scholarly journals Inertia-Free Spacecraft Attitude Control with Control Moment Gyroscope Actuation

2012 ◽  
Author(s):  
Kshitij Agarwal ◽  
Avishai Weiss ◽  
Ilya Kolmanovsky ◽  
Dennis Bernstein
Keyword(s):  
Attitude Control ◽  
Spacecraft Attitude ◽  
Spacecraft Attitude Control ◽  
Control Moment Gyroscope ◽  
Control Moment

Measuring Natural Frequency of Large Control Moment Gyroscope

2014 ◽  
Vol 526 ◽  
pp. 99-102
Author(s):  
Xue Li ◽  
Wei Cheng
Keyword(s):  
Natural Frequency ◽  
Attitude Control ◽  
Rapid Response ◽  
Spacecraft Attitude ◽  
Response Functions ◽  
Spacecraft Attitude Control ◽  
Control Moment Gyroscope ◽  
Control Moment ◽  
Output Torque ◽  
Long Life

As an actuator of spacecraft attitude control, the large control moment gyroscope (CMG) produces significant output torque and exhibits excellent linearity features for control, anti-disturbance, and rapid response functions. The large CMG is globally preferred for the execution mechanism of long-life spacecraft. This gyroscope is characterized by massive moving parts and distinct natural frequency between working and halting modes. Based on these features, this study measures the natural frequency of the large CMG by using both hammering and CMG startup testing.

Design of an Adaptive Singularity-Free Control Moment Gyroscope (ASCMG) Cluster for Spacecraft Attitude Control

2015 ◽  
Author(s):  
Sasi Prabhakaran Viswanathan ◽  
Amit K. Sanyal
Keyword(s):  
Angular Momentum ◽  
Finite Number ◽  
Attitude Control ◽  
Degrees Of Freedom ◽  
Spacecraft Attitude ◽  
Spacecraft Attitude Control ◽  
Dynamics Model ◽  
Control Moment Gyroscope ◽  
Control Moment ◽  
Control Scheme

Spacecraft attitude control using an Adaptive Singularity-free Control Moment Gyroscope (ASCMG) cluster design for internal actuation is presented. A complete dynamics model is derived using the principles of variational mechanics, relaxing some common assumptions made in prior literature on control moment gyroscopes. These assumptions include perfect axisymmetry of the rotor and gimbal structures, and perfect alignment of the centers of mass of the gimbal and the rotor. The resulting dynamics display complex nonlinear coupling between the internal degrees of freedom associated with the CMG and the spacecraft base body’s rotational degrees of freedom in the absence of these assumptions. This dynamics model is further generalized to include the effects of multiple CMGs placed in the spacecraft bus, and sufficient conditions for non-singular CMG cluster configurations are obtained. General ideas on control of the angular momentum of the spacecraft using changes in the momentum variables of a finite number of CMGs, are provided. A control scheme using a finite number of CMGs in the absence of external torques and when the total angular momentum of the spacecraft is zero, is presented. The dynamics model of the spacecraft with a finite number of CMGs is then simplified under the assumption that the rotor is axisymmetric, in which case it is shown that singularities are avoided. As an example, the case of three CMGs with axisymmetric rotors, placed in a tetrahedron configuration inside the spacecraft, is considered. The control scheme is then numerically implemented using a geometric variational integrator and the results confirm the singularity-free property and high control authority of the ASCMG cluster. Moreover, as rotor misalignments are addressed in the dynamics model, the ASCMG cluster can adapt to them without requiring hardware changes.

Spacecraft attitude control and vibration suppression integration based on single gimbal magnetically suspended control moment gyroscope pyramid configuration

2018 ◽  
Vol 233 (8) ◽  
pp. 2673-2684 ◽  
Author(s):  
Xiaocen Chen ◽  
Yuanwen Cai ◽  
Yuan Ren
Keyword(s):  
Attitude Control ◽  
Vibration Suppression ◽  
Magnetic Suspension ◽  
Spacecraft Attitude ◽  
Spacecraft Attitude Control ◽  
Control Moment Gyroscope ◽  
Control Moment ◽  
Attitude Maneuver ◽  
Static Performance ◽  
Micro Vibration

For the sake of improving the agility and super-static performance of spacecraft, this paper puts forward an idea for using single gimbal magnetically suspended control moment gyroscope pyramid configuration to realize dual control of attitude maneuver and micro-vibration suppression of spacecraft, in which gyro gimbal rotation is used to realize fast attitude maneuver and magnetic suspension rotor deflection is used to realize high-precision micro-vibration suppression of spacecraft; the switching design of spacecraft attitude/vibration controller realizes the coordinated operation of gyro gimbal and magnetic suspension motor, showing the control advantage of dual actuators. This strategy not only speeds up the attitude maneuver process of spacecraft, improving the dynamic response, but also reduces the attitude stabilization adjustment time as well as improves the stabilization precision, ensuring the fast vibration suppression after attitude maneuver. In addition, this method has strong robustness ensuring the smooth implementation of spacecraft attitude control and vibration suppression integration in the case of parameter change. The simulation results show the effectiveness and superiority of this strategy.

Retrospective cost adaptive spacecraft attitude control using control moment gyros

2014 ◽  
Author(s):  
Marc Camblor ◽  
Gerardo Cruz ◽  
Sergio Esteban ◽  
Fred A. Leve ◽  
Dennis S. Bernstein
Keyword(s):  
Attitude Control ◽  
Spacecraft Attitude ◽  
Spacecraft Attitude Control ◽  
Control Moment

Control moment gyroscopes for spacecraft attitude control systems: Current status and prospects

2015 ◽  
Vol 6 (3) ◽  
pp. 236-240 ◽  
Author(s):  
A. R. Mkrtychyan ◽  
N. I. Bashkeev ◽  
D. O. Yakimovskii ◽  
D. I. Akashev ◽  
O. B. Yakovets
Keyword(s):  
Control Systems ◽  
Attitude Control ◽  
Current Status ◽  
Spacecraft Attitude ◽  
Spacecraft Attitude Control ◽  
Control Moment ◽  
Control Moment Gyroscopes

scholarly journals Spacecraft Attitude Control Using Control Moment Gyro Reconfiguration

2014 ◽  
Vol 23 (3) ◽  
Author(s):  
Kanthalakshmi SRINIVASAN ◽  
Deepana GANDHI ◽  
Manikandan VENUGOPAL
Keyword(s):  
Attitude Control ◽  
Spacecraft Attitude ◽  
Spacecraft Attitude Control ◽  
Control Moment ◽  
Control Moment Gyro
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