NASA has been studying options to conduct missions beyond Low Earth Orbit, but within the Earth-Moon system, in preparation for deep space exploration including human missions to Mars. Referred to as the Proving Ground, this arena of exploration activities will enable the development of human spaceflight systems and operations to satisfy future exploration objectives beyond the cislunar environment. One option being considered includes the deployment of a habitable element or elements, which could be used as a central location for aggregation of supplies and resources for human missions in cislunar space and beyond. Characterizing candidate orbit locations for this asset and the impacts on system design and mission operations is important in the overall assessment of the options being considered. The orbits assessed in this paper were previously identified in work conducted by NASA and others. In this paper orbits are assessed for their relative attractiveness based on various factors. First, a set of constraints related to the capability of the combined Orion and Space Launch System (SLS) system to deliver humans and cargo to and from the orbit are evaluated. Second, the ability to support potential lunar surface activities is considered. Finally, deployed assets intended to spend multiple years in the Proving Ground would ideally require minimal station keeping costs to reduce the mass budget allocated to this function. Additional mission design drivers include potential for uninterrupted communication with deployed assets, thermal, communications, and other operational implications. The results of the characterization and evaluation of the selected orbits indicate a Near Rectilinear Orbit (NRO) is an attractive candidate as an aggregation point or staging location for operations. In this paper, the NRO is further described in terms which balance a number of key attributes that favor a variety of mission classes to meet multiple, sometimes competing, constraints.

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This paper will describe the benefits of execution of the Asteroid Redirect Mission as an early mission in deep space, demonstrating solar electric propulsion, deep space robotics, ground and on-board navigation, docking, and EVA. The paper will also discuss how staging in trans-lunar space and the elements associated with this mission are excellent building blocks for subsequent deep space missions to Mars or other destinations. NomenclatureARM = Asteroid Redirect Mission ARCM = Asteroid Redirect Crewed Mission ARRM = Asteroid Redirect Robotic Mission ARRV = Asteroid Redirect Robotic Vehicle DOF = Degree of Freedom DRO = Distant Retrograde Orbit DSS = Deployable Space Systems EHF = Extremely High Frequency ELV = Expendable Launch Vehicle This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. SpaceOps Conferences ISRU = In-Situ Resource Utilization LEA = Launch/Entry/Abort MACES = Modified Advanced Crew Escape Suit NEA = Near-Earth Asteroid NEOO = Near-Earth Object Observations NRE = Non-Recurring Engineering PLSS = Portable Life Support System RBC = Robotic Boulder Capture ROSA = Roll-Out Solar Array SAC = Small Asteroid Capture SEP = Solar Electric Propulsion SLS = Space Launch System STMD

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