include a rotor coupled to the central axis by planetary gearing such that a torque generated by the rotor is transmitted to the central axis via the planetary gearing. Each prime mover may, for example, include a stator and a counter-torque anchor coupled to the stator and suspended by the central axis such that the counter-torque anchor generates a counter-torque on the stator such that the torque of the rotor and the corresponding counter-torque additively generate work relative to the central axis. Various embodiments may advantageously increase a power output of the torque amplifier relative to a power supplied by the prime movers.

Abstract: A method and system for providing gyroscope bias self-calibration are described herein. The method comprises powering on one or more gyroscopes; after a predetermined first period of time, and upon determining that the one or more gyroscopes is stationary, measuring input rates of rotation during a predetermined second period of time; and determining an average rate of rotation for each gyroscope channel based upon the measured input rates of rotation during the predetermined second period of time. After determining the average rate of rotation and after the predetermined second period of time, the method further comprises commencing additional measurements by the one or more gyroscopes; determining calibrated gyroscope measurements by subtracting the average rate of rotation from each of the additional measurements; and providing, at the output of the one or more gyroscopes, the calibrated gyroscope measurements.

Abstract: Disclosed are devices, system, and method for mitigating wind damage to satellite antennas and for reducing the amount of ballast required to secure the satellite antennas. The device, system, and method include a mast on which an antenna may be affixed, a pivot gear capable of rotating between two or more positions, and a tension force or retention force on the pivot gear. A load force applied to the antenna creates a risk of damage proportional to the load force. The antenna system is capable of transitioning from a first orientation into a second orientation when the load force exceeds tension force or retention force, or the sum thereof, such that the antenna system experiences a reduced load force and therefore a reduced risk of damage. The device, system, and method also reduce the amount of ballast required to secure a non-penetrating antenna installation against tipping or sliding.

Abstract: In one embodiment of the present disclosure, a pan/tilt assembly for an antenna apparatus having a housing enclosing antenna components and a leg extending from the housing includes a first actuator for rotating a first gear, a second actuator for rotating a second gear, a third gear coupled to the leg and engaged by the first and second gears, and a tee having a first portion substantially transverse to a second portion, wherein the first portion has a first end rotatably received within the first gear and a second end rotatably received within the second gear, and wherein the second portion is rotatably received within the third gear.

Abstract: An inertia detection device includes one set of gyro sensors for detecting an angular velocity of a detection target object along a same direction, the gyro sensors arranged in a same physical quantity range, in which sensor movement is detectable as a same physical quantity. When an abnormality affecting an output signal of one of the gyro sensors is caused, based on an observation that a difference of magnitudes of the output signals from normal and abnormal gyro sensors is different from a difference of magnitudes of the output signals from two normal gyro sensors, such an abnormality of one of the gyro sensors is determinable by a comparison between the output signals, without using an estimated value thereof.

Abstract: An inertial navigation system includes a first inertial measurement unit with at least a first sensor and a second inertial measurement unit with at least a second sensor corresponding in type to the first sensor. The first inertial measurement unit is rotatably mounted relative to the second inertial measurement unit, The inertial navigation system further include a controller arranged to: acquire a first set of measurements simultaneously from both the first inertial measurement unit and the second inertial measurement unit; rotate the first inertial measurement unit relative to the second inertial measurement unit; acquire a second set of measurements simultaneously from both the first inertial measurement unit and the second inertial measurement unit; and calculate from the first set of measurements and the second set of measurements at least one error characteristic of the first sensor and/or the second sensor.

Abstract: A rotary damper includes a rotating input member rotating about a rotation axis; a first cylinder and a second cylinder coaxially arranged on opposite sides of the rotation axis; a first and a second pistons slidable inside the first and second cylinders and defining a first and a second working chambers containing incompressible working fluids, respectively; motion conversion mechanisms converting the rotary motion of the rotating input member about the rotation axis into reciprocating motion of the first and second pistons; a third cylinder; a fourth cylinder; and a third and fourth pistons, slidable inside the third and fourth cylinders, respectively and separating the inner volume of the respective cylinder into a respective main chamber in fluid communication with the first working chamber and auxiliary chambers; and the second working chamber and auxiliary chambers respectively.

