In-Space Testing of Satellite Servicing and Inspection Elements

By building on technology elements funded elsewhere, Microcosm proposes to develop an inspection and servicing architecture and test key components of that architecture in space by the end of Phase II, all within Phases I and II budgets. Phase I isprimarily a systems study concentrating on three principal issues: (1) system engineering trades leading to the development of an efficient, flexible architecture, (2) the benefits of on-orbit inspection and servicing to reduce cost and enable newmissions, and (3) definition of the in-space test in sufficient detail to ensure that it can be completed within the scope of a Phase II SBIR. This substantial step is made possible by leveraging recently awarded and related NASA and DARPA SBIRs,Microcosm's current autonomous GN&C and expert control systems, and Michigan Aerospace's autonomous docking system, and making use of a free test flight of Microcosm's Scorpius low-cost launch system currently undergoing development and flight tests. Thesystem level technologies developed here are critical to the Air Force Space Control mission and could be of substantial benefit to both NASA and commercial users. The in-space system testing represents a major, near-term step in making this technologyavailable to the space community.There is great potential for this technology to substantially lower the cost and extend the life of LEO science and defense related missions as well as GEO communications satellites. The lifetime of a LEO satellite islimited primarily by atmospheric drag. A virtually unlimited supply of fuel could be transferred to LEO satellites, indefinitely, for stationkeeping purposes. High priced defense programs (e.g. SBIRS Low and SBL) and science missions (e.g. HST and TOPEX)would no longer be consumables limited if they could support satellite docking, refueling, and component replacement. GEO satellites pay a high premium for stationkeeping fuel. If GEO satellites where able to refuel, their payload mass fraction could beincreased substantially at launch. This option is particularly attractive due to the relatively large number of launches per year into GTO. Re-fueling missions could be made small enough to fit as a secondary payload aboard the ASAP ring of the Ariane 5,for example, further increasing the cost efficacy of on-orbit servicing.