摘要:
An attitude control system for a spacecraft is disclosed that includes a scissored pair of control moment gyroscopes for delivering an output torque to the spacecraft along a an output axis, wherein each gyroscope has a spin motor for spinning a rotor about a rotor axis and a gimbal torque motor for rotating the rotor about a gimbal axis, and wherein the system includes a generator for extracting kinetic energy from the rotors during rotor deceleration to power the gimbal torque motors of the gyroscopes.
摘要:
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.
摘要:
The invention concerns a gear device, preferably motor device, for providing rotation about at least one output axis and a method for providing rotation. A body (2) is mounted for a rotation about first (4), second (11), and third (16) axes. The first axis (4) is oriented with respect to the second axis (11) at an inclination angle. The second axis (11) and/or the third axis (16) constitute the at least one output axis of device. The rotation of the body (2) about the third axis (16) gives rise to a change in the inclination angle. A ram (15) applies a torque (21) to the body (2) about the third axis (16) in a sense of increasing inclination angle when the first axis (4) is at a selected inclination angle with respect to the second axis (11) which is greater than 0° and less than 90°. The rotation of the body (2) about the third axis (16) in a sense of decreasing inclination angle is limited such that the inclination angle of the first axis (4) with respect to the second axis (11) remains greater than 0 degrees and less than 90 degrees. The body (2) is rotated about the first axis (4) at an angular velocity greater than a critical angular velocity so that a constant or a decreasing inclination angle is reached.
摘要:
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.
摘要:
The present invention relates to motors and, more specifically to rotary motors which can supply output motive power about an output axis in response to input rotary power about a different axis. A motor (1) comprises a wheel (2) mounted on a shaft (3) for rotation about a first axis (4). The shaft (3) is additionally mounted for rotation about both an inclination axis (16) and the output axis (11) of the motor (1).
摘要:
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.
摘要:
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.
摘要:
The present invention provides a control moment gyroscope that overcomes many of the limitations of the prior art. The control moment gyroscope provides a radial actuator mechanism to provide rotation to an inner gimbal assembly around a gimbal axis. The radial actuator mechanism comprises a circular ring at the midpoint of the gimbal axis, the circular ring extending around the outer periphery of the inner gimbal assembly housing. The radial actuator mechanism rotates the inner gimbal assembly around the gimbal axis through the use of a non-contact motor that provides rotational force directly to the outer perimeter of the inner gimbal assembly. Because the inner gimbal assembly is rotated from the midpoint of the gimbal axis, a torque module assembly at the end of the gimbal axis is not required. Thus, the overall length of the control moment gyroscope can be reduced. Additionally, the cost and life limiting attributes of the torque module assembly can be eliminated, and the operational bandwidth of the gyroscope increased. Finally, because the inner gimbal assembly is rotated from the outer perimeter, the torque provided to the inner gimbal assembly is naturally increased by the leverage arm of the inner gimbal assembly.
摘要:
A direct current (DC) powered gyroscope (41) utilizes an alternating current (AC) subsystem in which electrolytic switches (49, 50) control torquer motors (45, 46). The alternating current is obtained from commutation circuitry (21-23) in the gyroscope spin motor, so that the spin motor performs an inverter function. Advantages include reduced costs and the ability to operate the gyroscope (41) without an AC power supply.
摘要:
A gyro apparatus comprising a gyro casing incorporating therein a gyro the spin axis of which is made substantially horizontal, a supporting apparatus for supporting the gyro casing with a freedom of three axes, a north-seeking apparatus for giving a north-seeking action to the gyro, a follow-up ring having a follow-up shaft which follows the gyro casing around its substantially vertical axis, a binnacle for supporting the follow-up shaft, a servo motor for rotating the follow-up shaft and a slip ring for supplying a power to the gyro and the like through the follow-up shaft, in which the follow-up ring is formed as a fork-shape and supported to the binnacle in a canti-lever fashion, the follow-up shaft is rotatably supported to the binnacle by one thin-type ball bearing having a large diameter and one bearing having a small diameter, the follow-up shaft is fixedly provided with a rotor of a pancake-type servo motor of a direct drive system, a stator of the servo motor is attached to the binnacle at the position corresponding to the rotor and a slip ring is attached to the binnacle at the outer periphery of the servo motor.