The use of electric propulsion is more prevalent than ever, with industry pursuing all electric orbit transfers. Electric propulsion provides high mass utilization through efficient propellant transfer. However, the transfer times become detrimental as the ∆V transitions from nearimpulsive to low-thrust. Increasing power and therefore thrust has diminishing returns as the increasing mass of the power system limits the potential acceleration of the spacecraft. By using space-to-space power beaming, the power system can be decoupled from the spacecraft and allow significantly higher spacecraft alpha (W/kg) and therefore enable significantly higher accelerations while maintaining high performance. This project assesses the efficacy of space-to-space power beaming to enable rapid orbit transfer while maintaining high mass utilization. Concept assessment requires integrated techniques for low-thrust orbit transfer steering laws, efficient large-scale rectenna systems, and satellite constellation configuration optimization.This project includes the development of an integrated tool with implementation of IPOPT, Q-Law, and power-beaming models. The results highlight the viability of the concept, limits and paths to infusion, and comparison to state-of-the-art capabilities. The results indicate the viability of power beaming for what may be the only approach for achieving the desired transit times with high specific impulse. Nomenclature

This paper demonstrates infrastructure-free orbital Simultaneous Localization and Mapping (SLAM). Individual surface landmarks are tracked through images taken in orbit and the filter receives measurements of these landmarks in the form of bearing angles. The filter then updates the spacecraft's position and velocity as well as landmark locations, thus building a map of the orbited body. In contrast to other approaches that use an IMU, which doesn't work in orbit, to resolve scale, the contribution of this paper is to demonstrate that scale can be resolved using orbital dynamics. Radio localization can be replaced with onboard localization, enabling truly autonomous missions to both under-mapped and unmapped planetary bodies.Overall system convergence is shown by simulating landmark detection from an orbit of the Clementine Mission on a Moon model constructed using Lunar Reconnaissance Orbiter (LRO) digital elevation data in conjunction with the filter. The techniques developed in this work demonstrate that when combined with a gravity model, visual SLAM converges to a full scale solution.