A superconducting quenchgun for delivering lunar derived oxygen to lunar orbit

The development of a parametric model for a superconducting quenchgun for launching lunar derived liquid oxygen to lunar orbit is detailed. An overview is presented of the quenchgun geometry and operating principles, a definition of the required support systems, and the methods used to size the quenchgun launcher and support systems. An analysis assessing the impact of a lunar quenchgun on the OEXP Lunar Evolution Case Study is included

A trajectory generation and system characterization model for cislunar low-thrust spacecraft. Volume 2: Technical manual

The documentation of the Trajectory Generation and System Characterization Model for the Cislunar Low-Thrust Spacecraft is presented in Technical and User's Manuals. The system characteristics and trajectories of low thrust nuclear electric propulsion spacecraft can be generated through the use of multiple system technology models coupled with a high fidelity trajectory generation routine. The Earth to Moon trajectories utilize near Earth orbital plane alignment, midcourse control dependent upon the spacecraft's Jacobian constant, and capture to target orbit utilizing velocity matching algorithms. The trajectory generation is performed in a perturbed two-body equinoctial formulation and the restricted three-body formulation. A single control is determined by the user for the interactive midcourse portion of the trajectory. The full spacecraft system characteristics and trajectory are provided as output