An analysis of maneuver characteristics and propulsion system sizing parameters for proximity maneuvers performed by a small inspector spacecraft

Fielding smaller spacecraft able to perform the same tasks as larger predecessors is an on-going emphasis for the aerospace community. This is largely driven by high launch costs incurred on a per-mass basis. In addition to the desire for smaller spacecraft, there is a parallel course of emphasis to enable existing and future spacecraft to have longer operational lifetimes. Less frequent launches could reduce the long-term costs of maintaining a presence in space. One solution is to have a separate spacecraft that can rendezvous with and inspect, re-boost, or refuel target satellites. To minimize costs, this satellite should be as small as possible, yet still have capabilities of fulfilling the mission objectives. A critical aspect of an inspector satellite is the propulsion system utilized to move around in orbit to its target(s) and to perform the desired proximity operations upon arrival.; The initial step in the current research was to explore similar previous missions, with an eye on subsystems and practices used to directly enable rendezvous and proximity operations. (Abstract shortened by UMI.)...