- Nitrous oxide fuel blend
Nitrous Oxide Fuel Blend propellants are a class of liquid rocket propellants. The fuel and oxidizer are blended and stored, and are sometimes referred to as 'mixed monopropellants'. Upon use, the propellant is heated or passed over a catalyst bed and the Nitrous oxide decompose into oxygen-rich gasses. Combustion then ensues. Special care is needed in the chemical formulation and engine design to prevent detonating the stored fuel.
NOFBX is a recent example, developed by Firestar Technologies LLC.
Nitrous oxide decomposes into hot oxygen-rich air, and requires no separate supply of oxidizer such as the liquid oxygen used in many high performance rocket engines today. Consequently, it can be used as a monopropellant by itself. For added performance nitrous oxide may also be blended with a range of different fuels and emulsifiers. Such a blend of an oxidizer and a fuel is called a mixed monopropellant. It combines the simplified plumbing of a monopropellant with the performance of a bipropellant.
German rocket scientists were experimenting with nitrous oxide fuel blends as early as 1937. Nitrous oxide fuel blends testing continued throughout World War II. The promise of high performance, greater range and lighter feed systems drove experimentation with blends of nitrous oxide and ammonia, which resulted in numerous explosions and demolished motors.[Full citation needed] Until recently, (~2003) the complexities involved in building propulsion systems that can safely handle nitrous oxide fuel blend monopropellants have been a deterrent to serious development since the end of WWII.
NOFBX is the trademarked name for a proprietary nitrous oxide/fuel/emulsifer blended mono-propellant developed by Firestar Technologies LLC.. NOFBX has a higher ISP and is less toxic than other monopropellants currently used in space applicatons, such as hydrazine. Flight testing of NOFBX engines is planned on the ISS in 2012.[Full citation needed]
"NOFBX is being promoted as a “game changing” technology with the following characteristics:
- constituents are widely available from chemical suppliers, inexpensive and safe to handle.
- can be transported and handled without undue precautions or hazards.
- effluents are non-toxic and produces no accumulated deposits or contamination.
- propulsion system has high Isp (320-340 s) – similar to the most common bi-propellant.
- has far better lift capability than the current workhorse monopropellant, hydrazine.
- is tolerant to a wide thermal range; storable at room temperature on the ground and is Space-storable.
- [is projected to] lower cost compared to existing propulsion systems of comparable performance.
- is monopropellant, which significantly reduces the need for auxiliary hardware, saving cost, volume, and mass for launch systems.
- utilizes cool running thrusters that dramatically reduce thermal design challenges.
- burns in liquid, gas, and two-phase flow.
- does not have the materials compatibility constraints of traditional hypergolic systems."
Recent work on the decomposition of nitrous oxide has raised concerns about the safety risks of mixing hydrocarbons with nitrous oxide. By adding hydrocarbons, the barrier to an explosive decomposition event is lowered significantly. 
- ^ a b c Messier, Doug (2011-08-09). "A Non-Toxic Fuel From the Mojave Desert". Parabolic Arc. http://www.parabolicarc.com/2011/08/09/a-non-toxic-fuel-from-the-mojave-desert/. Retrieved 2011-08-09. "Innovative Space Propulsion Systems will test a green, high-performance mono-propulsion technology called NOFBX at the International Space Station ... in late 2012."
- ^ a b Joiner, Stephen (2011-05-01). "The Mojave Launch Lab". Air & Space Smithsonian. http://www.airspacemag.com/space-exploration/The-Mojave-Launch-Lab.html. Retrieved 2011-03-18 (online precedes the print edition date).
- ^ John D. Clark, Ignition! An Informal History of Liquid Rocket Propellants
- ^ NOFBX
- ^ NOFBX presentation
- ^ Karabeyoglu, A. et. al Modeling of N2O Decomposition Events 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Hartford CT 2008
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, 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, 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)
Spacecraft propulsion Chemical
propulsionClosed systemOpen system
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