Fast-Response ASCENT Fueling

Outpost and Rubicon propose a solution that maximizes the spacecraft fueling throughput by 1) reducing the number of facility related dependencies to a bare minimum, and 2) maximizing the exchange of limiting commodities such as propellant (in original containers from distributor or inventory) and spacecraft propellant loading in serial operations with inertia (movement). The proposed system would be limited to the internal mechanism, gauging, and operations necessary to move propellant through it methodically. Internal volume would be limited to the extent possible with low-point discharge ports for decontamination after a campaign. The design will have intrinsically safe electrical components and will be able to operate on battery power. Propellant mass gauging would be by scale and/or by flow metering. Propellant collection of assay before and after for propellant property verification. Pressurant requirement servicing will depend on the spacecrafts propulsion system design. Structural and fluid components are driven by NASA and DOD ground support equipment and propulsion system design standards (Ref. NASA-STD-5005, SSCMAN91-710V3) but shall be tailored to capitalize on ASCENT’s simplified handling, transportation, and lower safety concerns.  Internal volume would be limited to the extent possible with low-point discharge ports for decontamination after a campaign. The design will have intrinsically safe electrical components and will be able to operate on battery power in the event facilities are not compliant.  Electrical grounding and electrostatic discharge requirements are also levied on this system where necessary. Further, material conformity dictates the propellant lines, valve, gage, seals, and connector materials. Outpost and Rubicon are experienced in drafting and releasing test and operating procedures.  The team shall draft a list of required documents for the fueling system adapted from Zuttarelli. Tailoring these procedures is mandatory.  Lessons learned show that the complexity of past fueling systems would disqualify any candidate from meeting the reliability or availability requirements (24 hours to launch, 4 hours to fuel). Design considerations and simplifications may shorten or eliminate some of the checklists (CLs) and Standard Operating Procedures (SOPs) listed in Zuttarelli.  The Responsive Space Team will be expected to review and provide guidance for concept of operations (CONOPS) and procedure development.