NOFBX™ Monopropulsion Systems
- Develop high performance, liquid/gas monopropellant blends with bipropellant performance (NOFBX™monopropellants) that are low cost, non-toxic, self-pressurizing, and space-storable.
- Develop NOFBX™ fluid regulation systems with redundant anti-flashback inhibits.
- Develop robust, high temperature NOFBX™ gas generator cores and rocket thruster designs that can be operated over >10x dynamic range of thrust and in short pulse or continuous thrust modes.
NOFBX™ 100 lbf engine with carbon-carbon vacuum nozzle in front of an
RL-10 upper stage engine crudely illustrating difference in engine complexity
Short duration atmospheric pulse test of NOFBX™ 100 lbf engine combustion core.
12 m (40 ft) impact test of NOFBX™ monopropellant drop test article demonstrating insensitivity of the NOFBX™ monopropellants (4 different series were tested) to a high energy fall. The 12 m drop test is a MIL-STD2105D test requirement for assuring impact insensitivity of a container containing an energetic material.
Principal Investigators - Greg Mungas, David Fisher
Main Engine Assembly Flight System Engineer - Suparna Mukherjee
Propellant Chief Flight and Ground System Engineer - Chris Mungas
DA Flight Systems Engineer - Andrew Bingham
Demonstrated complex thruster design, characterized monopropellant specific impulse, characterized monopropellant physical properties, and defined ground handling safety procedures.
- Terrestrial Spinoff - Under IR&D funding, Firestar Technologies has been studying the development of very low specific emission fuels (combustion products are very similar to what is naturally occurring in the atmosphere) for renewable energy applications
- Awarded Phase I SBIR to study physics of NOFBX™ ignition in order to ultimately develop optimal miniature, low energy ignition systems for use with NOFBX™ propellants
- Awarded subcontract with commercialization partner Innovative Space Propulsion Systems (ISPS), LLC to further characterize NOFBX™ monopropellants as well as develop, qualify, and flight acceptance test an NOFBX™ deeply throttleable 100 lbf engine as part of a Flight Experiment to the International Space Station awarded to ISPS.
- Awarded Phase I/II SBIR to develop a prototype Single-Stage to Orbit NOFBX™ propulsion system for launching scientific samples from Mars back to Earth for a potential Mars Sample Return mission.
- Baseline propulsion option for Odyssey Space Research’s Altair (Lunar Lander Module) ascent main engine, descent stage RCS thrusters, and ascent stage RCS thrusters.
- NASA 2008-2010 Phase I/II SBIR development of NOFBX™ 25 - 100 lbf class engines for manned program ACS engines and scaled down test engines for future ascent stage engine testing.
- Completed 2008 NOFBX™ thruster exhaust plume interaction study with simulated Europa ice for feasibility study of a soft land Europa scientific probe (funded through Arizona State University).
- Completed 2005-2007 NASA Mars Advanced Technology Program award in Low Cost propulsion technologies (NASA NOFBOBS). Under this program the NOFBX™ monopropellants were invented, developed, and characterized for use in rocket thruster and power applications. In addition, preliminary NOFBX™ feed system hardware and breadboard NOFBX™ rocket thrusters have been demonstrated.
- Licensed NOFBX™ propulsion technology to commercialization partner, Innovative Space Propulsion Holdings, LLC and its subsidiaries.
- Two issued patents, 10 additional Pending Patents
- G.S. Mungas, D.J. Fisher, J.A. Smith, K.W. Doyle, G.H. Peters, A.P. London, L. Droppers, J. Fryer, S. Coley, T. Delange, NOFBX™ COLT Engine Development and Testing, Joint Army, Navy, NASA, Air Force (JANNAF) Interagency Propulsion Conference, SPS-IIE-3, CPIA/JHU, Colombia, MD (May 2010)
- G.S. Mungas, Regeneratively-Cooled, Vortex-Jacket, Fluids and Heat Transfer Model for Rocket Combustion Chambers, Joint Army, Navy, NASA, Air Force (JANNAF) Interagency Propulsion Conference, LPS-IIP-3, CPIA/JHU, Colombia, MD (May 2010)
- G.S. Mungas, D.J. Fisher, M. Johnson, B. Rishikof, NOFB Monopropulsion System for Lunar Ascent Vehicle Utilizing Plug Nozzle Ascent Engine. Joint Army, Navy, NASA, Air Force Interagency Propulsion Conference (JANNAF), LPS-II-33, CPIA/JHU, Colombia, MD (Dec 2008).
- G.S. Mungas, D.J. Fisher, C.B. Mungas, B. Carryer, NOFB Monopropellants – Background, Characterization, and Testing. Joint Army, Navy, NASA, Air Force Interagency Propulsion Conference (JANNAF), SPS-I-11, CPIA/JHU, Colombia, MD (Dec 2008).
- G.S. Mungas, D.J. Fisher, Regeneratively-Cooled Porous Media Jacket Theory and Model. Joint Army, Navy, NASA, Air Force (JANNAF) Interagency Propulsion Conference, LPS-II-30, CPIA/JHU, Colombia, MD (Dec 2008)
- G.S. Mungas, G. S., Fisher, D. J., Mungas, C. D., and Carryer, B., “NOFB Monopropellants – Background, Testing, and Characterization,” JPL Technical Report to Subcontract 1265181, 2008.
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