Abstract: The disclosure relates to a method and apparatus of rotating mass attitude control. The method and apparatus entails rotating a mass to generate thrust. Varying the speed and direction of rotation provides some control of the magnitude and direction of the thrust generated. The method and apparatus of the invention pertinent to an attitude control system for spacecrafts or astromotive vehicles under conditions of zero to low gravity and atmosphere.

Abstract: The present invention relates to: a posture control device for controlling the posture of a robot by means of a thruster; and a robot having the same. The posture control device, according to the present invention, comprises: a thruster for generating a propulsive force for supporting or hauling the load of a robot part; and a rotation mechanism installed between the robot part and the thruster so as to enable the robot part to rotate with respect to thruster or the thruster to rotate with respect to the robot part, wherein the rotation mechanism has at least two axes of rotation, wherein the axes of rotation respectively form a right angle. In addition, the robot, according to the present invention, comprises parts having the posture control device provided thereto, and may comprise: a first part and a second part having the posture control device provided thereto; and a bendable or extendable third part for connecting the first part and the second part.

Abstract: A stabilizing mounting apparatus coupled to a camera to enhance image quality captured by the camera is provided. The mounting apparatus absorbs undesirable movement resulting from travel on an uneven terrain to maintain the camera in a stable position. The apparatus includes a base frame assembly having a plurality of bars coupled together, a first portion of the plurality of bars forming a H-shaped base, a second portion of the plurality of bars having a plurality of upright bars coupled to the H-shaped base, and a third portion of the plurality of bars having a plurality of upper frame bars connected together and coupled to the plurality of upright bars. The H-shaped base is designed to permit attachment of the camera thereto.

Abstract: A fluid measurement system (3) is provided having a Coriolis flowmeter (5) with a meter electronics (20) comprising a processing system (303) and a storage system (304). The Coriolis flowmeter (5) has a sensor assembly (10) comprising conduits (103A, 103B), wherein the sensor assembly (10) is in communication with meter electronics (20). The Coriolis flowmeter (5) has a plurality of pickoffs (105, 105?) affixed to the conduits (103 A, 103B), that are in communication with the meter electronics (20). The Coriolis flowmeter (5) has a driver (104) affixed to the conduits (103A, 103B) that is in communication with the meter electronics (20). A gyroscopic sensor is in communication with the meter electronics (20). At least one actuator (406X, 406 Y, 406Z, 412) is coupled to the Coriolis flowmeter (5). The meter electronics (20) is configured to measure a fluid flow of a process fluid under acceleration through the sensor assembly (10).

Abstract: A gimbal mount system is configured to a couple to a gimbal coupled to and securing a camera. The gimbal mount system includes a handle, a power source, a user interface, a mounting interface, a communication interface, and a communication bus. The mounting interface is located within an end of the gimbal mount system and includes an opening configured to receive a reciprocal mounting protrusion of the gimbal. A locking mechanism removably couples the gimbal to the gimbal mount system. The communication interface is located within the mounting interface and is configured to couple to a reciprocal communication interface of the gimbal. The communication bus is coupled to the power source, user interface, and communication interface and is configured to provide power from the power source to the gimbal. The communication bus may provide instructions to the gimbal based on user input received via the user interface.

Abstract: The invention relates to an adapter for a gravity pendulum, which adapter comprises a support for fastening a gravity body to be measured and at least two seat parts arranged at the support. The at least two seat parts comprise ellipsoid caps which can be held on a holder or on seating faces of a holder and are used to oscillate the adapter.

Abstract: An agile attitude control system (AACS) that is a three axis attitude control device for small spacecraft based on miniature single gimbal control moment gyroscopes (SGCMGs) actuators. The AACS enables agile attitude slewing and accurate pointing/tracking for spacecraft made of multiple CubeSat units, or, more generally, for nanosatellites.

Abstract: A gimbal mount system is configured to a couple to a gimbal coupled to and securing a camera. The gimbal mount system includes a handle, a power source, a user interface, a mounting interface, a communication interface, and a communication bus. The mounting interface is located within an end of the gimbal mount system and includes an opening configured to receive a reciprocal mounting protrusion of the gimbal. A locking mechanism removably couples the gimbal to the gimbal mount system. The communication interface is located within the mounting interface and is configured to couple to a reciprocal communication interface of the gimbal. The communication bus is coupled to the power source, user interface, and communication interface and is configured to provide power from the power source to the gimbal. The communication bus may provide instructions to the gimbal based on user input received via the user interface.

