TY - JOUR

T1 - Study of wheel activated gyroscopic-like motion in spacecraft rotational dynamics

AU - Lin, Y. Y.

AU - Wang, C. T.

N1 - Funding Information:
This research work was supported by the National Space Organization of the Republic of China under Grant 98-NSPO(A)-GE-FA09-02.

PY - 2013

Y1 - 2013

N2 - This research investigates the applications of a gyroscopic-like motion embedded in the attitude dynamics of a rigid-body that can be induced with an onboard torque wheel. The motion may be utilized by a rigid spacecraft to regain its attitude stability from a tumbling or a flat-spin situation to rotate about a designated principal axis, which parallels to the spin axis of the torque wheel. Also, the total angular momentum of the spacecraft remains conserved during the process as disturbance torques around the system in space are considered relatively very small and are ignored. To start the motion, the wheel is manipulated to rotate the spacecraft platform with reaction torque such that the projection of the total angular momentum falls in a proper quadrant on the plane perpendicular to the designated principal axis. Then, the projection is able to activate a self-induced, gyroscopiclike motion, which in effect transfers angular momentum to the wheel and the platform along the designated principal axis, aligning the designated principal axis with the total angular momentum and reducing the nutation angle between the two to zero. The phenomenon can be derived from the attitude model in terms of angular momentum. The control law of the wheel torque is formulated with the method of feedback linearization following the results from the Lyapunov stability analysis. Without any direct control effort, simulation results indicate that efficient time and energy can be achieved with effective attitude recovery of a spacecraft to any of the principal axis compared to the existing methods, and the wheel momentum accumulated during the motion can be predicted after the alignment maneuver.

AB - This research investigates the applications of a gyroscopic-like motion embedded in the attitude dynamics of a rigid-body that can be induced with an onboard torque wheel. The motion may be utilized by a rigid spacecraft to regain its attitude stability from a tumbling or a flat-spin situation to rotate about a designated principal axis, which parallels to the spin axis of the torque wheel. Also, the total angular momentum of the spacecraft remains conserved during the process as disturbance torques around the system in space are considered relatively very small and are ignored. To start the motion, the wheel is manipulated to rotate the spacecraft platform with reaction torque such that the projection of the total angular momentum falls in a proper quadrant on the plane perpendicular to the designated principal axis. Then, the projection is able to activate a self-induced, gyroscopiclike motion, which in effect transfers angular momentum to the wheel and the platform along the designated principal axis, aligning the designated principal axis with the total angular momentum and reducing the nutation angle between the two to zero. The phenomenon can be derived from the attitude model in terms of angular momentum. The control law of the wheel torque is formulated with the method of feedback linearization following the results from the Lyapunov stability analysis. Without any direct control effort, simulation results indicate that efficient time and energy can be achieved with effective attitude recovery of a spacecraft to any of the principal axis compared to the existing methods, and the wheel momentum accumulated during the motion can be predicted after the alignment maneuver.

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U2 - 10.1016/j.proeng.2013.12.048

DO - 10.1016/j.proeng.2013.12.048

M3 - Conference article

AN - SCOPUS:84893388088

VL - 67

SP - 479

EP - 488

JO - Procedia Engineering

JF - Procedia Engineering

SN - 1877-7058

T2 - 7th Asian-Pacific Conference on Aerospace Technology and Science, APCATS 2013

Y2 - 23 May 2013 through 26 May 2013

ER -