Jitter and excessive settling time after slewing maneuvers has proven to be a severe limitation on the scientific utility of a number of spacecraft. In this article a new design and control strategy is presented that is based on advanced solar arrays that exploit their inertial properties and a balance of passive and active dynamics to minimize jitter and settling time, thereby boosting spacecraft scientific utility. This development will require the advancement of some promising optimization-based methods for simultaneous physical and control system design to determine the best possible synergy between the control system and passive structural system dynamics. The solar array will be designed specifically to be compliant using pseudo-rigid-body dynamic modeling theory. Shooting will be utilized to solve the optimal control problem posed in the co-design formulation.