Developments in space technology have enabled new, excitement mission concepts that are allowing humankind to push the boundaries of the known universe. One of such advancements, electric propulsion, has changed the paradigm of deep space exploration, enabling more efficient mass utilization throughout long missions. Large and highly-efficient solar arrays are often combined with electric propulsion as the main source of power in deep space.

Each of these instruments are associated by pointing requirements that must be respected in order for the instruments to operate effectively. Accurate pointing is often made possible by articulated components that can move with respect to the rigid spacecraft hub. This, however, adds degrees of freedom to the problem of defining an optimal attitude for a spacecraft with multiple pointing requirements. While ensuring satisfaction of pointing requirements is typically a trivial challenge for each piece of technology considered individually, combining multiple elements into one spacecraft gives rise to higher-dimensional problems whose solution is not trivial. The highly constrained nature of this problem becomes even more challenging when considering the dynamics of a spacecraft, specifically issues such as momentum buildup on the system due to external perturbations, or maneuvering the spacecraft between two commanded attitudes while ensuring that pointing constraints remain satisfied at all times.

For these reasons, there is the need for new, more versatile and comprehensive algorithms that can intelligently deliver solutions that are tailored to spacecraft with complex dynamics and pointing requirements. This work analyzes the dynamics of one such spacecraft, proposing GN&C algorithms that leverage the spacecraft design to enhance the performance and reduce costs and human input, while ensuring stability, requirement satisfaction, and online execution.