Abstract: A method for compensating for bias of a gyroscope. In one embodiment, bias measurements for a plurality of drive angles are generated using the gyroscope. A set of equations for the bias of the gyroscope is identified using a model for motion of the gyroscope. The set of equations includes a set of parameters for the bias of the gyroscope. A set of values for the set of parameters is identified using the bias measurements and the set of equations.

Abstract: A method for operating a sensor system that includes a rotation rate sensor and an electronic component includes generating, by the rotation rate sensor, a sensor signal as a function of a rotation rate measured about a rotational axis, comparing the sensor signal to at least one first threshold value, and, for controlling the electronic component, outputting an interrupt signal to the electronic component as a function of the comparison of the sensor signal and the at least one first threshold value.

Abstract: In one embodiment, a ball turret assembly for supporting a camera includes a first shaft rotatable about a first axis relative to a first fixed point, the first shaft having an axially-extending interior region in communication with an exterior of the first shaft by way of a first exit port. A first guide disposed at least partially circumferentially on the first shaft proximally to the first exit port is provided, and a cable extends along the interior region of the first shaft and exits the first shaft at the first exit port, the cable looping at least partially around the first shaft and affixed at the first fixed point.

Abstract: A method for adjusting a control moment gyroscope array includes receiving a stream and directing the stream to adjust momentum in the control moment gyroscope.

Abstract: A vehicle incorporating a plurality of control motion gyroscopes (CMTs) contained within a support structure is described. Optionally, a mass shifting mechanism may also be incorporated in the vehicle. The vehicle and its CMTs are configured to have a plurality of gravitationally stable states on a sloped surface.

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: The present technical solution solves a problem of keeping a given direction by use of an element stabilized in a given plane of inertial space, irrespective of disturbing torques, precessions of gyroscopes, and turns of a movable object in the given plane of inertial space when the current technical solution is used on the movable object. This solution is based on forcing precessions of two one-axis gyrostabilizers in opposite directions. The gyrostabilizers are connected with each other by a connection unit comprising a stabilized element. Since in the present solution low precision gyroscopes can be used, then the proposed solution can be implemented in a small-size version.

Abstract: Provided is a system and process of controlling motion. The system and process provide a force to substantially maintain a relative position in response to an external force being applied to at least one of one or more movable members or generate an internal force to adjust the relative position.

Abstract: Disclosed herein are two separate processes that do not require a propellant and do not produce an equal and opposite reaction against any external form of matter in the Local Inertial Reference Frame and do not violate Newton's Laws in the Universal Reference Frame. The first process produces horizontal motion, relies on the earth's gravitational field as an external force, and has been successfully tested. The second process produces vertical motion and relies only on the aether. It has been successfully tested considering the effect of the earth's gravity. Due to the law of conservation of angular momentum, the first process is considered by some to not be possible, but with the proper use of an external field (for example, gravity) and the phenomenon of precession, it is clearly possible. A clear distinction is made between a simple rotor and a gyroscope which is a far more complex device.

Abstract: A multi-axis gimbal has each axis defined by a respective spherical shell driven by a flat, compact motor attached to the driven shell and to a next outer shell (or to an external mounting platform, in the case of the outermost shell). The shells rotate about respective axes. In one configuration, the outermost shell is referred to as the “azimuth” shell because in use it rotates about a vertical axis. The next inner shell is an elevation shell that rotates about a first horizontal axis that is orthogonal to the axis of the camera or other sensor payload. An optional third shell can be used to provide “roll” motion, such as rotating a camera about its axis to obtain a particular rotational orientation with respect to a target.

Abstract: A control system for adjusting the attitude of a spacecraft comprises a set of control moment gyroscopes (CMGs) configured to allow null space maneuvering. The control system further comprises a momentum actuator control processor coupled to the set of CMGs and configured to determine a mandatory null space maneuver to avoid singularities and determine an optional null space maneuver to increase available torque. The mandatory null space maneuver can be calculated based upon certain gimbal angles, and can be implemented by augmenting the inverse-Jacobian control matrix.

