Optimal deployment/retrieval of a tethered formation spinning in the orbital plane

The deployment/retrieval of a spinning three-mass tethered formation is considered. The tethered formation is modeled by point mass satellites connected via inelastic tethers. Optimal deployment/retrieval trajectories using tension control are determined for different spin conditions. Deployment and retrieval trajectories are obtained that maintain the tether spin at the desired rate and keep the system in the desired physical arrangement at the end of deployment/retrieval. Parametric studies of the effect of system spin rate and maneuver time are performed. Numerical results show that it is necessary to constrain the relative tether geometry to prevent any two tethers crossing each other. It is also shown that the tether spin rate tends to decrease during deployment but can be restored to the desired value by overdeploying the tethers and then reeling them in rapidly. Numerical results also illustrate the symmetrical nature of deployment and retrieval.

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