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A. Steindl:
"Time optimal control for the deployment of a tethered satellite allowing for a massive tether";
Meccanica, 11 (2016), 51; S. 2741 - 2751.

The time optimal deployment of a satellite
from a space ship is studied. In order to take the mass
and lateral oscillations of the tether into account, a
discretized model of the tether is build. Applying
Pontryagin´s Maximum Principle a time-optimal
deployment from a trivial downhanging configuration
close to the space ship to another one farther away is
computed. It is found, that the obtained solution
displays a difficult switching pattern and during the
variation of the initial length different kinds of
bifurcations occur, leading to discontinuous variations
of the optimal solution candidates.

Optimal Control, Tethered Satellite, Deployment

http://dx.doi.org/10.1007/s11012-016-0541-9

http://publik.tuwien.ac.at/files/publik_254937.pdf