An evaluation of the feasibility and mission performance benefits of using advanced space storable propellants for outer planet exploration was performed. For the purpose of this study, space storable propellants are defined to be propellants which can be passively stored without the need for active cooling. A secondary purpose o f this study was to provide guidance as to the limits, benefits, and possible methods of passively storing such mild cryogenic propellants for deep space missions. The study was composed of four distinct efforts. First, candidate propellants were defined and their relevant properties determined. Second, a propellant combination analysis using the Two Dimensional Kinetics 1997 (TDK97) program was conducted. Third, a thermal storage design was analyzed. Lastly, a mission and systems analysis was performed for three outer planetary missions. The missions are representative in complexity, duration, and requirements for a variegated set of outer planet exploration missions currently being considered by NASA. Nonetheless, the analysis conducted and outlined in this paper determined that outer planet exploration using advanced storable propellants was feasible and offered a significant benefit in delivered payload compared to previous design studies.

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A new multi mate/demate metal face seal fitting has recently been flight qualified at JPL. The Omnisafe fitting incorporates a torque elimination feature that prevents misalignment of components and damage to the sealing surfaces. This fitting which has been used for ten years in the semiconductor industry and at Lawrence Livermore National Laboratories, has successfully maintained leak integrity after flight qualification testing. Following ten mate/demate cycles, this qualification included exposure to shock & vibration, thermal cycling, and pressure cycling that simulate flight conditions. Fluid delivery applications in xenon gas propulsion and liquid Freon cooling service have been proposed for this fitting. This robust, reusable fitting enables flight subsystems to be built and tested independently and in parallel. Fittings also facilitate late integration of fluid system components, unlike most welded systems. This reusable coupler can be used to modularize flight systems and reduce integration costs.