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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 dynamic characteristics of the microvibration isolation device are analyzed theoretically and experimentally. Abstract-Control moment gyroscope is a spacecraft attitude control actuators which act as torque amplifier. A control moment gyroscope (CMG) is provided for deployment on a spacecraft. Additionally, for a nano-satellite of a few kilograms, the results prove that it is feasible to manufacture the GCMG concept by using affordable and lightweight commercial off-the-shelf (COTS) stepper motors. In order to provide an ultraquiet environment for spacecraft payload, a six-degree-of-freedom microvibration isolation device for satellite control moment gyro (CMG) is proposed in this paper. An adaptive robust integrated power and attitude control system (IPACS) is presented for a variable speed control moment gyroscope (VSCMG)-actuated satellite. A comparison with the four-VSCMG cluster was conducted through numerical simulations, and the results indicated that the GCMG design was considerably more efficient in terms of power while achieving a better gimbal configuration at the end of the simulation, which is essential when it is desired for different manoeuvres to be consecutively executed. As the rotor tilts, the changing angular momentum causes a gyroscopic torque that rotates the spacecraft.
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The proposed design offers the advantages of SGCMGs, such as a low weight, size, and reduced complexity, with the additional benefit of overcoming the internal elliptic singularities, which create a minor attitude error. A control moment gyroscope (CMG) is an attitude control unit (actuator) consisting of a spinning rotor (also referred as a fly wheel) and one or more motorized gimbals that tilt the rotor’s angular momentum. Contrary to the use of four variable-speed control moment gyroscopes (VSCMGs), where eight degrees of freedom are available for singularity avoidance, the proposed GCMG design uses only five degrees of freedom (DoFs), and a modified steering law was designed for the new setup.
CONTROL MOMENT GYROSCOPE FULL
Four SGCMGs were used in a pyramid configuration, along with an additional small and simple stepper motor that was used to gimbal the full cluster around its vertical ( z) axis. The LPV model constructed by linearizing the nonlinear model around moving operating points contains fifteen scheduling variables causing a massive computational complexity involved in controller synthesis. This paper addresses the problem of singularity avoidance in a cluster of four Single-Gimbal Control Moment Gyroscopes (SGCMGs) in a pyramid configuration when used for the attitude control of a satellite by introducing a new gimballed control moment gyroscope (GCMG) cluster scheme. This paper presents an LPV output feedback control strategy for a 4-DOF control moment gyroscope (CMG).