TY - GEN
T1 - Decentralized guidance and control for spacecraft formation flying using virtual leader configuration
AU - Lee, Daero
AU - Viswanathan, Sasi Prabhakaran
AU - Holguin, Lee
AU - Sanyal, Amit K.
AU - Butcher, Eric A.
PY - 2013
Y1 - 2013
N2 - This paper proposes a novel guidance and control scheme for decentralized spacecraft formation flying on SE(3) via virtual leader configuration. The configuration space for a spacecraft modeled as a rigid body is the Lie group SE(3), which is the set of positions and orientations of the spacecraft moving in three-dimensional Euclidean space. A combined guidance and feedback control law in continuous time for the full (translational and rotational) motion of a rigid body under the influence of external disturbance is designed. The guidance scheme aims to reach a final relative configuration according to the desired formation where the relative configuration is described in terms of the exponential coordinates on SE(3). The control law then obtains the desired trajectory leading to the desired formation. The stability of the feedback control system is analyzed. Numerical simulation results demonstrates that the control law can effectively perform a decentralized formation flying for a selected rigid spacecraft formation between three spacecraft.
AB - This paper proposes a novel guidance and control scheme for decentralized spacecraft formation flying on SE(3) via virtual leader configuration. The configuration space for a spacecraft modeled as a rigid body is the Lie group SE(3), which is the set of positions and orientations of the spacecraft moving in three-dimensional Euclidean space. A combined guidance and feedback control law in continuous time for the full (translational and rotational) motion of a rigid body under the influence of external disturbance is designed. The guidance scheme aims to reach a final relative configuration according to the desired formation where the relative configuration is described in terms of the exponential coordinates on SE(3). The control law then obtains the desired trajectory leading to the desired formation. The stability of the feedback control system is analyzed. Numerical simulation results demonstrates that the control law can effectively perform a decentralized formation flying for a selected rigid spacecraft formation between three spacecraft.
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U2 - 10.1109/acc.2013.6580585
DO - 10.1109/acc.2013.6580585
M3 - Conference contribution
AN - SCOPUS:84883527936
SN - 9781479901777
T3 - Proceedings of the American Control Conference
SP - 4826
EP - 4831
BT - 2013 American Control Conference, ACC 2013
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 2013 1st American Control Conference, ACC 2013
Y2 - 17 June 2013 through 19 June 2013
ER -