Abstract: Systems, including apparatus and methods, for driving airflow along a surface of a gimbal. The systems may comprise a gimbal apparatus including a payload and also including a gimbal mount supporting a first gimbal and a second gimbal. The first gimbal may be coupled pivotally to the gimbal mount. The second gimbal may be coupled pivotally to and supported by the first gimbal. The second gimbal may be coupled to and may support the payload. The gimbal apparatus may orient the payload by pivotal movement of the first and second gimbals relative to the gimbal mount about at least two nonparallel axes. The system also may comprise a fan mounted to the first gimbal. The systems also may comprise operating the fan to drive airflow through a gap disposed between the first and second gimbals.

Abstract: A stabilizing and vibration-isolating mount to facilitate the manual operation of a camera from mobile platforms such as aircraft, motor vehicles, and watercraft. The camera mount comprises a carriage assembly that allows the roll axis of rotation to pass through the optical axis of the camera lens, thus eliminating the pendulum or over-the-center phenomenon that characterizes moving images filmed while the camera is moving about the roll axis. Movement around all three axes of rotation can be stabilized by gyrostabilizers that can be adjustably positioned through the centerlines of the pan, roll, and tilt axes.

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: A vehicle stabilising 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 stabilisation.

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: There is provided a motorized cycle comprising a frame, a seat mounted upon the frame, a plurality of suspensions mounted to the frame, a plurality of wheels each coupled to a suspension wherein the operation of the motorized cycle is based on the physical position and movements of the rider. Also provided is a suspension system for a motorized cycle comprising a plurality of suspensions each coupled to the frame of the motorized cycle, and a plurality of wheels each coupled to a suspension such that each wheel is able to move relative to the other wheels and the frame. According to another aspect, there is provided a rider positioning system for a motorized cycle comprising handle bars and a seat wherein the movement of the handle bars affects the movement of the seat.

Abstract: 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.

Abstract: Gyroscopic Torque Induced Unidirectional Engine is a combination of five engines with a center bi-directional torque motor controlling torque speed, direction and timing of both upper and lower pair-sets of Gyro engines attached to center motors upper and lower drive axles. By electronically manipulating the power to the bi-directional torque motor and the gyros', the force factors are controlled between the upper and lower sets. With the first phase of upper gyros operations repeated by the second phase of lower gyros inducing torques speeds and directions 180 degrees out of phase with the upper gyros. Timing is synchronized for gyros to support one another through its push-reach, pull-reach, “crawl” through space like a twisting caterpillar to obtain an overall combined total engine thrust in a single direction overcoming accelerated Gravity's weight plus POWER to create engine speed in any of the controlled directions.

Abstract: A momentum-control system comprising a plurality of momentum actuators and a platform upon which the plurality of momentum actuators are mounted. The momentum control system further comprises a plurality of active struts mounted on the bottom side of the platform. The active struts are configured to produce a force to steer the plurality of momentum actuators and the platform to produce forces and moments for spacecraft attitude control and disturbance suppression.

Abstract: The present invention is a combination of three interconnected gyroscopic ring-like rotating masses, with each of the three ring-like masses being configured to rotate in various planes, depending on the desired orientation. Regardless of the orientation of the three rings, 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. Additionally, a series of pedestal supports for supporting the three ring-like masses is disclosed.

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 (stabilization of any type of land vehicle), naval (maneuvers and stabilization of naval platforms) and aerospace (satellite attitude control).

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 dynamic unbalance compensation system that compensates for dynamic unbalance of a rotating assembly on a vehicle, such as a spacecraft, to compensate for the presence of a dynamic unbalance moment. The system includes a vehicle, such as a spacecraft, a rotational assembly mounted on the vehicle and rotatable about an axis of rotation relative to the vehicle, and one or more momentum devices mounted on the rotational assembly and generating a momentum vector component perpendicular to the axis of rotation. The one or more momentum devices generate a compensation torque during spinning of the rotational assembly so as to compensate for dynamic unbalance of the rotational assembly.

