TY - GEN
T1 - A reconfiguration scheme for control moment gyros with adjustable installation angles
AU - Jin, Jin
AU - Zhang, Jingrui
AU - Liu, Zaozhen
PY - 2011
Y1 - 2011
N2 - This paper proposes a novel reconfiguration scheme for Control Moment Gyros, where a rotator is introduced into the gyro's support bracket, to make the installation angles adjustable. When some gyros in the cluster fail, the control capability of actuator is reduced as the axial symmetry is broken and the momentum body is retracted and distorted. By adjusting the installation angles of the rest gyros, the axial symmetry could be repaired and the control capability could be fully exploited. Different topologic cases are considered in this scheme. In the process of reconfiguration, the output dynamic torque is studied, and then the expression of anti force in spacecraft is given. A special steering law is designed to counteract the disturbance from reconfiguration. The feasibility of singularity avoidance via reconfiguration is also discussed by calculating the derivative of the singularity measurement to installation angle. A singularity avoidance steering law is proposed based on the above calculation.
AB - This paper proposes a novel reconfiguration scheme for Control Moment Gyros, where a rotator is introduced into the gyro's support bracket, to make the installation angles adjustable. When some gyros in the cluster fail, the control capability of actuator is reduced as the axial symmetry is broken and the momentum body is retracted and distorted. By adjusting the installation angles of the rest gyros, the axial symmetry could be repaired and the control capability could be fully exploited. Different topologic cases are considered in this scheme. In the process of reconfiguration, the output dynamic torque is studied, and then the expression of anti force in spacecraft is given. A special steering law is designed to counteract the disturbance from reconfiguration. The feasibility of singularity avoidance via reconfiguration is also discussed by calculating the derivative of the singularity measurement to installation angle. A singularity avoidance steering law is proposed based on the above calculation.
UR - http://www.scopus.com/inward/record.url?scp=85086950701&partnerID=8YFLogxK
U2 - 10.2514/6.2011-6354
DO - 10.2514/6.2011-6354
M3 - Conference contribution
AN - SCOPUS:85086950701
SN - 9781600869525
T3 - AIAA Guidance, Navigation, and Control Conference 2011
BT - AIAA Guidance, Navigation, and Control Conference 2011
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - AIAA Guidance, Navigation and Control Conference 2011
Y2 - 8 August 2011 through 11 August 2011
ER -