NOVELTY - A monopropellant comprises nitrous oxide and at least one hydrocarbon fuel.    USE - As monopropellant (claimed) for rocket propulsion, working fluid production, or energy or gas generation; as propulsion propellants; in earth-orbiting spacecraft and missile propulsion systems, launch vehicle upper stage propulsion systems and booster stages, deep space probe propulsion and power systems, deep space spacecraft ascent and earth return stages, precision-controlled spacecraft station-keeping propulsion systems, human-rated reaction control propulsion systems, spacecraft lander descent propulsion, power, pneumatic systems for excavation, spacecraft pneumatic science sample acquisition and handling systems, micro-spacecraft high performance propulsion systems, military divert and kill interceptors, high altitude aircraft engines, aircraft backup power systems, remote low temperature power systems, combustion powered terrestrial tools including high temperature welding and cutting torches as well as reloadable charges for drive mechanisms (e.g. nail guns, anchor bolt guns); for generating thrust, gas generation, and/or power (mechanical and/or electrical) generation.    ADVANTAGE - The monopropellant is stable, storable and exhibits high specific impulse (Isp) performance. Due to physical properties of the nitrous molecule, fuel/nitrous blends demonstrate high degrees of miscibility as well as excellent chemical stability. They lend themselves well to power generation in demanding situations where some specific cycle creates useable work and for providing gas pressure and/or heat for inflating deployable materials. The monopropellant has high specific impulse, low toxicity and allows for easy storage and handling in addition to other desired characteristics. The mixtures of these fuels based on oxidizer-to-fuel ratio (O/F) generates desired monopropellant characteristics including, Isp, miscibility over a wide temperature and pressure range, favorable fluid handling performance, low freezing points, rapid combustion kinetics for fast engine response times, relatively high thermal decomposition limits, low mechanical shock sensitivity and impact-induced detonation, relatively high storage densities, and exhaust gas chemistries that do not produce carbon fouling or hot oxidizing environments that are difficult, to accommodate with combustor or reaction chamber design materials. The Isp performance for the nitrous oxide fuel (NOFB) blend monopropellant is higher than the hydrazine monopropellant.