Spacecraft large angle rotational maneuvers with optimal momentum transfer
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Optimal large-angle rotational maneuvers of rigid asymmetric spacecraft with multiple reaction wheels are presented. Necessary conditions for optimally subject to various performance indices are obtained via Pontryagin's principle. For a controllable spacecraft configuration, given the initial conditions and restricting attention to internal torques, the final angular velocity and orientation states are constrained in such a way that the system angular momentum is constant in inertial space. The resulting two-point boundary value problem is solved numerically, and optimal detumbling and reorientation maneuvers are illustrated through examples.
author list (cited authors)
VADALI, S., & JUNKINS, J.