Abstract: A reaction wheel system is provided that includes at least two rotors. The first rotor is the primary rotor that provides the large output torques to the vehicle. The second rotor is a vernier control rotor. The primary rotor and vernier control rotor each rotate about a common axis. The vernier control rotor has an inertial mass that is less than the inertial mass of the primary rotor, and rotates independently of the primary rotor. Because the vernier control rotor can be rotated independently from the primary rotor, it can be used to significantly improve the performance of the reaction wheel system. Specifically, the vernier control rotor is used to provide relatively small output torques. These relatively small output torques can be used to reduce the disturbances created by motor ripple, provide precise torque output control and/or reduce the disturbances created by static friction.

Abstract: A gyrostabilizer without a physical shaft or axle is constructed. The stabilizer has dual counter-revolving concentric rings filled with weights such as spherical balls that are propelled in orbital fashion by fluid pressure or electromagnet propulsion. The diameter of the concentric ring can vary from a few inches to more than ten (10) feet. Without an axle or shaft the weight of the gyrostabilizer is shifted to the perimeter where most of the momentum is generated at a fraction of the weight of gyrostabilizers that spin on an axle. Also without an axle or shaft the space between the center of revolution and the revolving balls is usable or void. When properly mounted in a vehicle or structure unsteadiness such as tremors, vibrations, sway, pitch, roll, yaw can be dampened.

Abstract: According to the preferred embodiments of the present invention, an apparatus and method for creating directional movement using the natural forces of rotational energy in a gravitational field is disclosed. 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. At high enough levels of angular momentum, outside cosmic forces, including the gravitational force of the environment, will cause the interconnected rotating masses to seek equilibrium by moving away from the strength of the gravitational force.

Abstract: A precessional device featuring a pair of axles each containing at least one flywheel forming a pair of rotors. The pair of axles are each mounted on circular track assemblies in which they rotate and generate a precessional torque that provides variable resistance along a first axis and a balancing of the precessional torque along a second axis.

Abstract: A two axis (azimuth and elevation) stabilized common gimbal (SGC) for use on a wide variety of commercial vehicles and military vehicles which are employed in combat situations capable of stabilizing a payload of primary sensors and of mounting a secondary sensor payload that is independent of the moving axes. The SCG employs three gyroscopes, inertial angular rate feedback for providing gimbal control of two axes during slewing and stabilization. In addition the third (roll) gyroscope is used for performing automatic calibration and decoupling procedures. In this regard, the SCG provides an interface for the primary suite of sensors comprising one or more sensors having a common line-of-sight (LOS) and which are stabilized by electronics, actuators, and inertial sensors against vehicle motion in both azimuth and elevation.

Abstract: A gyroscopic motion device constructed for relative motion over an external support structure. The device includes a frame structure configured to support a pair of spaced apart gyroscopes. The device also includes a substructure operatively interposed the pair of gyroscopes which initiates a precessing effect, which results in a change in the angular disposition of the axes of rotation of the gyroscopes to cause the device to move relative to the external support structure.

Abstract: A turntable acceleration generating apparatus includes a first servo motor, a large-diameter turntable rotated by the first servo motor, and a small-diameter turntable being mounted on the large-diameter turntable at a position offset from the central axis of the large-diameter turntable such that the small-diameter turntable is rotated by a rotary shaft. Furthermore, the turntable acceleration generating apparatus includes a signal line for deriving signals from an acceleration sensor located on one of the sides of the large-diameter turntable, and a control signal line for applying control signal to a second servo motor located on the other side of the large-diameter turntable, wherein the large-diameter turntable is grounded such that the large-diameter turntable prevents noise leakage from the control signal line to the signal line.

Abstract: A gimbal mount system is configured to a couple to a gimbal coupled to and securing a camera. The gimbal mount system includes a handle, a power source, a user interface, a mounting interface, a communication interface, and a communication bus. The mounting interface is located within an end of the gimbal mount system and includes an opening configured to receive a reciprocal mounting protrusion of the gimbal. A locking mechanism removably couples the gimbal to the gimbal mount system. The communication interface is located within the mounting interface and is configured to couple to a reciprocal communication interface of the gimbal. The communication bus is coupled to the power source, user interface, and communication interface and is configured to provide power from the power source to the gimbal. The communication bus may provide instructions to the gimbal based on user input received via the user interface.