Scalable, High Performance, Pump-Fed Spacecraft Propulsion System

The project focuses on the development of a low cost, compact, low tank pressure, high performance AF-M315E propulsion system for ESPA-class spacecraft which could be scaled to larger spacecraft. The technology, based on micropumps developed for hydrazine, MMH, NTO, AF-M315E and LMP-103S, has been demonstrated in hot-fire tests with hydrazine, and hot fire tests are planned for a 100 lbf class hypergolic thruster. The Phase II effort builds on results from Phase I including low cost tank with integrated feed system manufacturing and system pulsed cold flow tests. With a micropump, the pressurization system is eliminated, the propellant storage and feed system can be designed for low pressures, and lighter, conformal tanks can be used for greater compactness. This reduces system overall size and mass thus providing increases in performance. Hardware costs are significantly less and many of the components can be made affordably and quickly using additive manufacturing techniques.The technology can be used for steady-state burns, in pulse-mode, and for throttling if needed for optimum mission operations, and is applicable to all propellant combinations and scales ranging from CubeSats and Nanosats to larger satellites such as GPS and AEHF.