Skip Navigation
SBIR/STTR

Micropump for MON-25/MMH Propulsion and Attitude Control, Phase II

Completed Technology Project

Project Introduction

Flight Works is proposing to expand its work in micro-gear-pumps for hypergolic and ?green? propellants in order to develop and demonstrate a micropump for MON-25 and mono methyl hydrazine (MMH) bipropellant thrusters. MON-25, with 25% of nitric oxide (NO) and 75% nitrogen tetroxide (NTO, N2O4), allows lowering the oxidizer freezing point to -55 C, which is a close match to that of the fuel, MMH (which is around -51 C). While toxic, this propellant combination is hypergolic and allows operations over a wide range of temperatures, particularly in extremely cold environments as those envisioned for many future missions. For NASA deep space and Moon/Mars missions, such as lunar lander and Mars ascent vehicles, the introduction of a micropump in the propulsion system provides significant performance benefits. For missions with high delta-Vs, the system wet mass is greatly reduced, or at fixed total wet mass, scientific payload mass increases. For example, in the case of a lunar lander (delta-V > 3,000 m/s), a two-stage configuration can be replaced by a pump-fed single-stage system of the same mass while the pressure-fed would have to be larger. Flight Works is proposing to develop and characterize micropumps suitable for 5 lbf and 100 lbf MMH/MON-25 thrusters. These will be used to perform pump-fed MMH/MON-25 hot-fire test demonstrations of the technology under representative environmental conditions in order to reach a TRL 6 by the end of Phase II. More »

Anticipated Benefits

Primary U.S. Work Locations and Key Partners

Share this Project

Organizational Responsibility

Project Management

Project Duration

Technology Maturity (TRL)

Technology Areas

Light bulb

Suggest an Edit

Recommend changes and additions to this project record.
^