Аннотация
A new form of the equations of motion for a spacecraft with single
gimbal control moment gyros (CMG) is developed using a momentum approach.
This set of four vector equations describing the rotational motion
of the system is of order 2N + 7, where N is the number of CMGs.
The central input is an N X 1 column vector of torques applied to
the gimbal axes. A modification to a singularity robust Lyapunov
control law is examined and compared to that control law. Specifically,
the attempt to avoid singular gimbal configurations is abandoned
in favor of simply avoiding movement in the singular direction. The
singular value decomposition is used to compute a pseudoinverse that
prevents large gimbal rate commands near or at actual singularities.
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