The project focuses on the development of a low cost, compact, low tank pressure, high performance nanosat propulsion system 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 MMH/MON-25 thruster. The proposed effort leverages developments made as part of several on-going programs and integrates them into a high performance system. The Phase I effort also includes hardware manufacturing and test to reduce development risks. 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 (fewer components). Furthermore, 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.
