Abstract
A formalism of matrix description of the trajectory of in-orbit erection of large space structures was proposed. The objective functions that can be minimized to establish the optimal erection trajectory guaranteeing the least impact of the basic control on the flexible-structure dynamics were formulated. A software package for computer-aided support of the procedure generating a set of feasible erection trajectories of the large space structures and using the well-known approach to optimization on graphs to specify the optimal trajectory was developed.
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